Minimize Hayabusa-2

Hayabusa-2, Japan's second Asteroid Sample Return Mission

Spacecraft   Launch   Mission Status   Sensor Complement   MASCOT    MASCOT Instruments
Sample Return Capsule   References

Hayabusa-2 is JAXA's (Japan Aerospace Exploration Agency) follow-on mission to the Hayabusa mission, the country's first round-trip asteroid mission that sent the Hayabusa (MUSES-C) spacecraft to retrieve samples of asteroid Itokawa. The initial Hayabusa mission launched in May 2003 and reached Itokawa in 2005; it returned samples of Itokawa — the first asteroid samples ever collected in space — in June 2010. Hayabusa means 'falcon' in Japanese. 1) 2) 3) 4)

The objective of the Hayabusa-2 sample return mission is to visit and explore the C-type asteroid 1999 JU3, a space body of about 920 m in length and of particular interest to researchers, because it consists of 4.5 billion-year-old material that has been altered very little. Measurements taken from Earth suggest that the asteroid's rock may have come into contact with water. The carbonaceous or C-type asteroid is expected to contain organic and hydrated minerals, making it different from Itokawa, which was a rocky S-type (stony composition) asteroid.

Primitive bodies are celestial bodies which contain information of the birth or the following evolution of our solar system. In larger bodies such as the Earth, the pristine materials inside were once melted and we cannot access older information. On the other hand, hundreds of thousands of asteroids and comets discovered ever, though they are very small, retain memories of when and where they were formed in the solar system. Exploration of such primitive bodies will provide us an essential clue for how our solar system was formed and has grown, and how the primary organic materials of life on the Earth were composed and evolved, which will be important knowledge also in investigating formation and evolution of exoplanets.

Among primitive bodies, asteroids can be classified into several groups according to the spectroscopic observation by telescopes. Inside the asteroid belt between the Mars and Jupiter, it is known that distribution of each group varies according to the distance from the Sun.

In the region close to the Sun, we can observe many 'S-type asteroids' whose primary component is expected to be stony. These will give us hints about components of stony planets such as the Earth and Mars. S-type asteroids have been expected to be the birthplace of 'ordinary chondrite', the most common meteorites on the Earth. This hypothesis was extensively confirmed by exploration of S-type asteroid "Itokawa" by JAXA's asteroid probe Hayabusa.

Most commonly distributed around the midst of the asteroid belt are 'C-type asteroids' expected to contain substantial organic or hydrated minerals. This type is expected to be the birthplace of 'carbonaceous chondrite', and an important target for investigation of origin of life on earth. The Hayabusa-2 mission, following Hayabusa, is planning a sample-return from C-type asteroids.

Around the dark and cold outer edge of the belt, closer to Planet Jupiter rather than to Mars, there are many P-type or D-type asteroids, expected to be more primitive than the S- or C-type ones. Trojan groups sharing their orbits with Jupiter are repositories of D-type asteroids. Active comets abundant in volatile components, born in further space and changed its orbit relatively recently to come closer to the Sun, or "dormant comet nuclei" depleting gases or dusts and difficult to distinguish from asteroids, are also quite essential targets. Because meteorites from D-, P-type asteroids or comet nuclei have been scarcely discovered on the Earth, the surface materials and constructions of these distant bodies are entirely unknown. Materials yet to be acquired, holding the earliest information at the birth of the solar system, may be discovered. The successive mission after "Hayabusa-2" is discussed to fetch samples from such bodies.

In this respect, JAXA will conduct, not only random single missions, but programmatic and systematic mission series successively, by Hayabusa, Hayabusa-2 and post -Hayabusa-2 for sample-return from typical primitive bodies. This will allow a unified understanding of various primitive bodies, revealing of components and construction of the whole solar system, and elucidation of the mystery behind its origin and evolution. This successive sequence is directed to the more distant and more primitive bodies from the scientific view, with more sophisticated technologies.

Table 1: Some background on the programmatic exploration of primitive bodies

Hayabusa →Visit to S-type Asteroid

Hayabusa-2 →Visit to C-type Asteroid

Technological demonstrator:
- Round-trip to asteroid
- Sample return

1) Science:
-
Origin and evolution of the solar system
- Organic matter, H2O

Engineering:
- Ion engine
- Autonomous navigation
- Sample collection
- Reentry capsule

2) Engineering:
- Technology: more reliable and robust
- New challenge : ex) impactor

Science: Origin and evolution of the solar system
-
Remote sensing observation
- Sample analysis

3) Exploration:
- Extend the area that humanity can reach
- Spaceguard, Resources, Research for manned mission, etc.

Table 2: Objectives : Hayabusa vs Hayabusa-2 5)

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Figure 1: Overall schedule of the Hayabusa-2 mission (image credit: JAXA)

 

Detailed information of asteroid 1999JU3 has been obtained by observations of ground-based telescopes. According to observation data of 2008, the diameter of 1999JU3 is estimated to be about 900 m, larger than that Itokawa, and the rotation period is around 7.6 hours. Observation of the reflected sunlight spectrum showed, that it has features of a C-type asteroid. It is rather difficult to determine the spin axis of asteroid 1999JU3 because of its rather spherical shape.

Figure 2 shows the orbit of asteroid 1999 JU3. The orbit is similar to that of Itokawa, and it is orbiting from just inside the orbit of the Earth to just outside the orbit of Mars. The inclination of the orbit is small like the one of Itokawa. Such an orbit is suitable for a small spacecraft like Hayabusa-2 to reach and return to Earth.

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Figure 2: Illustration of the asteroid 1999JU3 orbit within the solar system (image credit: JAXA)

Legend to Figure 2: The blue circled lines in the figure illustrate the orbits of Mercury, Venus, Earth and Mars from inside, respectively, Itokawa's orbit is green, while the yellow orbit is that of 1999JU3.

The asteroid was discovered in 1999 by the LINEAR (Lincoln Near-Earth Asteroid Research) project, and given the provisional designation 1999JU3 (it hasn't been named so far). LINEAR is a collaboration of the United States Air Force, NASA, and MIT/LL (Massachusetts Institute of Technology /Lincoln Laboratory) for the systematic discovery and tracking of near-Earth asteroids.

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Figure 3: Schematic of the science of Hayabusa and Hayabusa-2 missions (image credit: JAXA)

 

Project short history:

The Hayabusa-2 mission was proposed in 2006 at first. In this first proposal, the spacecraft was almost same as that of Hayabusa, because the project team wanted to start it as soon as possible. Of course, the team realized that parts had to be modified where trouble occurred in Hayabusa, but there were no major changes. The launch windows to go for launch to asteroid 1999 JU3 were in 2010 and 2011. However, JAXA could not start Hayabusa-2 mission immediately, because no budget was available. Hence, the launch opportunity was missed. The next launch window came up in 2014. Thus, the project postponed the launch date, and continued proposing Hayabusa-2. Since the launch was delayed, the project had time to change the spacecraft a little. New instruments were added, such as a Ka-band antenna and what is called "impactor." The project even calls Hayabusa-2 a new spacecraft. 6)

In May 2011, the status of Hayabusa-2 project shifted to Phase-B, starting with the design of the spacecraft. In March 2012, the CDR (Critical Design Review) was done, and the team started manufacturing the flight model. The initial integration test started at the beginning of 2013, and the final integration test started at the end of 2013. At present (September 2014), the team has almost finished the final integration test, and the spacecraft will be shipped to the launch site soon.

International collaborations: The Hayabusa-2 mission involves international collaborations with Germany, the United States, and Australia. DLR (German Aerospace Center) and CNES (French Space Agency) are providing the small lander MASCOT. NASA was already a partner in the Hayabusa mission, a similar collaboration is under consideration for Hayabusa-2. The third collaboration is with Australia for capsule reentry as in the case of the Hayabusa mission.

 


 

Spacecraft:

Japan's Hayabusa-2 spacecraft is designed to study asteroid 1999 JU3 from multiple angles, using remote-sensing instruments, a lander and a rover. It will collect surface- and possibly also subsurface materials from the asteroid and return the samples to Earth in a capsule for analysis. The mission also aims to enhance the reliability of asteroid exploration technologies. 7) 8) 9)

In the current plan, the launch window for Hayabusa-2 is in late 2014. With this schedule, Hayabusa-2 will reach the asteroid in the middle of 2018, and return to the Earth at the end of 2020.

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Figure 4: Artist's rendition of the Hayabusa-2 spacecraft (image credit: JAXA, Akihiro Ikeshita)

The Hayabusa-2 mission will utilize new technology while further confirming the deep space round-trip exploration technology by inheriting and improving the already verified knowhow established by Hayabusa to construct the basis for future deep-space exploration.

The configuration of Hayabusa-2 is basically the same as that of Hayabusa, with modifications of some parts by introducing novel technologies that evolved after the Hayabusa era. For example:

• The HGA (High Gain Antenna) for Hayabusa featured a parabolic shape, while Hayabusa-2 uses two planar HGAs with a considerably lower mass but with the same performance characteristics. The reason why Hayabusa-2 has two HGAs is that spacecraft has two communication links, Ka-band as well as the X-band links. In daily operations support, the team uses the X-band for data transmission, but for the download of the asteroid observation data, the Ka-band is used to take advantage of the higher data rate of 32 kbit/s, provided by the Ka-band link. The DDOR (Delta-Differential One-way Ranging) technique is used for very accurate plane-of-sky measurements of spacecraft position which complement existing line-of-sight ranging and Doppler measurements.

• The AOCS (Attitude and Orbit Control Subsystem) of Hayabusa-2 was improved, now featuring 4 reaction wheels for a more reliable service in case of need.

- During the cruise phase, Hayabusa-2 controls its attitude with only one reaction wheel to bias the momentum around the Z-axis of the body. This is to save the operating life of reaction wheels for other axes, because the project experienced that two reaction wheels of three equipped on Hayabusa were broken after the touchdown mission. 10)

- In this one wheel control mode, the angular momentum direction is slowly moved in the inertial space (generally called precession) due to the solar radiation torque. This attitude motion caused by the balance of the total angular momentum and solar radiation pressure is known to trace the Sun direction automatically with ellipsoidal and spiral motion around Sun direction. Based on this knowledge of the past, the attitude dynamics model for the Hayabusa-2 mission had been developed before the launch. According to the newly developed attitude dynamics model of Hayabusa-2, the precession trajectory is almost the ellipsoid around the attitude equilibrium point, and this equilibrium point is determined mainly by the phase angle around Z-axis of the body.

- In the actual operation of Hayabusa-2, the spacecraft experienced already the one wheel control mode, and the attitude motion in this mode is nearly corresponding to the expected motion based on the dynamics model developed before the launch. The precession trajectory is ellipsoid around the equilibrium point, and the attitude dynamics model is verified by the actual flight data. In this one wheel operation, the Sun aspect angle is restricted within a certain limit angle in terms of the thermal condition of the spacecraft. Because the precession radius is determined by the initial attitude and the equilibrium point, the Sun aspect angle almost exceeds the limit angle due to the precession without change of the equilibrium point. At this operation, the project executes the attitude maneuver around the Z-axis to change the equilibrium point, in order to reduce the Sun aspect angle - and succeeded. After that, the project executed the maneuver again to change the equilibrium point to a close point in order to make the small precession trajectory (Ref. 10).

• IES (Ion Engine System) has been modified to account for the aging effect during extended support periods. The thrust level of IES was increased by 25%, using the same Xe microwave discharge ion engine system.

IES will be used for orbit maneuvers during the cruising of the Hayabusa-2's onward journey to the asteroid and return trip to Earth. The engine enables to make the round trip with only one tenth of the power consumption compared to that of chemical propellant.

Major improvements from the Hayabusa mission are:

- Countermeasures to plasma ignition malfunction of one ion source of an ion engine. Carefully coordinating each part of the ion engine to improve both ion source propulsion generation efficiency and ignition stability.

- Countermeasures to degradation and malfunction of three neutralizers that occurred after 10,000 to 15,000 hours of operation. To make the neutralizer's lifespan longer, the walls of the electric discharge chamber are protected from plasma and the magnetic field has been strengthened to decrease the voltage necessary for electron emission.

- The maximum power was successfully increased to 10 mN per ion engine from the conventional 8 mN.

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Figure 5: Photo of the IES assembly (image credit: JAXA)

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Figure 6: Top view of the deployed Hayabusa-2 spacecraft illustrating the various elements of the spacecraft (image credit: JAXA)

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Figure 7: Bottom view of Hayabusa-2 spacecraft illustrating the various elements of the spacecraft (image credit: JAXA)

The Hayabusa-2 spacecraft has a stowed size of 1.6 m x 1 m x 1.25 m (height). With the solar panels deployed, the 600 kg satellite as a width of 6 m.

Spacecraft structure

Size: 1.6 m×1.0 m×1.4 m(height) box structure with two fixed SAPs
Mass: 609 kg(wet), 493 kg(dry)

Data handling subsystem

- COSMO16 based DHU-PIM bus system
- Onboard autonomous command generation feature
- 1GB data recorder

AOCS (Attitude and Orbit Control Subsystem)

- HR5000S based processor, double redundant
- 4 Reaction Wheels, 2 IRUs, 2 Star Trackers (STT), 4 CSAS Coarse Sun Aspect Sensors), 4 ACS (Accelerometers)
- Sensors for Proximity Operation: LIDAR, LRF, 5 Target Makers (TM), Flash lamp (FLASH)
- ONC (Optical Navigation Cameras): Wide: ONC-W1, ONC-W2, (FOV 54º x 54º, 1Mpix); Telescopic: ONC-T (FOV 5.4º x5.4º, 1Mpix, 5 band filter)

Propulsion subsystems

- RCS (Reaction Control System): Bi-propellant hydrazine system, 20 N thruster x 12
- IES (Ion Engine System): Xe microwave discharge ion engine system; Maximum thrust 28 mN, Isp=2800 s; 4 thruster heads on gimballed stage; 3 operative at once (4/3 redundant)

Power subsystem

SAP (Solar Array Paddle): -1.4 kW@1.4 AU, 2.6 kW@1AU; BAT: Li-ion battery 13.2 Ah; power bus: SSR (Series Switching Regulator) system, 50 V bus.

Communication subsystem

- X-band TT&C (coherent X-up/X-down), data rate: 8 bit/s-32 kbit/s, double redundant.
- Ka-band telemetry (coherent X-up/Ka-down), data rate: 8 bit/s-32 kbit/s
- Normal/Regenerative Ranging System
- DDOR or ΔDOR (Delta-Differential One-way Ranging) support
- 1 X-HGA, 1 Ka-HGA, 1 two-axis gimballed X-MGA, 3 X-LGA

Table 3: Spacecraft system parameters

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Figure 8: Photo of the Hayabusa-2 flight model, taken in Aug. 31, 2014, before shipping to the launch site, TNSC (Tanegashima Space Center). The SRC (Sample Return Capsule) is mounted to the bottom front side center of the spacecraft (image credit: JAXA)

 

Launch: The Hayabusa-2 spacecraft was launched on December 03, 2014 (04:22:04 UTC) on a H-IIA vehicle (No. 26) from TNSC (Tanegashima Space Center), Japan. The launch service provider was MHI (Mitsubishi Heavy Industries, Ltd). The launch was nominally and about 1 hr 47 minutes and 21 seconds after liftoff, the separation of the Hayabusa-2 spacecraft into an Earth-escape trajectory was confirmed. 11) 12)

Secondary payloads:

• Shin'en-2, a nanosatellite technology demonstration mission (17 kg) of Kyushu Institute of Technology and Kagoshima University, Japan. The objective is to establish communication technologies with a long range as far as moon. Shin'en-2 carries into deep space an F1D digital store-and-forward transponder which offers an opportunity for earthbound radio amateurs to test the limits of their communication capabilities.

• ArtSat-2 (Art Satellite-2)/DESPATCH (Deep Space Amateur Troubadour's Challenge), a joint project of of Tama Art University and Tokyo University. DESPATCH is a microsatellite of ~30 kg. The microsatellite carries a "deep space sculpture" developed using a 3D printer, as well as an amateur radio payload and a CW beacon at 437.325 MHz.

• PROCYON (PRoximate Object Close flYby with Optical Navigation) is a microsatellite (67 kg) developed by the ISSL (Intelligent Space Systems Laboratory) of the University of Tokyo and JAXA. The objective is to demonstrate microsatellite bus technology for deep space exploration and proximity flyby to asteroids performing optical measurements. 13)

Orbit: The trajectory of Hayabusa-2 for the whole mission is shown in the sun-earth fixed coordinate in Figure 9. The total cruising time is about 4.5 years, and the asteroid proximity period is about 1.5 years. So the total flight time is about 6 years. The departure C3 is 21 km2/s2, the total impulse of the ion engine is 2 km/s, and the reentry speed of the capsule is 11.6 km/s.

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Figure 9: Round-trip trajectory design for Hayabusa-2 (J2000EC Sun-Earth line-fixed coordinates), image credit: JAXA

Legend to Figure 9: Hayabusa-2 is equipped with a high-specific impulse ion engine system to enable the round-trip mission. First one year after launch is an interplanetary cruise phase called EDVEGA (Electric Delta-V Earth Gravity Assist).

 


 

Mission status:

• October 14, 2018: The second touchdown rehearsal of Hayabusa-2 will be performed from October 14 – 16. The purpose of this rehearsal is to confirm the operation characteristics of the LRF (Laser Range Finder) which performs the altitude measurement at short distances. To test this, the spacecraft will descend to an altitude of about 25 m. This will be the lowest altitude reached to date. 14)

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Figure 10: Schematic of the TD1-R1-A operation (image credit:JAXA)

- The first touchdown rehearsal (TD1-R1) was conducted between September 10 – 12. During this operation, problems occurred with the distance measurement taken with the LIDAR (laser altimeter) once the spacecraft had descended to about 600 m. This caused the spacecraft to rise autonomously. The issue was addressed by adjusting the settings on the laser altimeter and it was confirmed that there were no further issues during the subsequent separation operations of MINERVA-II1 and MASCOT. As the spacecraft was only able to descend to an altitude of 600 m during TD-R1, the LRF characteristics could not be verified. Therefore, we are performing this check with this rehearsal.

- Although this is the second time a rehearsal operation has been performed, the name is TD1-R1-A as it is re-starting the challenge of TD1-R1.

• October 12, 2018: Six minutes of free fall, a gentle impact on the asteroid and then 11 minutes of rebounding until coming to rest. That is how, in the early hours of 3 October 2018, the journey of the MASCOT asteroid lander began on Asteroid Ryugu – a land full of wonder, mystery and challenges. Some 17 hours of scientific exploration followed this first 'stroll' on the almost 900 m diameter asteroid. The lander was commanded and controlled from the MASCOT Control Center e at the DLR (German Aerospace Center) site in Cologne in the presence of scientific teams from Germany, France and Japan. MASCOT surpassed all expectations and performed its four experiments at several locations on the asteroid. Never before in the history of spaceflight has a Solar System body been explored in this way. It has now been possible to precisely trace MASCOT's path on Ryugu's surface on the basis of image data from the Japanese Hayabusa-2 space probe and the lander's images and data. 15)

- "This success was possible thanks to state-of-the-art robotic technology, long-term planning and intensive international cooperation between the scientists and engineers of the three space nations Japan, France and Germany," says Hansjörg Dittus, DLR Executive Board Member for Space Research and Technology about this milestone in Solar System exploration. "We are proud of how MASCOT was able to master its way across the asteroid Ryugu over boulders and rocks and send so much data about its composition back to Earth," says DLR Chair Pascale Ehrenfreund.

- MASCOT had no propulsion system and landed in free fall. Six minutes after separating from Hayabusa-2, and following the end of a ballistic trajectory, the landing module made its first contact with asteroid Ryugu. On the surface, MASCOT moved through the activation of a tungsten swing arm accelerated and decelerated by a motor. This made it possible for MASCOT to be repositioned to the 'correct' side or even perform hops across the asteroid's surface. The gravitational attraction on Ryugu is just one 66,500th of the Earth's, so the little momentum provided was enough: a technological innovation for an unusual form of mobility on an asteroid surface used for the first time in the history of space travel as part of the Hayabusa-2 mission.

Through a rock garden full of rough boulders and no flat surfaces

- To reconstruct MASCOT's path across the surface of Ryugu, the cameras aboard the Hayabusa-2 mother probe were aimed at the asteroid. The Optical Navigation Cameras (ONC) captured the lander's free fall in several images, detected its shadow on the ground during the flight phase, and finally identified MASCOT directly on the surface in several images. The pattern of the countless boulders distributed on the surface could also be seen in the direction of the respective horizon in oblique photographs of the lander's DLR MASCAM camera. The combination of this information unlocked the unique path traced by the lander.

- After the first impact, MASCOT smoothly bounced off a large block, touched the ground about eight times, and then found itself in a resting position unfavorable for the measurements. After commanding and executing a specially prepared correction maneuver, MASCOT came to a second halt. The exact location of this second position is still being determined. There, the lander completed detailed measurements during one asteroid day and night. This was followed by a small ‘mini-move' to provide the MicrOmega spectrometer with even better conditions for measuring the composition of the asteroid material.

- Finally, MASCOT was set in motion one last time for a bigger jump. At the last location it carried out some more measurements before the third night on the asteroid began, and contact with Hayabusa-2 was lost as the spaceship had moved out of line of sight. The last signal from MASCOT reached the mother probe at 21:04 CEST. The mission was over. "We were expecting less than 16 hours of battery life because of the cold night, says MASCOT project manager Tra-Mi Ho from the DLR Institute of Space Systems. "After all, we were able to operate MASCOT for more than one extra hour, even until the radio shadow began, which was a great success." During the mission, the team named MASCOT's landing site (MA-9) 'Alice's Wonderland', after the eponymous book by Lewis Carroll (1832-1898).

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Figure 11: MASCOT's approach to Ryugu and its path across the surface (image credit: JAXA/U. Tokyo/Kochi U/Rikkyo U/Nagoya U/Chiba Inst Tech/Meiji U/U Aizu/AIST)

A true wonderland

- Having reconstructed the events that took place on asteroid Ryugu, the scientists are now busy analyzing the first results from the acquired data and images. "What we saw from a distance already gave us an idea of what it might look like on the surface," reports Ralf Jaumann from the DLR Institute of Planetary Research and scientific director of the MASCOT mission. "In fact, it is even crazier on the surface than expected. Everything is covered in rough blocks and strewn with boulders. How compact these blocks are and what they are composed of, we still do not know. But what was most surprising was that large accumulations of fine material are nowhere to be found – and we did not expect that. We have to investigate this in the next few weeks, because the cosmic weathering would actually have had to produce fine material," continues Jaumann.

- "MASCOT has delivered exactly what we expected: an 'extension' of the space probe on the surface of Ryugu and direct measurements on site," says Tra-Mi Ho. Now there are measurements across the entire spectrum, from telescope light curves from Earth to remote sensing with Hayabusa2 through to the microscopic findings of MASCOT. "This will be of enormous importance for the characterization of this class of asteroids," emphasizes Jaumann.

- Ryugu is a C-type asteroid – a carbon-rich representative of the oldest bodies of the four-and-a-half-billion year-old Solar System. It is a 'primordial' building block of planet formation, and one of 17,000 known Near-Earth asteroids.

- On Earth, there are meteorites with a composition that could be similar to Ryugu's, which are found in the Murchison Range, Australia. However, Matthias Grott from the DLR Institute of Planetary Research and responsible for the radiometer experiment MARA is skeptical as to whether these meteorites are actually representative of Ryugu in terms of their physical properties: "Meteorites such as those found in Murchison are rather massive. However, our MARA data suggests the material on Ryugu is slightly more porous. The investigations are just beginning, but it is plausible to assume that small fragments of Ryugu would not survive the entry into the Earth's atmosphere intact."

Time (CEST)

Event

03:57:21

At an altitude of 51 m above asteroid Ryugu, MASCOT is pushed out of the Hayabusa2 supporting frame by means of a spring
mechanism behind a push-off plate at about 4 cm/s and starts to descend to Ryugu without control of its ground station.

04:03

Approximately six minutes later, MASCOT touches down on Ryugu, making contact with a block of rocks about three to four meters
high. The Optical Navigation Camera (ONC) from Hayabusa-2 records the process in high-resolution images. At the same time,
DLR's MASCAM acquires 20 images of the asteroid during the descent. MASCOT lands on the designated landing site MA-9
(Alice's Wonderland). It is located at about 300 degrees east and 30 degrees south.

Around 04:34
First location

After another approximately 31 minutes and several contacts with the surface, MASCOT reaches its first resting position. It is
asteroid day at the landing site and the surface measurements start.

Around 06:30

At the DLR Control Center in Cologne it is recognized that MASCOT is lying on an unfavorable side and thus cannot carry out
its planned experiments. All systems and experiments are operating as intended.

Around 09:20

An unscheduled command from the Earth is sent to Hayabusa-2 and from there to MASCOT to activate the swing arm to turn
the lander into its intended position for the experiments. The command time to Ryugu, which is about 300 million kilometers
away, is about 18 minutes one way.

Around 09:52

MASCOT has completed its first day-and-night cycle. The second day on Ryugu begins.

Around. 10:30
Second location

The maneuver has brought the desired result. MASCOT is in the right position, is now operational and automatically starts
to perform its four experiments again.

Around 12:51

The second daylight phase on Ryugu is slowly coming to an end, and MASCOT turns with Ryugu into its second asteroid night.

Around 17:28

MASCOT's third day on Ryugu begins.

Around 18:29
Third location

MASCOT successfully executes a mini-move. This maneuver was commanded by the operations team in Cologne to optimize
the position of the sensors of the experiments. Further scientific investigations are carried out.

Around 20:04
Fourth location

The last jump is commanded to MASCOT and the lander goes into the End of Life phase. Further scientific investigations
are carried out.

21:04

It is the end of the third day for MASCOT on Ryugu. In the meantime, more than 16 hours have passed – the lander's expected
maximum battery life. Contrary to the calculations, the battery still provides some power before the contact with MASCOT
breaks off by the entry of a radio shadow and the upcoming night. Instead of 16 hours, the experiments were able to work for
17 hours and 7 minutes.

Table 4: MASCOT's 17 hours and 7 minutes on Ryugu

• October 11, 2018: JAXA told reporters the Hayabusa-2 probe is now expected to touch down on the Ryugu asteroid in "late January" at the earliest, rather than at the end of this month as initially expected. JAXA project manager Yuichi Tsuda said they needed more time to prepare the landing as the latest data showed the asteroid surface was more rugged than expected. 16)

- "The mission... is to land without hitting rocks," Tsuda said, adding this was a "most difficult" operation. "We had expected the surface would be smooth... but it seems there's no flat area."

- Scientists are already receiving data from other subsatellites deployed on the surface of the asteroid. Last week, JAXA successfully landed a new 10 kg observation robot known as MASCOT (Mobile Asteroid Surface Scout). Ten days earlier, a pair of MINERVA-II micro-rovers were dropped onto the asteroid - marking the first time that moving, robotic observation devices have been successfully deployed.

- These rovers are taking advantage of Ryugu's low gravity to jump around on the surface - travelling as far as 15 m and staying above the surface for as long as 15 minutes - to survey the asteroid's physical features with cameras and sensors.

• October 05,2018: It was a day full of exciting moments and a happy team of scientists and engineers: late in the afternoon of 3 October 2018, the German-French lander MASCOT completed its historic exploration of the surface of the asteroid Ryugu at 21:04 CEST, as its battery ran out. On-asteroid operations were originally scheduled to last 16 hours after separation from the Japanese mother craft Hayabusa-2. But in the end, the battery lasted more than 17 hours. Upon landing in the early morning and subsequently relocating using the built-in swing arm, all instruments collected detailed data on the composition and nature of the asteroid. The on-board camera provided pictures of the landing, hopping maneuvers and various locations on the surface. 17) 18)

a) As planned, MASCOT was able to acquire data about the composition and texture of the asteroid at several locations.

b) Before the battery depleted, the lander sent all scientific data to the Hayabusa-2 mothercraft.

c) New images from MASCOT's landing on asteroid Ryugu were presented by DLR, JAXA and CNES today at the International Astronautical Congress (IAC).

e) Focus: Space, exploration.

- For MASCOT, the Sun set three times on Ryugu. The lander was commanded and controlled from the MASCOT Control Center at the German Aerospace Center (Deutsches Zentrum für Luft- und Raumfahrt; DLR) in Cologne, in the presence of teams of scientists from Japan, France and Germany. All scientific data was transferred to the mother probe according to plan.

- "With MASCOT, it has been possible to, for the first time, explore the surface of an asteroid directly on site so extensively," says Hansjörg Dittus, DLR Executive Board Member for Space Research and Technology. "A mission like this can only be done working in close cooperation with international partners – bringing together all their expertise and commitment." With MASCOT, DLR has been working closely with the Japanese space agency JAXA and the French space agency CNES.

Figure 12: Hayabusa2 acquires images of MASCOT on its approach to Ryugu. Three consecutive images acquired on 3 October 2018 between 03:57:54 and 03:58:14 CEST with the wide-angle optical navigation camera (ONC-W2). MASCOT can be seen at the top (image credit: JAXA, Tokyo University, Kochi Univ., Rikkyo Univ., Nagoya Univ., Chiba Institute of Technology, Meiji Univ., Aizu Univ., AIST)

- Jumps and a mini-move: MASCOT landed safely on Ryugu in the early morning of 3 October 2018. "After a first automated reorientation hop, it ended up in an unfavorable position. With another manually commanded hopping maneuver, we were able to place MASCOT in another favorable position thanks to the very precisely controlled swing arm," says MASCOT operations manager Christian Krause from DLR. From that position, MASCOT completed a complete measurement sequence with all instruments over one asteroid day and an asteroid night. "Later, we were able to continue the activities on Ryugu with a special maneuver," adds Ralf Jaumann, DLR planetary scientist and scientific director of MASCOT. "With a 'mini-move' we recorded image sequences that will be used to generate stereo images of the surface once they have been analyzed."

- During the first maneuvers, MASCOT moved several meters to the next measuring point. Finally, and seeing that the lander still had battery power left, the researchers dared to make a bigger jump. All in all, MASCOT explored Ryugu for three asteroid days and two asteroid nights. A day-night cycle on Ryugu lasts about 7 hours and 36 minutes. At 21:04 CEST, communications with Hayabusa-2 were interrupted, because of the radio shadow entering with each asteroid rotation. Hayabusa-2 is now returning to its home position, at an altitude of 20 km above the asteroid's surface.

- In addition to the images acquired by the DLR camera MASCAM, a DLR radiometer, a magnetometer from TU Braunschweig and a spectrometer from the Institut d'Astrophysique Spatiale provided a variety of measurements on the temperature, magnetic properties and the composition of the near-Earth asteroid Ryugu.

- Waiting for the scientific data: MASCOT is now a silent inhabitant of Ryugu. "The evaluation of the valuable data has just begun," says MASCOT project manager Tra-Mi Ho from the DLR Institute of Space Systems. "We will learn a lot about the past of the Solar System and the importance of near-Earth asteroids like Ryugu. Today, I look forward to the scientific publications that will result from MASCOT and the remarkable Hayabusa-2 mission of our Japanese partners. "Hayabusa-2 played a crucial role in the success of MASCOT. The Japanese probe brought the lander to the asteroid. Thanks to precise planning and control, the communication links to the lander could be optimally used for data transmission, so that the first pictures were received on the very day of landing. The remaining scientific data, which was transmitted to Hayabusa-2, will be sent to Earth in the coming days.

• October 03, 2018: The near-Earth asteroid Ryugu, located approximately 300 million km from Earth, has a new inhabitant: On 3 October 2018, the Mobile Asteroid Surface Scout (MASCOT) landed on the asteroid and began to work. The lander successfully separated from the Japanese Hayabusa-2 space probe at 03:58 CEST (Central European Summer Time, corresponding to 01:58 UTC). The 16 hours in which the lander will conduct measurements on the asteroid's surface have begun for the international team of engineers and scientists. The day before, JAXA's Hayabusa-2 began its descent towards Ryugu. MASCOT was ejected at an altitude of 51 meters and descended in free fall – slower than an earthly pedestrian – to its destination, the asteroid. The relief about the successful separation and subsequent confirmation of the landing was clearly noticeable in the MASCOT Control Center at DLR in Cologne as well as in the adjoining room: "It could not have gone better," explained MASCOT project manager Tra-Mi Ho from the DLR Institute of Space Systems. "From the lander's telemetry, we were able to see that it separated from the mothercraft, and made contact with the asteroid surface approximately 20 minutes later." The team is now in contact with the lander. 19) 20)

- The moment of separation was one of the risks of the mission: If MASCOT had not successfully separated from Hayabusa-2 as planned and often tested, the lander's team would hardly have had the opportunity to solve this problem. But everything went smoothly: Already during the descent on the asteroid, MasCam (MASCOT Camera) took 20 pictures, which are now stored on board the Japanese space probe. "The camera worked perfectly," says Ralf Jaumann, DLR planetary scientist and scientific director of the camera instrument. "The team's first images of the camera are therefore safe." The magnetometer team was also able to recognize in the data sent by MASCOT that the MASMAG instrument had switched on and performed measurements prior to the separation. "The measurements show the relatively weak field of the solar wind and the very strong magnetic disturbances caused by the spacecraft," explains Karl-Heinz Glaßmeier from the Technical University of Braunschweig. "At the moment of the separation, we expected a clear decrease of the interference field – and we were able to recognize this clearly."

- MASCOT came to rest on the surface approximately 20 minutes after the separation. Now, the team is analyzing the data that MASCOT is sending to Earth to understand the events occurring on the asteroid Ryugu. The lander should now be on the asteroid's surface, in the correct position thanks to its swing arm, and have started to conduct measurements independently. There are four instruments on board: a DLR camera and radiometer, an infrared spectrometer from IAS ( Institut d'Astrophysique Spatiale, Orsay, France) and a magnetometer from the TU Braunschweig. Once MASCOT has performed all planned measurements, it is expected to hop to another measuring location. This is the first time that scientists will receive data from different locations on an asteroid. "With MASCOT, we have the unique opportunity to study the Solar System's most primordial material directly on an asteroid," emphasizes DLR planetary researcher Ralf Jaumann. With the data acquired by MASCOT and the samples that Hayabusa2 brings to Earth from Ryugu in 2020, scientists will not only learn more about asteroids, but more about the formation of the Solar System. "Asteroids are very primordial celestial bodies."

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Figure 13: Shadow of MASCOT on asteroid Ryugu during descent: DLR's MasCam on board MASCOT acquired this image as it descended to the the asteroid Ryugu 3.5 minutes after separating from its mothercraft Hayabusa-2. In the image, the lander is ~20 m above the asteroid's surface, and MASCOT's shadow can be seen at the top right (image credit: MASCOT/DLR/JAXA)

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Figure 14: Artist's rendition of MASCOT during the landing approach (image credit: DLR (CC-BY 3.0))

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Figure 15: Left: Illustration of MASCOT separating from Hayabusa-2. Right: Illustration of MASCOT landing on the surface of Ryugu (image credit: JAXA, Ref. 20)

- For the landing site for MASCOT, a region in the southern hemisphere of Ryugu was selected (Figure 16). This location was selected based on criteria that ensured no overlap between the landing sites for the touchdown of Hayabusa-2, MINERVA-II1 and MASCOT, the time to be able to communicate with Hayabusa-2, the duration of sunlight exposure and expectation of scientifically meaningful exploration.

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Figure 16: MASCOT landing site candidate region (light blue area). Since MASCOT is expected to bounce several times after first touching down, a reasonably wide region was selected (image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, University of Aizu, AIST, CNES, DLR)

- MASCOT does not use solar cells but is equipped with a lithium primary battery built into the lander. The duration of the battery is about 16 hours (about two rotations of Ryugu), allowing MASCOT to operate continuously for two Ryugu days after a successful separation. Operation of the lander will end when the battery runs out.

• September 27, 2018: The MINERVA-II1 rovers were deployed on September 21 to explore the surface of asteroid Ryugu. Here is the second report on their activities, following our preliminary article at the start of this week. We end this report with a video taken by one of the rovers that shows the Sun moving across the sky as seen from the surface of Ryugu. Please take a moment to enjoy "standing" on this new world. 21)

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Figure 17: These images were taken by Rover-1B on 23 September 2018; confirmation of Rover-1B hop. Observation time (JST): Left: 09:50; Center: 09:55; Right: 10:00 (image credit: JAXA)

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Figure 18: This image was captured immediately before a hop of Rover-1B on 23 September 2018 at 09:46 JST (image credit: JAXA)

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Figure 19: Surface image from Rover-1B after landing, taken on 23 September at 10:10 JST (image credit: JAXA)

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Figure 20: Surface image taken from Rover-1A on September 23 2018 at 09:43 JST (image credit: JAXA)

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Figure 21: Rover-1A captured the shadow of its own antenna and pin. Surface image taken from Rover-1A MINERVA-II1 successfully on 23 September 2018 at 09:48 JST (image credit: JAXA)

The pins on the MINERVA-II rovers have three roles:

1) To increase friction when hopping

2) Protect the solar cells during landing

3) A few of the pins also have a temperature sensor, so surface temperature can be measured directly.

• On 21 September 2018, 180 million miles ( 290 million km) from Earth, a roughly 1.5 m2 cube descended towards a primitive space rock. After years of planning and 4 years in flight, this tiny spacecraft captured this ‘shadow selfie' as it closed in on asteroid Ryugu, just 80 m from the remnant of our Solar System's formation, 4.6 billion years ago. 22)

- The Hayabusa-2 spacecraft is operated by JAXA (Japanese Space Agency) and supported in part by ESA's Estrack Malargüe deep-space tracking station in Argentina. The spacecraft carries four small landers that will investigate the asteroid's surface, all four designed to gently fall onto the surface of the rocky boulder, taking advantage of its low gravity environment.

- Around the time this remarkable picture was taken, the spacecraft released its two MINERVA-II1 rovers which have since successfully landed and demonstrated an ability to hop around this rock-strewn body.

- "I cannot find words to express how happy I am that we were able to realize mobile exploration on the surface of an asteroid" enthused Yuichi Tsuda, Hayabusa-2 Project Project Manager, "I am proud that Hayabusa-2 was able to contribute to the creation of this technology for a new method of space exploration by surface movement on small bodies."

- The next stage will see the Mobile Asteroid Surface Scout (MASCOT) lander released onto the asteroid's surface. Developed by the German Aerospace Center (DLR) in cooperation with the French Space Agency (CNES) MASCOT has enough power for a 12-hour mission, in which it will analyze the asteroid's surface at two different sites.

- The Hayabusa-2 spacecraft itself will collect three samples from Ryugu, bringing them back to Earth in December 2020. These strange specimens will provide insights into the composition of this carbonaceous asteroid — a type of space rock expected to preserve some of the most pristine materials in the Solar System.

- As well as hopefully shining light on the origin and evolution of the inner planets, and the sources of water and organic compounds on Earth, this knowledge should help in efforts to protect our planet from marauding masses that come too close for comfort to our home planet.

- Understanding the composition and characteristics of near-Earth objects is vital to defending ourselves from them, if one were to head in our direction. ESA's proposed Hera mission to test asteroid deflection is an ambitious example of how we can get to know these ancient bodies better, all in the name of planetary defence.

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Figure 22: Hayabusa-2 took this selfie, i.e. its shadow projected onto Ryugu when the tiny spacecraft was closing in on the ancient rocky body, around the time when the two MINERVA-II1 rovers were released (image credit: JAXA)

• On 21 September 2018, the small compact MINERVA-II1 rovers separated from the Hayabusa-2 spacecraft (time of separation was 13:06 JST). The MINERVA-II1 consists of two rovers, Rover-1A and Rover-1B. We have confirmed both rovers landed on the surface of asteroid Ryugu. The two rovers are in good condition and are transmitting images and data. Analysis of this information confirmed that at least one of the rovers is moving on the asteroid surface. 23)

- MINERVA-II1 is the world's first rover (mobile exploration robot) to land on the surface of an asteroid. This is also the first time for autonomous movement and picture capture on an asteroid surface. MINERVA-II1 is therefore "the world's first man-made object to explore movement on an asteroid surface". We are also delighted that the two rovers both achieved this operation at the same time. "Each of the rovers is operating normally and has started surveying Ryugu's surface," JAXA said in a statement.

- Taking advantage of the asteroid's low gravity, the rovers will jump around on the surface — soaring as high as 15 m and staying in the air for as long as 15 minutes — to survey the asteroid's physical features. 24)

- "I am so proud that we have established a new method of space exploration for small celestial bodies," said JAXA project manager Yuichi Tsuda.

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Figure 23: Image captured by Rover-1A on September 21 at around 13:08 JST. This is a color image taken immediately after separation from the spacecraft. Hayabusa-2 is at the top and the surface of Ryugu is bottom. The image is blurred because the shot was taken while the rover was rotating (image credit: JAXA)

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Figure 24: Image captured by Rover-1B on September 21 at around 13:07 JST. This color image was taken immediately after separation from the spacecraft. The surface of Ryugu is in the lower right. The colored blur in the top left is due to the reflection of sunlight when the image was taken (image credit: JAXA)

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Figure 25: Image captured by Rover-1A on September 22 at around 11:44 JST. Color image captured while moving (during a hop) on the surface of Ryugu. The left-half of the image is the asteroid surface. The bright white region is due to sunlight (image credit: JAXA)

The MINERVA-II1 cameras can shoot in color. In Figure 23, although the image is blurred due to the rover rotating, you can clearly see the body of Hayabusa-2 and the paddle of the solar cells. The solar paddle appears blue. In Figure 25, the image was taken during a hop on the surface and you can feel this dynamic movement.

Operation of MINERVA-II1 will continue from now on. We are planning to acquire more data for analysis.

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Figure 26: MINERVA-II1 schematic showing the deployment operation sequence (image credit: JAXA)

Legend to Figure 26:

- dV, ΔV: acceleration of the spacecraft

- free fall: The speed of the spacecraft is not controlled, but falls due to the pull of Ryugu's gravity.

- GCP-NAV: Ground Control Point Navigation, tool for image guided navigation during the descent operation.

- HP: home position

- LIDAR: laser altimeter

- ONC-T: Optical Navigation Camera Telescopic (installed on the bottom of the spacecraft).

- ONC-W1: Optical Navigation Camera Wide angle (installed on the bottom of the spacecraft).

- ONC-W2: Optical Navigation Camera Wide angle (installed on the side of the spacecraft).

- Attitude scan: change the attitude of the probe to photograph MINERVA-II1

- constant descent velocity: the spacecraft descends at a nearly constant speed. At first, this speed is about 40 cm/s. From an altitude of about 5 km, the speed is about 10 cm/s.

- Trigger Altitude: when this altitude is reached, the spacecraft's speed will be controlled.

- Additional free fall for preventing plume contamination: the spacecraft will not use thrusters during the period shown in the figure when MINERVA-II1 is in free fall. This is to avoid thruster gas hitting MINERVA-II1.

 

• August 23, 2018: Landing sites of the Hayabusa-2 mission on the asteroid Ryugu determined: 25)

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Figure 27: The MASCOT lander is set to land on the blue-marked ellipse MA-9 on Ryugu. The Japanese Hayabusa-2 probe will approach the asteroid surface at location L07 (L08 and M04 are substitute landing sites), where it will take samples. The MINERVA rovers will be dropped off at the red-marked landing site N6 (image credit: JAXA, University of Tokyo & collaborators)

• July 25, 2018: Hayabusa-2 arrived at asteroid Ryugu on June 27, after which the spacecraft remained at a distance of about 20 km (the Home Position) to continue to observe the asteroid. During this time, the spacecraft was maintaining a hovering altitude of 20 km above the asteroid surface. — In the week of July 16, operations were begun to lower this orbiting altitude, eventually bringing the spacecraft to less than 6 km from the asteroid surface. One of the images taken at that time is shown in Figure 28. 26) 27)

- The resolution in Figure 28 is about 3.4 times higher than the images taken from the Home Position so far. One pixel in Figure 28 corresponds to about 60 cm. The largest crater on the surface of Ryugu is situated near the center of the image and you can see that it has a shape like a "mortar". You can also see that the surface of Ryugu is covered with a large number of boulders. This picture will provide important information as we choose the landing site.

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Figure 28: Asteroid Ryugu from an altitude of 6 km. The image was captured with ONC-T (Optical Navigation Camera - Telescopic) on July 20, 2018 at around 16:00 JST (image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, University of Aizu, AIST)

- The activity at this lowered altitude is called a "BOX-C operation". In the Hayabusa-2 Project, we define three regions for spacecraft operations above Ryugu; BOX-A, BOX-B and BOX-C. A diagram of these operation regions is shown in Figure 29.

- BOX-A corresponds to the Home Position, with an altitude of about 20 km. BOX-B is at same altitude as BOX-A, but the spacecraft can now move ±10 km forwards, backwards, left and right. BOX-C has the same dimensions at BOX-A front-to-back and left-to-right, but this region contains an altitude down to about 5 km from the asteroid surface. We define the coordinate system here as the Home Position coordinate system. To understand this system, take a look at Figure 30. The important point is that the Z-axis always points in the direction away from the asteroid towards the Earth.

- During the last week, the project operated the spacecraft within BOX-C, descending slowly towards the asteroid from July 17. Hayabusa-2 orbited at the lowest altitude for one day from July 20. After conducting observations of Ryugu during this time, Hayabusa-2 began to ascend on July 21 and returned to BOX-A on July 25.

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Figure 29: Definition of the operation BOX. XHP, YHP, ZHP are the coordinates of the Home Position. The YHP -axis is perpendicular to this page (or screen) and faces towards the reverse side of the page (image credit: JAXA)

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Figure 30: Definition of the Home Position coordinate system (image credit: JAXA)

• August 14, 2018: In early October 2018, the Mobile Asteroid Surface Scout (MASCOT) lander is expected to be in operation for approximately 16 hours on the Ryugu asteroid. The selection of the landing site will take place this August. The ideal site must firstly offer the MASCOT team engineers excellent conditions for a safe landing and stable operation on the asteroid, while providing the researchers with a wealth of new and productive measurements. The lander made its way to the asteroid on board the Japanese Hayabusa-2 space probe, carrying four instruments that will examine the celestial body directly on the surface. The German Aerospace Center (Deutsches Zentrum für Luft- und Raumfahrt, DLR) is contributing the MASCOT Camera (MasCam), which will acquire the first images during the descent to the asteroid and is intended to investigate the area around the landing site, in addition to the fine structure of the surface. DLR is also providing the MARA radiometer, which will measure the temperature on the asteroid's surface, among other things. The Technical University of Braunschweig will use the MasMag magnetometer to research the magnetization of the asteroid, while the French space agency CNES (Centre National d'Etudes Spatiales) will analyze the minerals and rocks on Ryugu using the MicrOmega spectrometer. Ralf Jaumann from the DLR Institute of Planetary Research is supervising the MasCam camera experiment and is the Principal Investigator of the MASCOT lander. In this interview, he explains what a suitable landing site may look like and what the scientists expect to find on the asteroid. 28)

• June 28, 2018: After a 42-month journey, Japan's Hayabusa-2 spacecraft arrived at asteroid 162173 Ryugu, 300 million km from Earth, on 27 June at 00:35 GMT. This remarkable achievement was confirmed when the spacecraft closed to just 20 km from the 1 km-diameter asteroid's surface, having entered a critical phase of this ambitious mission. 29)

- The confirmation of the Hayabusa-2 rendezvous, made at 9:35 a.m. (Japan Standard Time, JST), is based on the following data analyses: 30)

a) The thruster operation of Hayabusa-2 occurred nominally

b) The distance between Hayabusa-2 and Ryugu is approximately 20 kilometers

c) Hayabusa-2 is able to maintain a constant distance to asteroid Ryugu

d) The status of Hayabusa-2 is normal

- From this point, JAXA is planning to conduct exploratory activities in the vicinity of the asteroid, including scientific observation of asteroid Ryugu and surveying the asteroid for sample collection.

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Figure 31: Image of Ryugu, captured with ONC-T (Optical Navigation Camera – Telescopic) at 12:50 p.m. (JST), June 26, 2018 (image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, University of Aizu, AIST)

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Figure 32: The location of Hayabusa-2 thrusters: A set of 12 thrusters is loaded with the Hayabusa-2 spacecraft as circled in red. Propulsion at 2.9 cm/s in the plus z-axis proceeded for the rendezvous (image credit: JAXA, Ref. 30)

- Hayabusa-2 aims to study Ryugu in detail, deposit a European and a series of Japanese landers on the surface and return a sample of ancient rock to Earth in 2020.

- "Together with all of you, we have become the first eyewitnesses to see asteroid Ryugu. I feel this amazing honor as we proceed with the mission operations," said Yuichi Tsuda, project manager of JAXA (Japan Aerospace Exploration Agency).

- In 2014-17, during Hayabusa-2's cruise phase from Earth to the asteroid, ESA's deep-space ground station at Malargüe, Argentina - part of the Agency's worldwide Estrack network - provided crucial communication support to the mission.

- In July this year, Malargüe will resume support, providing one communication contact session per week together with ESA's Cebreros station in Spain. The Malargüe station will also support the ESA-JAXA BepiColombo mission, due for launch in the autumn (Ref. 29).

• June 15, 2018: Hayabusa-2, JAXA's asteroid explorer, and the MASCOT lander, developed by the German Aerospace Center (DLR) and the French space agency (CNES) have been travelling through space since December 2014. They are finally closing in on their destination asteroid – Ryugu. As of 14 June 2018, the distance between Hayabusa-2 and Ryugu is less than 770 km and the closing speed is 2.1 m/s. 31) 32)

- On 13 June 2018, the 'Optical Navigation Camera – Telescopic' (ONC-T) acquired an image of Ryugu, where the asteroid extends to 10 pixels. The short exposure time means that the background star field is invisible.

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Figure 33: Left: An image of Ryugu acquired by the ONC-T on board Hayabusa-2 at around 13:50 JST (06:50 CEST, 04:50 UTC) on 13 June 2018. The distance to the asteroid is approximately 920 km and the field of view is 6.3º x 6.3º; the exposure time was 0.09 seconds. Right: enlarged section of left-hand image [image credit: JAXA, Kyoto University, Japan Spaceguard Association, University of Seoul, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, University of Aizu, and AIST (National Institute of Advanced Industrial Science and Technology)]

- Earlier, the ONC-T also acquired an image with a much longer exposure time in which the background stars are visible.

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Figure 34: Image of Ryugu acquired by the ONC-T on board Hayabusa-2 on 13 June 2018 at 12:50 JST. The distance to the asteroid is about 920 km and the field of view is 6.3º x 6.3º; the exposure time was 178 seconds. Ryugu, which is visible against the constellation Gemini, is sufficiently bright that it has partially saturated the ONC-T sensor [image credit: JAXA, Kyoto University, Japan Spaceguard Association, University of Seoul, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, University of Aizu, and AIST (National Institute of Advanced Industrial Science and Technology)]

- Arrival at Ryugu is scheduled for June 27.

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Figure 35: Overview of the Hayabusa-2 mission schedule (image credit: JAXA)

• On February 26, 2018, Hayabusa-2 saw its destination —asteroid Ryugu— for the first time! The photographs were captured by the ONC-T (Optical Navigation Camera - Telescopic) imager onboard the spacecraft (Figure 36). Images were taken between noon JST on February 26th and 9:00am the following morning, with about 300 shots taken in total. Data for nine of these images were transmitted from the spacecraft on February 27th, allowing us to confirm that Ryugu had indeed been seen. The animation shows these nine consecutive frames. 33) 34)

- Ryugu's brightness from Hayabusa-2 is about magnitude 9, which would be impossible to see with the naked eye but visible with the ONC-T. Looking at the image above, you can see how the position of the surrounding stars relative to Ryugu appears to change as Hayabusa-2 moves towards the asteroid. The distance between Ryugu and Hayabusa-2 when the images were taken is about 1.3 million km. Ryugu as seen from Hayabusa-2 is in the direction of the constellation Pisces.

- Ryugu was photographed when the Sun, Hayabusa-2 and Ryugu were almost in a line. This configuration can be seen in Figure 37, which shows a snapshot of the header from the Hayabusa-2 website on February 26, 2018, which continuously updates to show the position of Hayabusa-2. If you were to stand on Ryugu, Hayabusa-2 would be seen in the direction of the Sun.

- Hayabusa-2 is currently using its ion engine to make adjustments to its course. This makes it difficult to alter the orientation of the spacecraft. However, at the alignment shown in Figure 37, the ONC-T camera can image Ryugu without needing to make significant changes to the spacecraft's orientation. This made February 26th the perfect time to try and capture Ryugu's image with the ONC-T. From the data, Ryugu was observed to be exactly at the expected location based on Hayabusa-2's estimated position. This tells us that Hayabusa-2 is flying on the planned course.

- "Now that we see Ryugu, the Hayabusa-2 project has shifted to the final preparation stage for arrival at the asteroid. There are no problems with the route towards Ryugu or the performance of the spacecraft, and we will be proceeding with maximum thrust," explains Project Manager, Yuichi Tsuda.

- The remaining images will be transmitted back to Earth from the spacecraft and allow us to further confirm the asteroid and spacecraft location. Although we can currently see Ryugu only as a point, it is very exciting for the whole project team to catch sight of the destination!

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Figure 36: Ryugu as imaged by Japan's Hayabusa-2 asteroid explorer mission (image credit: JAXA)

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Figure 37: The position of Hayabusa-2 on February 26, 2018, captured from the diagram at the top of the mission website.

• As of September 2017, two of three IES (Ion Engine System) sessions have been completed. The first and second IES session, 798 hours and 2558 hours of IES operation was executed, respectively. The total IES operation time is about 3,900 hours and a velocity increment of about 580 m/s has been obtained. 35)

- In December 2017, the last IES session will be started and will continue until June 2018. After the completion of the third IES operation, the Hayabusa-2 spacecraft will arrive in the vicinity of Ryugu. Since there are large uncertainties on the asteroid ephemeris, the Hayabusa-2 spacecraft will perform an optical navigation campaign to reduce the relative position error to the asteroid. The direction of the asteroid will be determined by the ONC-T (Optical Navigation Camera - Telescopic) imager; if required, a series of guidance maneuvers with the RCS will be used to correct the trajectory toward the asteroid. A month of an optical navigation campaign is scheduled for this final approach phase.

- Hayabusa-2 will arrive at the asteroid vicinity in the summer of 2018. Hayabusa-2 will explore Ryugu for 1.5 years and return to the Earth in the winter of 2020. The 1.5 year allocation for proximity phase operations is much larger than the 3 months of Hayabusa's proximity operation, however the schedule is marginal. Three touchdown operations need to be planned within the limited amount of time to satisfy the mission success criteria.

- There are three main uncertainty parameters, which impact the schedule. Those are: gravity, thermal environment, and spin axis orientation of Ryugu.

- Firstly, the Ryugu gravity limits the number of descent operations. This is because the limitation of the fuel onboard and the fuel consumption per descent operation. The smaller the gravity constant, the less fuel requirement - thus, more descent attempts can be done. Currently, the porject assumes the gravity coefficient between 11 to 92 m3/s2. The "worst case" for the scheduling is the largest number of the descent operations, derived by the smallest gravity. The maximum number of descent operations is considered as a slot in the nominal schedule.

- Secondly, the thermal environment of the asteroid impacts the schedule. This constraint is the solar distance constraint for the TD (Touch Down) operation. There are upper constraints in the solar distance because the spacecraft temperature becomes too high when the spacecraft approaches the asteroid surface and receives the thermal inputs both from the asteroid as well as from the Sun. The current best estimate of Ryugu's thermal environment derived resulted in a touch down epoch requirement between October 2018 and May 2019; this corresponds with a 1.25 AU sun distance. This constraint will be updated after the Ryugu in-situ observation of Hayabusa-2 in the Summer of 2018.

- The third uncertainty parameter is the spin axis orientation of the asteroid. Although there is series of light curve observation of Ryugu from ground based telescope, the spin axis orientation is still uncertain. The spin axis impacts the Hayabusa-2 visibility of the asteroid. Since the Hayabusa-2 spacecraft stays in the vicinity of the Earth-asteroid line, the limited visible latitude is given as a function of spin axis. Assuming that the asteroid is a single spinner, the visible latitude varies due to the asteroid orbital motion around the Sun. The orbital motion changes the geometry between the asteroid and the Earth, therefore the visible latitude changes. — The accessible region for the descent operation also depends on the spin axis orientation. Due to the GNC limitation, the descent operation need to be done within 200 m from the asteroid-Earth line. This restriction describes the accessible latitude band as a function of time. Figure 38 illustrates the schematic image of the change of the visible area and accessible latitude band. The relative position in HP (Home Position) frame will change due to the orbital motion around the Sun.

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Figure 38: Example of change of accessible latitude band (image credit: JAXA/ISAS)

- Figure 39 describes the latitude band and visibility of a sample spin axis orientation. The blue region is the touch down or MASCOT release point accessible latitude band. The gray zone during the end of 2018 is the conjunction phase and neither observation nor critical operation can be performed. In this example, the accessible latitude before and after the conjunction have a large difference. 36)

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Figure 39: Example of change of accessible latitude band during the proximity phase operations (image credit: DLR, CNES, JAXA/ISAS)

- Considering all three points, the nominal schedule is conducted as shown in Figure 40. The TD1 is allocated just before the conjunction (with margin). All the previous operations are derived by the TD1 operation. Especially, the landing site selection is the most important input for the operation.

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Figure 40: Outline of the nominal proximity phase schedule at Ryugu (image credit: JAXA/ISAS)

Legend to Figure 40: LSS =Landing Site Selection, SCI =Small Carry-on Impactor.

• As of September 2016, 1346 hours of the ion engine operation have been achieved as planned. Three touch downs/sample collections, one kinetic impact/crater generation, four surface rovers deployment and many other in-situ observations are planned in the asteroid proximity phase. The operation team will perform extensive operation practice/rehearsal using a hardware-in-the-loop simulator in the year 2017 to be ready for the asteroid arrival in the summer 2018. 37)

Period

IES run time

Thrusters used

ΔV

Comment

March 3-21, 2015

409 hr

A+D

44 m/s

Trajectory control

May 12-13, 2015

24 hr

A+C+D

4 m/s

3-thruster operation test

June 2-6, 2015

102 hr

A+D

11 m/s

Trajectory control

September 1-2, 2015

12 hr

A+D

1.3 m/s

TCM for EGA targeting

EGA (Earth Gravity Assist)

March 22-May 5, 2016

795 hr

A+C+D

127 m/s

Trajectory control

May 20-21, 2016

3 hr

A+D

0.3 m/s

Trajectory control

Table 5: Ion Engine System (IES) operation history in forward cruise phase (as of September 2016)

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Figure 41: Trajectory design from EGA to Ryugu arrival (J2000EQ heliocentric inertial frame), image credit: JAXA

- Hayabusa-2 adopts a novel attitude control technique called "Solar Sail Mode" for reliable and fuel-efficient attitude operation. 38) It is used in ballistic cruise periods and realizes a coarse Sun pointing attitude using one RW only and actively utilizing SRP (Solar Radiation Pressure). The last 1 month of the commissioning phase from January 24 until March 2 was dedicated to the SRP torque characterization and Solar Sail Mode attitude control testing/demonstration, which was completed successfully.

- Forward Cruise Operation: Hayabusa-2 started the forward cruise phase (cruise from Earth to Ryugu) on March 3, 2015, following the completion of the commissioning phase. Total of approximately 7000 hours IES operation is planned to reach Ryugu. Table 5 shows the history of the IES operation from launch until present. Figure 41 shows the trajectory from EGA to Ryugu arrival with the IES thrust vector history.

- Ballistic flight phase (cruise without IES operation) is effectively utilized for precise navigation, regular onboard instruments checkout/calibrations, and engineering demonstration/testing. For example, Mars observation campaign was conducted from May 28-June 9, 2016 at the closest distance (41 million km) for ONC/TIR/NIRS3 calibration purpose. The Ka-band operation between Hayabusa-2 and an ESA's deep space station (ESTRACK Malargue station in Argentina) was conducted successfully on July 5-8, 2016. The Ka-band DDOR was tested several times using NASA(DSN) and ESA(ESTRACK) stations and achieved the world-first successful inter-agencies operation of the Ka-band DDOR under the CCSDS (Consultative Committee for Space Data Systems) DDOR operation standard. Besides testing, X-band DDOR is regularly used for precise orbit determination in ballistic cruise periods.

- EGA (Earth Gravity Assist) operation: Hayabusa-2 performed the EGA on December 3, 2015. Four TCMs (Trajectory Correction Maneuvers) were planned and three were actually conducted. The final TCM was canceled because the spacecraft had already been guided accurately with the three TCMs. Table 5 shows the list of TCMs for the gravity assist with the guidance accuracy results.

- The Earth closest approach occurred at 10:08:07 UT, December 3, 2015 over the Pacific Ocean (Figure 42). The closest distance was 3090 km (from the Earth surface) and the flyby deflection angle (angle between incoming and outgoing velocity vector in ECI frame) is 83º. The interplanetary velocity increment by this EGA is 1.6 km/s. The spacecraft experienced an eclipse for 20 minutes, which is the longest battery-powered operation for Hayabusa-2 throughout its mission.

- The operation team is now preparing for operation practice/rehearsals using the hardware-in-the-loop simulator in the year 2017 to be ready for the asteroid arrival in the summer 2018.

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Figure 42: Closest Earth flyby of Hayabusa-2 on December 3, 2015 (image credit: JAXA)

• July 14, 2016: MASCOT (Mobile Asteroid Surface Scout) of DLR has been travelling on board the Japanese Hayabusa-2 spacecraft for the last 1.5 years, and is currently at approximately 65 million km from Earth. On 14 July 2016, DLR (German Aerospace Center) engineers in the LCC (Lander Control Center) in Cologne switched the shoebox-sized lander and its four German and French-built instruments back on, and will spend the next few days finding answers to two questions: How is MASCOT's state of health? And how are the experiments on board? "We do a check-up once a year to find out whether all system components and instruments are still in good working order," explains Christian Krause from the Lander Control Center team at DLR. 39)

- The Hayabusa-2 spacecraft by JAXA (Japan Aerospace Exploration Agency) set off on its mission on 3 December 2014, carrying the French-German MASCOT lander. One year later, the duo zipped round the Earth to gain momentum and sent back photos from our planet before continuing on toward the asteroid Ryugu. The spacecraft will venture deeper into space until the summer of 2018, when it will enter orbit around the celestial body that DLR planetary researcher Ralf Jaumann refers to as a 'beautifully primitive object'. "During this mission, we will be investigating primordial material from the solar nebula; it has remained practically unchanged in its 4.5 billion years of existence." Then, while the Hayabusa-2 spacecraft measures and analyses the asteroid from its position in orbit, MASCOT will descend to its surface to conduct scientific measurements. The Japanese spacecraft will also take on soil samples that it will bring back to Earth in 2020. "This is a complete package. There has never been anything like this before: we will be observing and mapping remotely, measuring the asteroid, analyzing its surface and bringing the samples back to Earth." But this complete package requires the concerted efforts of engineers and scientists from Germany, France and Japan who have joined forces in an international cooperation.

• December 25, 2015: Before and after the Earth swing-by, the laser altimeter (LIDAR) on Hayabusa-2 attempted to receive laser light from the SLR (Satellite Laser Ranging) ground stations. 40)

- After the swing-by, the Mt. Stromlo station at SERC (Space Environment Research Center Australia) in the suburbs of Canberra, Australia, transmitted laser light towards Hayabusa-2. The spacecraft successfully received the beam using the onboard LIDAR that can send and receive laser signals to accurately establish the range of objects from the spacecraft. At the time of the transmission from Mt. Stomlo, Hayabusa-2 was 6,700,000 km from Earth. This success established the one-way 'up link' of the optical connection.

• December 14, 2015: JAXA confirmed that the Asteroid Explorer "Hayabusa-2" is cruising on its target orbit after measuring and calculating the post-Earth-swing-by orbit. With the swing-by results, the explorer's orbit turned by about 80 degrees and its speed increased by about 1.6 km/s to about 31.9 km/s (against the sun), thus the orbit achieved the required target velocity (Figure 43). According to the operational support provided by the NASA DSN (Deep Space Network) stations and the ESA (European Space Agency) deep space ground station Malargüe in Australia, the Hayabusa-2 is in good health. 41) 42)

- At 9:00 UTC on Dec. 14, 2015, the Hayabusa-2 is at a distance of ~4.15 million km from Earth, and about 144.85 million km from the sun. Its cruising speed is 32.31 km/s (against the sun). Hayabusa-2 is increasing its speed under the influence of the sun's gravity after the swing-by.

- After the swing-by, Hayabusa-2 took images of the Earth using its onboard ONC-T (Optical Navigation Camera - Telescopic). The ONC-T can shoot color images using seven filters. The image of Figure 44 is composed by using three of these filters. One can see the Australian continent and Antarctica in the image. The South Pole is not lit by the sun during the(northern hemisphere) summer, and the meteorological satellites also do not cover the Antarctic continent to take their imagery, hence the shot this time is precious.

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Figure 43: Conceptual diagram of the Hayabusa-2 orbit (image credit: JAXA)

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Figure 44: Shot at 22:09 (UTC) on Dec. 4, 2015, about 340,000 km from the center of the Earth One can see the Australian continent on the upper right, and Antarctica on the lower right (image credit: JAXA)

• December 3, 2015: JAXA performed an Earth swing-by operation of the Asteroid Explorer "Hayabusa-2 " in the evening of December 3 (Thursday), 2015 JST (Japan Standard Time). The Hayabusa-2 flew closest to the Earth at 10:08 (UTC) and passed over Hawaii at an altitude of about 3,090 km. - The Hayabusa-2 project team is currently measuring and calculating the post-swing-by orbit. It will take about a week to confirm if the explorer entered the target orbit. We will report the result once it is determined. The Hayabusa-2 is in good health. 43)

- ESA's deep-space Malargüe ground station in Australia lent a helping ear as Japan's Hayabusa-2 asteroid mission visited Earth on Thursday. 44)

• October 5, 2015: The asteroid 1999 JU3, a target of the Asteroid Explorer "Hayabusa-2," was named "Ryugu". 45)

- JAXA conducted a naming proposal campaign between July 22 and August 31, 2015.

- Selection reasons: In the Japanese ancient story "Urashima Taro", the main character, Taro Urashima, brought back a casket from the Dragon's palace, or the "Ryugu" Castle, at the bottom of ocean. The Hayabusa-2 will also bring back a capsule with samples, thus the theme of "bringing back a treasure" is common.

- Rocks containing water are expected to exist on asteroid 1999 JU3. The name "Ryugu" also reminds us of water, as "Ryugu Castle" is under the ocean. The name is not similar or identical with any other already existing names of planets or asteroids, and there were many entries for this name among suggested names that are related to mythology.

- According to the naming rule stipulated by the International Asteroid Union (IAU), the name "is preferably from mythology" and the "Ryugu" fits that rule. Also, there is little concern of infringing the Trademark Law or any other third party trademarks.

• June 8, 2015: The Hayabusa-2 spacecraft has been continuously operating its ion engine for the second time since June 2, and successfully completed its operations at 0:25 a.m. on June 7 (Japan Standard Time.) The second continuous operation lasted for 102 hours as scheduled. 46)

- The ion engine boost was needed in preparation for the Earth swing-by planned in December 2015, and the total hours of the first and second operations (409 hours and 102 hours respectively) reached 511 hours.

• April 29, 2015: ESA is set to support Japan's ‘touch-and-go' Hayabusa-2 spacecraft, now en route to a little-known asteroid, helping to boost the scientific return from this audacious mission. A flawless launch last December marked the start of a six-year round-trip for Japan's Hayabusa-2, which is on course to arrive at the carbon-rich asteroid 1999 JU3 in June 2018. 47)

- In the first such support provided to a Japanese deep-space mission, ESA's 35 m diameter dish at Malargüe, Argentina, will provide up to 400 hours of tracking, establishing radio contact as the asteroid arcs through the Solar System between 135 million to 210 million km from the Sun. Telecommands from mission controllers at JAXA (Japan Aerospace and Exploration Agency) will be fed to the station via ESA/ESOC in Darmstadt, Germany.

- ESA is using its ESTRACK network with deep space stations at Malargüe (Argentina), Cebreros (Spain) and New Norcia (Australia). On 22 April, ESA completed a live, inflight compatibility test, linking the Malargüe station with the Japanese spacecraft, demonstrating the network's readiness to provide tracking for the Hayabusa-2 mission.

• April 10, 2015: Hayabusa-2 is stably flying in space. The new fiscal year has just started in Japan, and JAXA is taking a new step as we became a 'National Research and Development Agency' from the previous independent administrative agency. The Hayabusa-2 project is also taking a fresh step with a new team, including handing the baton over to a new project manager, namely from Hitoshi Kuninaka to Yuichi Tsuda. All members of the project are engaged in the mission with a fresh mindset. 48)

• March 18, 2015: LIDAR (LIght Detection And Ranging) is one of the satellite buses onboard Hayabusa-2. Basically LIDAR is used to measure the distance between the satellite and the target asteroid, 1999JU3. The distance is important information to control the satellite in descending operation such as close-up observation from low altitude and separation of rover, lander, and small carry on impactor. Especially an accurate measurement of the distance is required during touch-down and sampling operations. Thus, the LIDAR onboard Hayabusa-2 is required to measure about 4 orders of magnitude variety of distance, from 30m to 25km. To satisfy this requirement, the LIDAR has two types of receiver optics, one is for near range (nearer than 1km) and another is for far range (farther than 1km). 49) 50)

- The distance from the target asteroid, 1999JU3, is one of the fundamental information for operational and scientific observations. For example, the gravitational acceleration is calculated from the change rate of the distance from the target asteroid during free fall operation. Construction of a shape model requires a characteristic length scale in camera image. And also, the measurement of the absolute reflectance from camera image and/or spectrometer data requires an absolute distance from the target.

- The dust count mode is one of the operational modes of the LIDAR in which the LIDAR detects faint scattered light from dust grains on the line of sight. The distribution of dust grains along the line of sight is estimated from the profile of received light and the effective reflectance of dust cloud. Its function was tested both electrically and optically, and it seemed working properly.

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Figure 45: Schematic view of dust count mode. Thick curve in the bottom figure represents hypothetical profile of received light. Black-and-white line at the bottom represent an output of dust count mode observation (white=0, black=1), image credit: Hayabusa-2 team

• March 5, 2015: Hayabusa-2, launched on Dec. 3, 2014, completed its initial functional confirmation period of about three months. The explorer was moving to the cruising phase on March 3 while heading to the asteroid 1999 JU3. 51)

- The Hayabusa-2 is in good health. It will be under preparatory operation including speed increase by continuous operation of the ion engines for an Earth swing-by scheduled in Nov. or Dec., 2015.

- The project plans to increase the cruising speed of the explorer (60 m/s) by operating two ion engines twice (in total about 600 hours or 25 days) until the Earth swing-by. For the first operation, the project will gradually increase the time duration of continuous ion-engine operation from March 3 onwards, and will operate the engines for about 400 hours within March. The second operation is scheduled in early June.

• Feb. 3, 2015: Hayabusa-2 is now undergoing the initial functional confirmation. Basic operations and performance of onboard instruments and ground systems have been tested one by one as of the end of January. Some examples: 52) 53)

- Ion engine test operation (one unit at a time). Four ion engines were being operated one by one. A thrust of 7-10 mN was generated on the orbit for the first time.

- Establishing communication by Ka-band communication equipment (between Jan. 5 to 10, 2015). Communication was successful between the Hayabusa-2 and NASA DSN stations to establish deep-space Ka-band communication for the first time for a Japanese space explorer. Ka-band communication will be used to send observation data during the mission for the Hayabusa-2 to stay near the asteroid.

- Ion engine can autonomously operate for 24 hours. Long duration of autonomous operation with two or three ion engines was tested, and 24-hour continuous operation was attained. The maximum thrust was confirmed to be about 28 mN, which is the expected value.

• Dec. 5, 2014: JAXA) confirmed the completion of a sequence of the important operations for the Asteroid Exploration Hayabusa-2 mission including the deployment of the horn part of the sampler that captures samples from the asteroid's surface, the release of the locks for the launch that ratchet the gimbal that controls the direction of the ion engine, and functional verification of the three-axis stabilization controls and the ground precision orbit determination system. With this confirmation, the critical operation phase of the Hayabusa-2 was completed. 54)

• JAXA received the first signals of Hayabusa-2 on December 3, 2014 at 6.44 UTC on Dec. 3, 2014, acquired by the NASA DSN (Deep Space Network) at Goldstone in California; it was confirmed that its initial sequence of operations including the solar array paddle deployment and sun acquisition control have been performed normally. - The explorer is now in a stable condition. 55)

 


 

Sensor complement: (SMP, SCI, NIRS3, TIR, MINERVA-II-1A/1B/2, DCAM3, ONC-T, MASCOT, SRC)

SMP (Sampler Horn):

The SMP, also referred to as "sampler mechanism", will collect samples from the surface of the asteroid. The basic design is the same of that aboard the Hayabusa mission; thus, the same mechanism will be used, which is a small projectile to be shot as soon as the tip of a cylinder-shaped horn touches the asteroid surface, then materials ejected from the surface will be collected in a catcher (storage).

Major improvements from the Hayabusa:

• The seal performance has been improved for Hayabusa-2, and a newly developed metal seal method is applied, so that volatile gas such as rare gas can be brought back thanks to high airtightness.

• The number of compartments for the catcher that will store captured materials is increased by one to three compartments compared to two for the Hayabusa.

• For the Hayabusa-2, the edge of the sampler horn was folded back inward as you can see in the left figure so that sand gravel can be hung on the cuff (gravel of 1 to 5 mm can be captured.) If the explorer makes an emergency stop during its ascending, gravel will keep going up to be stored in the catcher. This mechanism is a backup for sample retaining. 56)

Hayabusa2_Auto1C

Figure 46: Photo of the SMP assembly (image credit: JAXA)

 

SCI (Small Carry-on Impactor):

SCI is a new payload, an impactor caller "Liner", which is featured on Hayabusa-2. It consists of a small box, about 30 cm in size, which will be released a few hundred meters above the surface of the asteroid. The 2 kg copper liner will be shot at high speed (2 km/s) into the surface of the asteroid to create a small artificial crater by collision. The size of the crater may be about 2 or 3 m in diameter. The purpose of this impact experiment is not only to study the physical characteristics of the asteroid surface, but also to reveal the subsurface material, of which Hayabusa-2 will try to recover samples. It is expected that the fresh crater samples are less weathered by the space environment or heat. — The impactor (Liner) is made of pure copper to be able to easily identify the sample from other materials on the asteroid.

Hayabusa2_Auto1B

Figure 47: SCI pyrotechnics: Left: A conical shape structure filled with explosives. The "Liner" will be ejected forward at a high speed by explosive power. Right: The flying "Liner" at 2 km/s (image credit: JAXA)

 

NIRS3 (Near InfraRed Spectrometer, and 3 comes from "3µm") and TIR (Thermal Infrared Imager)

The Hayabusa-2 will be orbiting asteroid 1999JU3 at an altitude of ~20 km, and observe the asteroid by remote sensing. Two kinds of infrared observations will play an important role in this remote sensing.

• One is the near infrared spectrometer "NIRS3" to investigate mineral and water metamorphism or reciprocal chemical action of minerals and water by spectroscopic observations with near infrared rays.

• The other is the TIR (Thermal Infrared Imager) to study the temperature and thermal inertia of the asteroid, by capturing images of thermal radiation from the asteroid. In other words, it will find particles of the soil and the porosity of the mass of rock that influence the temperature.

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Figure 48: Photo of the NIRS3 (left) and of the TIR (right) instruments (image credit: JAXA)

 

MINERVA-II (Rover payload)

There are three small MINERVA-II rovers in total. They are of the heritage of MINERVA of Hayabusa, and they move on the surface of the asteroid by hopping. Hayabusa had only one MINERVA rover which failed to land it on the surface of Itokawa. Hayabusa-2 has two kinds of rovers, MINERVA-II-1 which separates into two (A and B), and MINERVA-II-2, so there are three small rovers in total. The rovers have small sensors (cameras, thermometers) onboard to convey their information to the orbiting Hayabusa-2 spacecraft.

Hayabusa2_Auto19

Figure 49: Schematic view of the MINERVA-II rovers (image credit: JAXA)

All the rovers have hopping mobile systems to explore over the surface after the deployment from the mother spacecraft at the vicinity of the target asteroid. 57)

Size

17 cm diameter; 7 cm in height

Mass

1.15 kg (Rover-1A); 1.129 kg (Rover-1B)

OBC (On-Board Computer)

SH2

Actuator

DC motor x 1

Mobile system

Hopping

Power supply

Solar cells generating 2 W @1.4 AU from Sun; Capacitors:100 F, 2.5 V x 3

Communication

32 kbit/s (max) telemetry link

Sensors for navigation

Photo diodes, thermometers, gyro, accelerometer

Sensors for observation

Camera x 4 (Rover-1A); Cameras x 3 (Rover-1B), thermometers, potentiometers

Table 6: Specification of the twin rovers (Rover-1A and Rover-1B)

 

DCAM3 (Deployable Camera)

DCAM3 is a miniaturized optical camera with the objective to observe the artificial impact of SCI ( Small Carry-on Impactor) on the asteroid. DCAM3 takes images of the spreading ejecta motion on the asteroid, which provides information of surface physical properties and ejecta behavior under microgravity. 58)

Collisions between primitive planetary bodies are one of the most important physical processes in the planetary accretion from planetesimals to planets. DCAM3 is a detachable camera inherited from DCAM-1,2 of the Japanese IKAROS mission. A separable instrument is necessary to obtain close up views of the impact, because the mother ship (Hayabusa-2) will be hiding in a safe region far from the impact point to avoid a risk that the mother ship encounters high-speed ejecta from the asteroid during the impact operation.

The impact observation part in the DCAM3 system consist of a separable small camera cylinder, its detachment instrument, and receiving antennas on the mother ship (Figure 50). After separation in the SCI impact operation, DCAM3 starts its observation at visible wavelength and sends image data on one-way communication to the mother ship. The design of DCAM3 is similar to IKAROS DCAM1,2 (Figure 51), but has an additional high-resolution camera in the body.

The DCAM3 instrumentation is provided by a Japanese University Consortium in cooperation with JAXA. The University Consortium consists of: University of Tokyo, Kashiwa; Kobe University, Kobe; JAXA (Japan Aerospace Exploration Agency), Sagamihara; Planetary Exploration Research Center, Chiba Institute of Technology, Narashino; Kochi University, Kochi; The Graduate University for Advanced Studies, Sagamihara; and the University of Occupational and Environmental Health, Kitakyusyu.

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Figure 50: Components of DCAM3 system on the Hayabusa-2 mother ship (image credit: University Consortium, JAXA)

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Figure 51: A photo of the IKAROS DCAM-1,2, the body diameter is about 60 mm (image credit: University Consortium, JAXA)

The scientific observations are performed by DCAM3-D, a wide-angle high-resolution camera and its fast digital transmission component in the DCAM3 body. The scientific objectives of this camera are summarized as (1) clarifying the subsurface structure, and (2) constructing the impact scaling rule applicable to the surface of asteroid 1999JU3. The observation objects of the camera are ejecta and a subsequent crater of the SCI impact, and a relative position of the SCI to the asteroid when it is launched. DCAM3-D can determine the size and the angle of the ejecta curtain, and the speed of the ejecta spreading or fragment spattering, which are the key information for the above objectives. In addition, low-speed ejecta (dust) spreading will possibly be observed around the DCAM3 in a few hours after the impact.

The DCAM3-D CMOS detector produces 2000 x 2000 pixels 8 bit monochromatic images with a 74º x 74º wide-angle optics. It takes 1 frame/s sequential images at maximum. Figure 52 shows a virtual image of spreading ejecta on asteroid 1999JU3 taken by the DCAM3-D in an ideal position. The optical camera has enough-high space resolution and bright resolution for its sciences. DCAM3 continues to produce data for a few hours until the batteries run out or the DCAM3 falls and crashes on the asteroid. The digital communication device can send the image data to the mother ship with 4 Mbit/s at maximum. Instruments in the mother ship store all data taken by the deployed camera. The total volume of image data is estimated to be approximately 5 Gbit after compression.

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Figure 52: A virtual image of asteroid 1999JU3 and ejecta cone taken by the DCAM3-D camera. The blue oval sphere shows a potential region in which SCI exists. The green cone shows a possible trajectory of the projectile (image credit: University Consortium, JAXA)

 

ONC-T (Optical Navigation Camera-Telescopic) imager

The ONC-T was developed under collaboration between JAXA, the University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, The University of Aizu, the National Institute of Advanced Industrial Science and Technology (AIST).

The ONC system onboard the Hayabusa-2 spacecraft consists of one telescopic camera (T) and two wide-angle cameras (W1 and W2). ONC-T is a telescopic camera with seven band-pass filters in the visible and near-infrared range. These filters are placed on a wheel, which rotates to put a selected filter for different observations, enabling multiband imaging. 59)

The main objective of this instrument is to optically navigate the spacecraft to asteroid Ryugu (1999 JU3) and to conduct multi-band mapping the asteroid for choosing touchdown candidate sites and understanding the nature of this asteroid.

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Figure 53: Photo of the ONC-T imager (image credit: JAXA)

 


 

MASCOT (Mobile Asteroid surface SCOut)

MASCOT is a small lander provided by DLR (German Aerospace Center) in collaboration with CNES (French Space Agency). Building upon the successful joint development of the Philae lander of the Rosetta mission, DLR and CNES have studied this lander since 2008, and its realization was formally decided in early 2012. 60) 61) 62) 63)

After Hayabusa 2's arrival to its target – asteroid 1999JU3 - in 2018, MASCOT will be dropped to the surface where it will perform in-situ investigations for about 15 hours. A hopping mechanism of MASCOT will enable measurements at several locations. The payload of MASCOT consists of four scientific instruments, a wide angle camera, an imaging IR spectrometer (MicrOmega), a radiometer (MARA) and a magnetometer. MASCOT will significantly enhance the overall scientific return of the Hayabusa-2 mission by providing context measurements to support the interpretation of analyses of the returned samples. 64)

 

MASCOT spacecraft:

The general concept of MASCOT is to provide a small landing system intended to be deployed from a main spacecraft (or "mother-ship") on an asteroid sample return mission. MASCOT has been specifically designed to be compatible with JAXA Hayabusa-2 spacecraft and the environment given by the target asteroid 162173 Ryugu to fulfill the following scientific objectives: 65)

- In-situ observations of undisturbed materials and microscopic scale observations, not possible from the main spacecraft, to determine the asteroid regolith structure, texture and composition

- Magnetic properties measured during the descent, during the hopping maneuvers and on the surface on more than one site

- Temperatures of one asteroid rotation and thermal properties on more than one site

- Help the selection of the sampling spot(s) by the main spacecraft.

MASCOT is a 11 kg lander with a 3 kg payload, of 0.3 x 0.3 x 0.2 m3 volume and a single energy source (of 220 Wh) allowing about a 12 hours of mission duration. The design for MASCOT is based on the following subsystems:

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Figure 54: Photo of the MASCOT flight model (image credit: DLR, Telespazio VEGA)

Structure & Accommodation: The lander baseline design features a highly integrated carbon-fiber composite structure with a middle wall as main load bearing element. A common electronics box, called E-box, houses all the electronics. The lander is connected with the main spacecraft Hayabusa-2 via MESS (Mechanical and Electronics Support Structure), which comprises the PRM (Preload Release Mechanism) and the separation device. An umbilical connector supplies the power during the cruise phase.

Thermal Control: The thermal control concept is based mainly on passive means such as MLI (Multi-Layer Insulation) and color coatings. Thus, it relies also on a day-night-cycle on the asteroid's surface to balance the heat-load build-up. This constraint drives the selection of the operating asteroid site for MASCOT. An exception to the passive concept are the heaters used for the thermal control of batteries and MicrOmega during the cruise and commissioning phase. The heater is controlled by Hayabusa-2.

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Figure 55: Overview of MASCOT elements (image credit: DLR, Telespazio VEGA)

• Power: The power and energy supply is maintained by a primary battery, provided by the SAFT company (France), based on an earlier development for Philae. The unregulated bus voltage is converted into auxiliary voltages for MASCOT electronics by an internal PCDU (Power Control and Distribution Unit) located in the E-box. During the cruise and commissioning phase, the power will be supplied by the Hayabusa-2 spacecraft via a regulated power line. The power subsystem is a French contribution to MASCOT.

- During the cruise phase, the power is supplied by the Hayabusa-2 spacecraft via a dedicated power line, through the MESS connector. After separation, the power is supplied by a primary battery. Its capacity is dimensioned for an operating time of two asteroid days, ~16 hours nominal. Both the Hayabusa-2 power and the battery power line is converted into auxiliary voltages for MASCOT electronics by an internal PCDU (Power Control and Distribution Unit), located in the common E-box. The PCDU is made of two similar units forming a redundant architecture, with redundant power converters for the secondary voltages to redundant and non-redundant equipment. The data link with the OBC is via two UART RS422 lines for each PCDU unit.

• GNC (Guidance and Navigation) sensors: The GNC sensors are used to determine the MASCOT motion state and orientation on the asteroid's surface. They are distributed all over the MASCOT body and are acquired via the hot redundant A/D converter of the OBC. The algorithms to determine the motion status, the illumination status and the MASCOT side in contact with the soil (side2soil) are implemented in the MASCOT OBSW. The navigation sensors consist of:

- OPS (Optical Position Sensors): 5 optical distance sensors are mounted on the outer skin of MASCOT on each side, except -Z, the nominal side at surface contact. The optical position sensors use an IR LED and a photodiode. The IR LED is switched on/off by the OBC to perform a differential measurement and detect the presence of a surface. With these sensors it is also possible to detect if MASCOT is moving or is lying still, the side on which MASCOT is lying and the distance to the soil.

- PECs (Photo-Electric Cells): These sensors are used for redundancy to the OPS. One PEC is mounted on each side of MASCOT. There are a total of 6 sensors. The output of the PEC is a voltage proportional to the cosine of angle between the sun vector and the cells normal vector.

- Separation sensor: Break-wire contacts on the power connector from Hayabusa-2, integrated in the MESS, will detect the separation.

• OBC (On-Board Computer): The MASCOT OBC is a dual redundant computer composed by 2 CPU boards (CPU-M, CPU-R) to execute the OBSW (On-Board Software) and 2 I/O boards (IOM-M, IOM-R) to provide interfaces with all MASCOT subsystems. The 4 PCBs are accommodated in the common E-box. The two CPU boards work in cold redundancy, while the I/O boards work in warm redundancy, cross-strapped with the CPU boards via SpaceWire links. Each I/O board uses a radiation tolerant FPGA to implement:

- the I/O controllers for the external UART serial interfaces

- the I/O controllers to handle the analog section and bi-level I/O interfaces

- a NAND Flash controller featuring a page level Reed - Solomon encoder / decoder

- the CPU switch-over logic driving the reconfiguration of the CPU from main to redundant or vice versa

- a local timer to centrally maintain the MOBT (MASCOT On-Board Time) independent from the CPU

- a small RAM area, EDAC protected, used as Safe Guard Memory (SGM) to propagate the OBSW context in case of CPU reset or switch-over.

These devices are accessible by the two CPU board via SpaceWire interface. The I/O board also contains the NAND Flash mass memory device, the analog section circuits, the RS422 transceivers, the SpaceWire LVDS transceivers and other interface drivers/receivers needed for the external interfaces. The CPU board uses an Aeroflex GR712RC SOC (System On a Chip) clocked at 40 MHz, embedding a dual LEON3FT CPU core and a few other cores, like SpaceWire controllers, timers, DSU (Debug Support Unit) etc. The board also accommodates the program and data RAM (implemented as a SRAM multi chip module), a reprogrammable non-volatile memory PROM (implemented as a MRAM device), the Watch Dog and Reset circuits and the SpaceWire LVDS and other transceivers needed for the external interfaces. The SOC DSU JTAG interface is routed to the E-box test connector through dedicated transceivers. The SpaceWire serial interfaces to the MicrOmega and CAM instruments are implemented by the CPU board.

In terms of processing and memory resources, each OBC section (1 CPU + 1 IOM) provides:

- CPU speed: minimum 40 DMIPS, 10 MFLOPS

- RAM (SRAM): 16 MByte EDAC protected

- PROM (MRAM): 256 kByte / 204 kByte with EDAC enabled

- NAND Flash: 1 GByte / 860 MByte with Reed-Solomon encoding.

• RF communications: The communication architecture is based on a redundant CCOM (Child -COM) transceiver provided by JAXA; it is identical with the communications subsystem of the MINERVA small landers. The data link is based on CCSDS TM/TC packets and the transmission protocol between the MASCOT CCOM and the Hayabusa-2 PCOM (Parent-COM) ensures one-to-one delivery of the CCSDS packets by automatic retransmission requests in both directions in case of errors. MASCOT is equipped with two CCOM units working in cold redundancy. Each CCOM unit has two RF ports connected to two patch antennas via an RF coupler. One antenna located on top (+Z) and the other on the bottom (-Z) of MASCOT ensure almost omnidirectional coverage.

The maximum bit rate possible is ~37.04 kbit/s for telemetry packet downlink; ~1.7 kbit/s for telecommand packet uplink. An UART RS422 TM/TC umbilical interface is foreseen through the E-box test connector, to be used as alternative to the CCOM RF channel only during ground AIV activities. After the Hayabusa-2 launch, only the CCOM RF channel is used for TM/TC with MASCOT, via the Hayabusa-2 data handling unit (DHU) and the lander's computer,OME (On-board Minerva Equipment).

MASCOT antenna: For cruise phase operations, a dedicated MESS antenna is required whereas for on asteroid operations, the OME-A Hayabusa antenna is used. Two omnidirectional antennas are positioned on the top and bottom sides of MASCOT (Figure 56). The communication subsystem (CCOM transceiver excepted) is a French contribution to MASCOT.

Inside MASCOT a redundant set of JAXA-provided Child-Communication-transceivers (CCOM) is used to communicate with its counterpart - the Parent-Communication transceiver (PCOM) - on board of Hayabusa-2 based on a half-duplex communication and time division multiple access (TDMA) methods. The whole inter-spacecraft communication chain is shown in Figure 58.

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Figure 56: Upper and and lower faces of the FM antenna (image credit: CNES)

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Figure 57: MASCOT communication subsystems overview (image credit: DLR, Telespazio VEGA)

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Figure 58: RF communication chain between MASCOT and Hayabusa-2 (image credit: Hayabusa-2 consortium)

MASCOT Mobility Mechanism: It fulfils two functions, namely up-righting MASCOT into the correct attitude after landing, and providing a hopping capability to relocate MASCOT onto a different site. The motion is generated by driving an off-centered mass to provide the adequate momentum. The mass is driven by an electric motor, which is controlled by a dedicated, dual, cold-redundant electronic unit called MMC (Mobility Mechanism Controller). Each MMC branch is connected to the OBC via a UART RS422 line.

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Figure 59: Sketch of separation & surface operation concept (image credit: DLR)

The OPS (Optical Position Sensors), designed and manufactured by Cosine Research B.V., Leiden, The Netherlands, is a small sensor (32:6 mm x 27 mm x 21:6 mm) with a mass of about 28 g. It consists of an infrared LED and an appropriate photodiode (Figure 60). The light omitted by the LED is reflected by any object in the FOV (Field of View) of the sensor. Nearer objects reflect more light and light from objects further away than 12 cm can not detected any more. This gives the opportunity to detect objects in proximity in a certain direction. In addition the LED is on/off modulated by the OBC and the signal from the photodiode is correlated with this modulation. With this method one can distinguish between reflected light from the LED and background illumination e.g. from sunlight. Figure 61 shows the output voltage of the OPS as function of the distance from the object.

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Figure 60: Photo of the OPS (image credit: Cosine Research B.V)

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Figure 61: OPS output voltage as function of distance (image credit: Cosine Research B.V.)

Five of these OPS systems are used on MASCOT, mounted on 5 different sides of the cuboid. Only the instrument side is not equipped with such a sensor. This space is needed for the scientific instruments. As one can see in Figure 61, the output voltage decreases again for distances smaller than 10 mm. To prevent such small distances, the sensors are not mounted flat to the surface but shifted inside the body of MASCOT.

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Figure 62: Photo of the Mascot EQM, mounted on the Hayabusa-2 Flight Model at JAXA (image credit: DLR, CNES)

 


 

MASCOT instruments: (MicrOmega, CAM, MAG, MARA)

The payload consists of a suite of instruments which fit into the payload compartment of the structure (Figure 63). Each instrument has its own electronic unit, which provides the signal conditioning to the instrument sensors/detectors and, where present, to the actuators, converts the acquired measurements into digital format and transmits them to the OBC via dedicated serial lines. The OBC is in charge of configuring the instruments, driving their acquisition sequence and performing data processing realizing instrument specific data acquisition modes. The instruments are not designed to be fault tolerant, except for the data lines, which are connected to both OBC main and redundant sections.

As an in situ Science Landing Package, MASCOT will augment the science capabilities of the Hayabusa-2 mission on three levels:

1) ‘Context Science' – By coordinated and complementary observations of the instruments on board MASCOT, on the main spacecraft and in combination with the lab analysis of the returned samples, MASCOT will ensure ground truth, down to the microscopic scale, for the acquired scientific results of the other mission elements. The goal is to obtain a cross-scale link with respect to surface and subsurface science , combining all three data sets to obtain a profound knowledge of the asteroid.

2) ‘Stand-alone Science' – MASCOT can perform unique investigations of major science importance including those that only a landed package can do, such as geophysics. Direct in situ measurements by the MASCOT instruments will also enable the analytical characterization of the elemental, isotopic and molecular (organic and mineral) composition of 1999JU3's surface and its near-surface material for samples in their natural state. Since 1999JU3 is a C-type asteroid, the astrobiological relevance of such measurements is significant. In addition, complementing visual documentation at the level of microscope scale would place the analytical results in context to the sample setting. MASCOT will investigate several locations on the asteroid to determine compositional and structural homogeneity and heterogeneity.

3) ‘Reconnaissance & Scouting' - By supporting Hayabusa-2's task of obtaining samples relevant to the top-level science objectives, MASCOT can serve as a ‘scouting vehicle' for assessing candidate sampling sites before the Hayabusa-2 samples are acquired; in other words, if enough lead time for MASCOT deployment is accounted for in mission operations, the final selection of the sampling sites can be guided by the results from the MASCOT instruments.

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Figure 63: Accommodation of the instruments in the MASCOT lander (image credit: DLR)

MicrOmega:

MicrOmega is a near infrared spectrometer and a hyperspectral infrared microscope for in situ mineralogical analyses of the ground, developed by IAS (Institut d'Astrophysique Spatiale, Orsay). The objective is to characterize the composition of surface samples at their grain scale. Supported by CNES, MicrOmega/MASCOT has been developed within the frame of the Pasteur payload of ExoMars' rover. It is also derived from a first MicrOmega model which was developed for Phobos Grunt. MicrOmega/MASCOT will enable the first in situ microscopic characterization of a C-type asteroid.

MicrOmega/MASCOT acquires monochromatic images of samples, 128 x 128 pixels of 20 µm2 each. The samples are illuminated by an AOTF-based dispersive system, onto a 2D HgCdTe array, cooled by a dedicated cryocooler. By scanning the illumination wavelength, over the spectral range 0.9 to 3.5 µm with steps of 20 cm-1, 3D (x,y,λ) image cubes are built, in about 10 mn.

The overall instrument, including its driving electronics, has a mass of 2 kg. The detector assembly, the illuminator and the analog electronic box of MicrOmega are shown in Figure 64.

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Figure 64: Photo of the MicrOmega flight model (image credit: CNES)

CAM (camera):

The camera is provided by DLR (Figure 65) is mounted inside the lander slightly tilted, such that the center of its FOV (Field of View) is aimed at the surface at an angle of 22º with respect to the surface plane. This implies that both the surface close to the lander at a distance of 15 cm and the horizon are in the FOV. The optics are designed according to the Scheimpflug principle, which ensures that the entire scene is in focus.

This wide angle camera uses LED illumination for nighttime operation. It is equipped with a 1024 x 1024 pixel CMOS sensor sensitive in the 400-1000 nm wavelength range, and has a FOV of 60° x 60°. The instantaneous field of view is 2.1 mrad/pixel. The camera images will be high priority and involve five pictures per day and four per night. Images will also be made during descent and hopping.

Each photo has a volume of 14.7 Mbit. The instrument has heritage from ExoMars, Rosetta/Philae and the ISS.

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Figure 65: Illustration of the CAM camera (image credit: DLR)

MAG (Magnetometer):

MAG is provided by TU Braunschweig, Germany. As indicated by meteorite composition, the asteroid material is magnetic, but how is the magnetic field arranged? In order to answer the question about the magnetization state of asteroids, MASCOT MAG shall:

- Observe magnetic field profile during descent and hopping

- Determine global and local magnetization of the asteroid.

This will provide new data on asteroid formation and history, and provide deeper insight on early planetary formation stages. MAG (Figure 4) is a three-axial fluxgate vector compensated magnetometer based on a long heritage (Themis, Rosetta, VeX, BepiColombo).Its main performance parameters are :

- Dynamic range is ±50000 nT

- Sensor noise (@1Hz) 10 pT/√Hz

- Resolution 6 pT

- Sampling rate 10 Hz

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Figure 66: Schematic view of MAG (image credit: TU Braunschweig)

MARA (MASCOT Radiometer):

MARA is a multispectral instrument, provided by DLR, to measure the radiative flux emitted from the asteroid's surface using thermopile sensors. Six individual filters will be employed to measure the flux in the wavelength bands between 5.5-7, 8-9.5, 9.5-11.5, 13.5-15.5, 8-14, and 5-100 µm. The primary scientific goal of the MARA instrument is the determination of the asteroid's thermal inertia, the secondary goal is the characterization of the surface mineralogy.

To determine the surface thermal inertia, MARA will measure the temperature of the asteroid's surface over the period of a full rotation using the long wavelength channel from 5 - 100 µm. In addition, the emissivity of the surface can be determined from the flux in the bandpass filters from 5.5-7, 8-9.5, 9.5-11.5, 13.5-15.5, and 8-14 µm. Thermal inertia can then be determined from an investigation of the surface radiative energy balance.

The mineralogy of the surface can be characterized from an investigation of the radiative flux in the same bandpass channels, as rock forming minerals like olivine and pyroxene have characteristic absorption features in the channels covered by MARA. In addition, the 8 to 14 µm filter is identical to the filter used by the thermal mapper on the Hayabusa-2 spacecraft, such that measurements by MARA can be directly compared to the results obtained from the spacecraft. In this way, MARA can provide ground truth at small scales, thus providing context for the spacecraft measurements.

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Figure 67: Photo of the MARA sensor head flight model (image credit: DLR)

MARA is mounted in between the infrared spectrometer and the camera, such that the FOV of MARA and the camera overlap. MARA consists of the following functional elements:

- Sensor head

- MARA electronics

- In-flight calibration surface.

 

Overview of the MASCOT operational concept:

In the context of Hayabusa-2 mission, the following major flight operational phases are foreseen for MASCOT:

1) Cruise phase (~4 years): MASCOT is normally off controlled in temperature by Hayabusa-2. At agreed times, MASCOT is activated from the ground to perform checkouts and instrument calibrations; Special operations, like PRM activation, instrument commissioning, on-board software maintenance are also foreseen.

2) Asteroid approach and global mapping: This phase is to characterize the asteroid's surface and select the target landing site based on scientific relevance and lander's constraints; Operational preparation for landing will occur: Initial on-board parameter tuning, science command sequences upload, on-asteroid operations rehearsal.

3) Pre-separation: Final on-board parameter tuning, final science command sequences upload, battery depassivation, full MASCOT check-out, lander pre-heating.

4) SDL (Separation, Descent and Landing) and on-asteroid operations: During an Hayabusa-2 descent maneuver, MASCOT will be deployed towards the asteroid's surface. Primary batteries will supply the power for the mission. Due to the short lifetime (10-16 hrs depending on the mission profile) all operations for science data collection, processing, downlink to Hayabusa-2, uprighting and hopping maneuvers will be fully autonomous, driven by the MAM (Mission Autonomy Manager), an OBSW package. This phase will last up to EOL (End-Of-Life), corresponding to the discharge of the primary batteries.

 

Autonomous Operations during SDL and On-Asteroid Phase:

After the global mapping and pre-separation phase operations, MASCOT will be released towards the asteroid's surface: Autonomous operations driven by the MAM will start at this point, after the separation detection. Manual commanding from the ground is still possible in parallel to MAM, but its use is only in case of unforeseen contingencies, not handled on-board. MAM commanding can be paused if necessary to avoid interference in the commanding.

MASCOT deployment will occur either during a dedicated Hayabusa-2 descent or during one of the Hayabusa-2 sampling touchdown rehearsals. This maneuver foresees Hayabusa-2 to descent to a separation altitude less than 100 m at which point MASCOT will get ejected via a spring mechanism. As MASCOT has no propulsion system, its descent to the surface of the asteroid will be completely passive, under the effects of the weak asteroid gravity field, followed by a bouncing period, before it comes to rest in
an unknown orientation. The descent to the asteroid after ejection should take approximately 20-30 minutes and the bouncing period strongly depends on the surface characteristics. Communications to Hayabusa-2 will be maintained active throughout this phase.

During descent, MASCOT will measure the asteroid magnetic field by the MAG instrument. The MAM will also schedule several image takings of the asteroid by the CAM instrument (a specific CAM image processing algorithm is implemented in the OBSW to discard dark - night sky - or saturated - sun facing - pictures).

During descent, MASCOT will measure the asteroid magnetic field by the MAG instrument. The MAM will also schedule several image takings of the asteroid by the CAM instrument (a specific CAM image processing algorithm is implemented in the OBSW to discard dark - night sky - or saturated - sun facing - pictures).

Once at rest on the surface, the MAM will start an upright maneuver, in case MASCOT is not laying with the -Z side (bottom) in contact with the surface: This is necessary for CAM, MARA and MicrOmega instrument science operations to characterize the asteroid soil. The upright maneuver may take several attempts and a specific FDIR algorithm has been devised to maximize the chance of success, to cope against adverse surface morphology and possible on-board failures.

Landing is currently foreseen at around the asteroid midday, so the MAM will schedule a day and a night science measurement cycle on the first landing location. Afterwards, the mobility mechanism will be activated by the MAM to send MASCOT in an uncontrolled hop across the asteroid's surface at a varying distance of up to a few 10 m. Further scientific activities will take place, and then, depending on the power and data download status, a second hop will be considered.

After MASCOT's release, Hayabusa-2 will return to its home position (HP), hovering 20 km above the asteroid's surface (Figure 68). During the ascent phase, pictures will be taken from Hayabusa-2 of the MASCOT landing site, using the asteroid camera.

The selected landing site will have to ensure the following characteristics:

- daylight duration between 50% and 70% of the asteroid's rotation period, due to thermal and scientific reasons (one asteroid day is estimated to be ~7.6 hours)

- the duration per asteroid rotation period of visibility of the landing site from Home Position must be over 40% (TM/TC link constraint)

- the velocity at touchdown must be smaller than half the escape velocity

- average surface temperature between -50ºC and +25ºC (under re-assessment) to grant acceptable landing conditions.

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Figure 68: MASCOT SDL and On-Asteroid Phase (image credit: DLR, Telespazio VEGA)

 


 

SRC (Sample Return Capsule)

The SRC is designed to deliver the asteroid samples to Earth. A series of major TCM (Trajectory Correction Maneuvers) are to be carried out starting a month before the reentry (R) day. The spacecraft is to be inserted into the reentry orbit targeting the landing center at the final TCM on about R-3 day. A schematic view of the reentry sequence is shown in Figure 69. - The SRC is separated from the mothership about 8 hours before the reentry and the spacecraft will enter the escape trajectory after orbital maneuvering by the RCS while the SRC enters Earth's atmosphere at a velocity of about 12 km/s. After passing through the severe aerodynamic environment, SRC deploys the parachute at the altitude of about 5 km and it descends slowly with beacon signal emitted for localization until landing on the ground. 66)

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Figure 69: Schematic view of the reentry sequence (image credit: JAXA)

Figure 70 shows the aerodynamic heating environment of the Hayabusa-2 SRC when compared with that of Hayabusa-1 as a function of the flight path angle and the entry velocity. The main parameters dominating the reentry flight environment are the flight path angle and the entry velocity while the effect of the entry position (latitude/longitude) and the flight azimuth direction is secondary, so that we can neglect them at the present discussion. A maximum heat flux of 13 MW/m2 is predicted on the stagnation heat transfer rate with total heat input of 270 MJ/m2.

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Figure 70: Aerodynamic heating environment of the Hayabusa-2 Capsule compared with that of Hayabusa-I as a function of the flight path angle and the entry velocity (image credit: JAXA)

Design and verification tests for the Hayabusa-2 SRC:

There are strong demands of short-term development and cost reduction as well as improvement of the reliability for the Hayabusa-2 project. Therefore, the basic design concept for the Hayabusa-2 SRC is not to change the design from the former SRC except for the following items:

1) During the period of over 10 years since the development of the Hayabusa-1 SRC, some components have gone out of production. Since the many electronics parts, including FPGAs, used as the core processors of the SRC instrument module are discontinued, the onboard electronics of the instrument module need to be redesigned.

2) The SRC design needs to be improved based upon the experience of Hayabusa-1 operation. Examples of this case include employing a new HK telemetry for monitoring of the on-board clock accuracy and a backup timer for generating the parachute deployment trigger for the case of an acceleration sensor malfunction.

3) The items judged by their design shall be changed to be compatible with the change of the design condition such as environmental requirements and the design standard of Hayabusa-2 system. Examples of this case include a change of the criterion on the tensional force of the Marman Clamp band of the SRC separation mechanism.

4) The items judged by their design need to be improved to ensure higher reliability based on the result of the design review including the evaluation of the reliability analysis such as FMEA, FTA and SPFA. Examples of this case include a change of an ignition circuit design, strengthening of the puller used for the SRC separation mechanism, and an adoption of the additional O-ring to prevent the inflow of high-temperature gas during reentry operation.

 

Overview of the SRC Subsystem:

Hayabusa-2 SRC is designed with the following functions in its compact body:

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Figure 71: Hayabusa-2 SRC reentry configuration (image credit: JAXA)

• Sampler Interface: SRC has an interface with the sampler-container system for collecting and storing asteroid sample. The sampler-container is fixed to the inside of the SRC at the time of the launch. The sampler-catcher is held in the sampler-mechanism. After Hayabusa-2 approaches the target asteroid and collects a "sample", the sampler-catcher is conveyed into the sampler container and is fixed to it with the latch mechanism. The SRC conducts the Earth reentry in the configuration of Figure 71.

• Mothership Interface / SRC Separation Mechanism: In addition to its mechanical I/F, the SRC has electric and thermal I/F with the mother ship, such as HK telemetry, command, heater control, and external power supply from the mothership. The SRC separation mechanism holds the SRC on the mothership during the orbital flight. The mechanism deploys the Merman Clamp band and ejects the SRC from the mothership with proper velocity and spin rate given by the helical coil spring.

• Heatshield and Thermal Protection Subsystem: In order to protect the internal instruments from the aerodynamic heating environment during reentry operation, the SRC is wrapped with an ablator made of carbon phenolic resin. The ablator consists of four parts; the fore body ablator, the aft ablator, the support ablator and the sampler ablator. With the aim of avoiding soakback from the ablator, the instrument box in the SRC throws the fore body ablator and the aft ablator away after passing through the excessively severe aerodynamic environment (Figure 72).

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Figure 72: Hayabusa-2 SRC reentry configuration (image credit: JAXA)

• Descending Subsystem: After the separation of the ablators, the instrument box connected to a parachute starts slow descending. The descending system consists of the cross-type parachute, the parachute deployment mechanism and the ignition circuit (IG-BOX). The instrument box is also equipped with the parachute anchor release mechanism in order to avoid breakage due to dragging by strong ground-winds after landing.

• Beacon Transmission: The beacon antenna is pulled out and hanged from the bottom of the instrument module (I/M) by a small mass at the time of the parachute deployment. And simultaneously, I/M starts transmitting the beacon signal for the localization from the ground stations. The beacon is transmitted even after the instrument box lands on the ground according to the prescribed sequence.

• Reentry Flight Measurement: Hayabusa-2 has a new capability to measure acceleration, attitude motion (angular rate) and the temperature of each part inside the SRC during reentry operation. The measurement data is stored to a memory and is retrieved after recovery. This function is implemented in a new instrument: REMM (Reentry Flight Measurement Module).

REMM is an instrument which was newly developed to add the function of flight environment measurement to SRC. REMM measures the heat shield temperatures, the acceleration and the attitude motion of the SRC during the reentry and records the measurement data to a non-volatile memory. Since there is no structural design change for Hayabusa-2 SRC, only very limited space and mass can be allocated for the REMM. A COTS based design was adopted in design of REMM to meet the requirement under this very strict constraints.

Acceleration

- Range
- Sample rate
- Measurement error

-50 to +50 G (3-axis)
125 Hz
Random <0.1 G (1σ), Bias < 0.25 G, Nonlinearity < 2%

Angular rate

- Range
- Sample rate
- Measurement error

±200º/s(3-axis)
125 Hz
Random < 0.1º/s (1σ), Bias < 0.6º/s, Nonlinearity < 0.5%

Temperature

- Channel number
- Range
- Range rate
- Measurement error

13 ch (9 ch for SRC, 4 ch for REMM internal use)
-50 to +600ºC
1 HZ
±3ºC (-50 to +400ºC), ±8ºC (+400 to +600ºC)

Measurement duration

420 s

Data storage

Flash memory 8 Mbit x 2 (redundancy)

Power supply

Primary cell used separately from the power source for SRC bus electronics.

Table 7: Specification of REMM

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Figure 73: REMM functional block diagram (image credit: JAXA)

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Figure 74: REMM FM (Flight Model) and its configuration in SRC (image credit: JAXA)

 


1) "Asteroid Explorer Hayabusa2," JAXA, brochure, URL: http://global.jaxa.jp/activity/pr/brochure/files/sat33.pdf

2) "Hayabusa 2 Project," JAXA, URL: http://b612.jspec.jaxa.jp/hayabusa2/e/hayabusa2_e.html

3) http://www.jspec.jaxa.jp/e/activity/hayabusa2.html

4) H. Kuninaka, "Robotic Pre-Cursor Contribution to Human NEA Mission," URL: http://www.nasa-usa.de/pdf/604314main_6-GER_WS
_JAXA-RoboticPrecursor-Kuninaka.pd
f

5) Paul Abell, H. Kuninaka, N. Inaba, Y. Tsuda, M. Yoshikawa, "Hayabusa-2,"11th SBAG (Small Bodies Assessment Group) Meeting, Washington, D.C., July 29-31, 2014, URL: http://www.lpi.usra.edu/sbag/meetings/jul2014/
presentations/0330_Tue_Abell_Hyabusa2.pdf

6) Makoto Yoshikawa, Hitishi, Kuninaka, Noriyasu Inaba, Sei-ichiro Watanabe, Yuichi Tsuda, Ryudo Tsukizaki, "Status of the Japanese Hayabusa-2 asteroid explorer mission," Proceedings of the 65th International Astronautical Congress (IAC 2014), Toronto, Canada, Sept. 29-Oct. 3, 2014, paper: IAC-14-A7.3.4

7) H. Kuninaka, "Hayabusa-2 Asteroid Sample Return Mission," 10th SBAG (Small Bodies Assessment Group) Meeting, Washington, D.C., Jan. 8-9,2014, URL: http://www.lpi.usra.edu/sbag/meetings/jan2014/presentations/09_1500_Kuninaka_Haya2-SBAG.pdf

8) Hitoshi Kuninaka, Hajime Yano, "Hayabusa-2: Carbonaceous Asteroid Sample Return Mission," The 10th IAA International Conference on Low-Cost Planetary Missions," Pasadena, CA, USA, June 18-20, 2013, URL: http://www.lcpm10.caltech.edu/pdf/session-3/
4_LCPM2013-Hayabusa2-HK%2BHY.pdf

9) Sho Sasaki, Makoto Yoshikawa, Hayabusa-2 Project Team, "The Next Asteroid Sample Return Mission of Japan - Hayabusa-2," March 5, 2011, URL: http://www.lpi.usra.edu/meetings/sssr2011/presentations/yoshikawa.pdf

10) Yuya Mimasu, Go Ono, Kosuke Akatsuka, Fuyuto Terui, Naoko Ogawa, Takanao Saiki, Yuichi Tsuda, "Attitude Control of Hayabusa2 by Solar Radiation Pressure in One Wheel Control Mode," Proceedings of the 25th International Symposium on Space Flight Dynamics, Munich, Germany, Oct. 19-23, 2015, URL: http://issfd.org/2015/files/downloads/papers/129_Mimasu.pdf

11) "Launch Success of H-IIA Launch Vehicle No. 26 with "Hayabusa2" Onboard," JAXA Press Release, December 3, 2014, URL: http://global.jaxa.jp/press/2014/12/20141203_h2af26.html

12) "MASCOT en route to Asteroid 1999 JU3," DLR, Dec. 3, 2014, URL: http://www.dlr.de/dlr/en/desktopdefault.aspx/tabid-
10081/151_read-12372/year-all/#/gallery/17357

13) Bruno Victorino Sarli, Yoshihide Sugimoto, Chit Hong Yam, Stefano Campagnola, Naoya Ozaki, Hongru Chen, Shintaro Nakajima, Satoshi Ogura, Ryu Funase, Yasuhiro Kawakatsu, Shinichi Nakasuka, "PROCYON Mission: A Micro-Spacecraft to an Asteroid," Proceedings of the 65th International Astronautical Congress (IAC 2014), Toronto, Canada, Sept. 29-Oct. 3, 2014, paper: IAC-14, A3.P, 41

14) "TD1-R1-A operation schedule," JAXA, Hayabusa-2 Project, 14 October 2018, URL: http://www.hayabusa2.jaxa.jp/en/topics/20181014e_TD1-R1-A/

15) "Numerous boulders, many rocks, no dust: MASCOT's zigzag course across the asteroid Ryugu," DLR News, 12 October 2018, URL: https://www.dlr.de/dlr/en/desktopdefault.aspx/
tabid-10081/151_read-30235/year-all/#/gallery/32338

16) "Japan delays touchdown of Hayabusa2 probe on asteroid: official," Space Daily, 11 October 2018, URL: http://www.spacedaily.com/reports/Japan_delays_
touchdown_of_Hayabusa2_probe_on_asteroid_official_999.html

17) "Three hops in three asteroid days – MASCOT successfully completes the exploration of the surface of asteroid Ryugu," DLR, 5 October 2018, URL: https://www.dlr.de/dlr/en/desktopdefault.aspx/tabid-
10081/151_read-30138/year-all/#/gallery/32253

18) Tra-Mi Ho, Ralf Jaumann, Jean-Pierre Bibring, Matthias Grott, David Herčík, Stephan Ulamec, Jens Biele, Jan Thimo Grundmann, Christian Krause, Oliver Küchemann, Caroline Lange, Michael Lange, Laurence Lorda, Michael Maibaum, Aurelie Moussi, Celine Cenac-Morthe, Tatsuaki Okada, Josef Reill, Kaname Sasaki, Norbert Toth,Yuichi Tsuda, Tetsuo Yoshimitsu and the MASCOT Team, "MASCOT: Latest News of Landing on (162173) Ryugu," Proceedings of the 69th IAC (International Astronautical Congress) Bremen, Germany, 1-5 October 2018, paper: IAC-18,A3,4A,2

19) "MASCOT lands safely on asteroid Ryugu," DLR News, 03 October 2018, URL: https://www.dlr.de/dlr/en/desktopdefault.aspx/
tabid-10081/151_read-30118/year-all/#/gallery/32231

20) "The small asteroid lander, MASCOT," JAXA, 02 October, 2018, URL: http://www.hayabusa2.jaxa.jp/en/topics/20181002e_MSC/

21) "MINERVA-II1: Images from the surface of Ryugu," JAXA, 23 09.2018, URL: http://www.hayabusa2.jaxa.jp/en/topics/20180927e_MNRV/

22) "A shadowy selfie taken 180 million miles away," ESA, Operations image of the week, 27 September 2018, URL: http://m.esa.int/spaceinimages/Images/2018/
09/A_shadowy_selfie_taken_180_million_miles_away

23) "MINERVA-II1: Successful image capture, landing on Ryugu and hop!," JAXA, 21 September 2018, URL: http://www.hayabusa2.jaxa.jp/en/topics/20180922e/

24) "Japan space robots start asteroid survey," Space Daily, 22 September 2018, URL: http://www.spacedaily.com/reports/Japan_space_robots_
start_asteroid_survey_999.html

25) "Landing site on the asteroid Ryugu determined," DLR, 23 August 2018, URL: https://www.dlr.de/dlr/en/desktopdefault.aspx/
tabid-10081/151_read-29511/year-all/

26) "Imaging Ryugu from an altitude of 6 km," JAXA, 25 July 2018, URL: http://global.jaxa.jp/projects/sat/hayabusa2/topics.html#topics12394

27) http://www.hayabusa2.jaxa.jp/topics/20180725je/index_e.html

28) Manuela Braun, "Landing on Ryugu – a surface with a view of boulders - Interview with Ralf Jaumann, DLR planetary researcher and Principal Investigator of the MASCOT lander ," DLR, 14 August, 2018, URL: https://www.dlr.de/dlr/en/desktopdefault.aspx
/tabid-10081/151_read-29344/year-2018/#/gallery/31672

29) "Asteroid Ryugu," ESA, 28 June 2018, URL: http://m.esa.int/spaceinimages/Images/2018/06/Asteroid_Ryugu

30) "Hayabusa2 Rendezvous with Ryugu," JAXA Press Release, 27 June 2018, URL: http://global.jaxa.jp/press/2018/06/20180627_hayabusa2.html

31) "Hayabusa2 and MASCOT lander nearing Ryugu," DLR, 15 June 2018, URL: http://www.dlr.de/blogs/en/all-blog-posts/
Hayabusa2-and-MASCOT-lander-nearing-Ryugu.aspx

32) "Current status of the asteroid explorer, Hayabusa2, leading up to arrival at asteroid Ryugu in 2018," JAXA Hayabusa-2 Project, 14 June 2018, URL: http://global.jaxa.jp/projects/sat/hayabusa2/pdf/Hayabusa2_Press20180614e.pdf

33) "Hayabusa2 has detected Ryugu!," JAXA, 1 March 2018, URL: http://www.hayabusa2.jaxa.jp/topics/20180301_e/

34) "Hayabusa2 has detected Ryugu," JAXA Press Release, 1 March 2018, URL: http://global.jaxa.jp/press/2018/03/20180301_hayabusa2.html

35) Tomohiro Yamaguchi, Takanao Saiki, Satoshi Tanaka, Yuto Takei, Tatsuaki Okada, Tadateru Takahashi, Yuichi Tsuda, "Hayabusa2-Ryugu Proximity Operation Planning and Landing Site Selection," Proceedings of the 68th IAC (International Astronautical Congress), Adelaide, Australia, 25-29 Sept. 2017, paper: IAC-17-A3.4A.7

36) Christian Ziach, Volodymyr Baturkin, Christian Grimm, Jan Thimo Grundmann, Tra-Mi Ho, Caroline Lange, Kaname Sasaki, Nawarat Termtanasombat, Norbert Toth, Elisabet Wejmo, Maximilian Maier, Josef Reill, Hans-Jürgen Sedlmayr, Friederike Wolff, Michael Lange, Olaf Mierheim, Jens Biele, Barbara Cozzoni, Cinzia Fantinati, Koen Geurts, Kagan Kayal, Christian Krause, Oliver Küchemann, Michael Maibaum, Stephan Ulamec, Matthias Grott, Ralf Jaumann, Céline Cénac-Morthe, Muriel Deleuze, Clément Dudal, David Granena, Laurence Lorda, Aurélie Moussi, Jean-Pierre Bibring, David Hercik, Hans-Ulrich Auster, Yuya Mimasu, Tatsuaki Okada, Takanao Saiki, Sathoshi Tanaka, Fuyuto Terui, Yuichi Tsuda, Tomohiro Yamaguchi, Tetsuo Yoshimitsu, Seiichiro Watanabe, "MASCOT – preparations for its landing in 2018: a status update from ground and space one year ahead of the landing on Ryugu," Proceedings of the 68th IAC (International Astronautical Congress), Adelaide, Australia, 25-29 Sept. 2017, paper: IAC-17-A3.4.7

37) Yuichi Tsuda, Sei-ichiro Watanabe, Takanao Saiki, Makoto Yoshikawa, Satoru Nakazawa, "Cruise Status of Hayabusa2 : Round Trip Mission to Asteroid 162173 Ryugu," Proceedings of the 67th IAC (International Astronautical Congress), Guadalajara, Mexico, Sept. 26-30, 2016, paper: IAC-16.A3.4.5

38) Ono Go, Yuichi Tsuda, Kosuke Akatsuka, Takanao Saiki, Yuya Mimasu, Naoko Ogawa, and Fuyuto Terui. "Generalized Attitude Model for Momentum-Biased Solar Sail Spacecraft", Journal of Guidance, Control, and Dynamics, Vol. 39, No. 7,2016, pp. 1491-1500

39) "Health check for asteroid lander MASCOT," DLR, July 14, 2016, URL: http://www.dlr.de/dlr/en/desktopdefault.aspx/
tabid-10081/151_read-18664/year-all/#/gallery/23720

40) "The Optical Link Experiment with the Laser Altimeter (LIDAR)," JAXA, Dec. 25, 2015, URL: http://www.hayabusa2.jaxa.jp/topics/20151225_02_e/

41) "Hayabusa2 Earth Swing-by Result," JAXA, Dec. 14, 2015, URL: http://global.jaxa.jp/press/2015/12/20151214_hayabusa2.html#pic1

42) Takanao Saiki , Hiroshi Takeuchi, Tomohiro Yamaguchi, Yuto Takei, Satoshi Tanaka, Yuichi Tsuda, "Hayabusa2 Earth Swing-by Operation Results," Proceedings of the 67th IAC (International Astronautical Congress), Guadalajara, Mexico, Sept. 26-30, 2016, paper: IAC-16-A3.4.4

43) "Hayabusa2 Earth Swing-by," JAXA, Dec. 3, 2015, URL: http://global.jaxa.jp/projects/sat/hayabusa2/topics.html#topics6403

44) "ESA station tracks Earth flyby mission," ESA, Dec. 3, 2015, URL: http://www.esa.int/Our_Activities/Operations/
Estrack/ESA_station_tracks_Earth_flyby_mission

45) "Name Selection of Asteroid 1999 JU3 Target of the Asteroid Explorer "Hayabusa2" ," JAXA Press Release, Oct. 5, 2015, URL: http://global.jaxa.jp/press/2015/10/20151005_ryugu.html

46) "Hayabusa2 second ion engine continuous operation completed," JAXA, June 8, 2015, URL: http://global.jaxa.jp/projects/sat/topics.html

47) "Tracking Japan's Asteriod Impact Mission," ESA, April 29, 2015, URL: http://www.esa.int/Our_Activities/Operations
/Tracking_Japan_s_asteroid_impact_mission

48) "Baton passes to new Hayabusa2 project manager," JAXA, April 10, 2015, URL: http://global.jaxa.jp/projects/sat/hayabusa2/topics.html#topics4474

49) H. Senshu, S. Oshigami, R. Yamada, M. Kobayashi, N. Namiki, T. Mizuno, and the Hayabusa-2 LIDAR science team, "Dust count mode of LIDAR onboard Hayabusa-2," 46th LPSC (Lunar and Planetary Science Conference), The Woodlands, TX, USA, March 16-20, 2015, paper:1863, URL: http://www.hou.usra.edu/meetings/lpsc2015/pdf/1863.pdf

50) S. Oshigami, H. Senshu, R. Yamada, N. Namiki, T. Mizuno, and the Hayabusa-2 LIDAR science team, "Detectability of levitation dust around the asteroid by Hayabusa-2 LIDAR,"Detectability of levitation dust around the asteroid by Hayabusa-2 LIDAR," 46th LPSC (Lunar and Planetary Science Conference), The Woodlands, TX, USA, March 16-20, 2015, paper:1292, URL: http://www.hou.usra.edu/meetings/lpsc2015/pdf/1292.pdf

51) "Hayabusa2 initial functional confirmation completed and moved to cruising phase to asteroid 1999 JU3," JAXA, March 5, 2015, URL: http://global.jaxa.jp/projects/sat/hayabusa2/topics.html

52) "Hayabusa2 in great shape – Initial functional confirmation going smoothly," JAXA, Feb. 3, 2015, URL: http://global.jaxa.jp/projects/sat/hayabusa2/topics.html#topics3767

53) M. Yoshikawa, "Status Update of Hayabusa2," 52nd session of the Scientific and Technical Subcommittee, UNOOSA (United Nations Office for Outer Affairs), Vienna, Austria, Feb. 2-13, 2015, URL: http://www.unoosa.org/pdf/pres/stsc2015/tech-17E.pdf

54) "Asteroid Explorer "Hayabusa-2" Completion of Critical Operation Phase," JAXA Press Release, Dec. 5, 2014, URL: http://global.jaxa.jp/press/2014/12/20141205_hayabusa2.html

55) "Asteroid Explorer "Hayabusa2" Flight Status and Orbit Calculation Result," JAXA Press Release, Dec. 3, 2014, URL: http://global.jaxa.jp/press/2014/12/20141203_hayabusa2.html

56) "Overview of Hayabusa2 major onboard instruments," JAXA, URL: http://global.jaxa.jp/projects/sat/hayabusa2/instruments.html

57) Tetsuo Yoshimitsu, Takashi Kubota, Atsushi Tomiki, "Asteroid surface exploration rovers developed for Hayabusa-2 mission," Proceedings of the 66th International Astronautical Congress (IAC 2015), Jerusalem, Israel, Oct.12-16, 2015, paper: IAC-15-A3.4.5

58) K. Ogawa, M. Arakawa, H. Sawada, Y. Iijima, K. Wada, R. Honda, K. Shirai, K. Ishibashi, N. Sakatani , T. Kadono, S. Nakazawa, M. Kobayashi, H. Hayakawa, "Development of Hayabusa-2 Deployable Camera (DCAM3) for observation of impact simulation on asteroid," EPSC Abstracts, Vol. 8, EPSC2013-733, 2013 EPSC (European Planetary Science Congress), 2013, URL: http://meetingorganizer.copernicus.org/EPSC2013/EPSC2013-733.pdf

59) "Hayabusa-2 Optical Navigation Camera (ONC)," JAXA, 2017, URL: http://darts.isas.jaxa.jp/pub/hayabusa2/onc_bundle/browse/

60) Pierre W. Bousquet, Muriel Deleuze, Elisabet Canalias, Tra-Mi Ho, Stephan Ulamec, Ralf Jaumann, Matthias Grott, Karl Heinz Glassmeier, Jean-Pierre Bibring, Tatsuaki Okada, "MASCOTt, a small asteroid lander ready for launch on Hayabusa-2," Proceedings of the 65th International Astronautical Congress (IAC 2014), Toronto, Canada, Sept. 29-Oct. 3, 2014, paper: IAC-14-A3.4.7

61) M. Schlotterer, R. Findlay, T.-M. Ho, L. Witte, C. Ziach, "Histogram filter for attitude determination of small asteroid lander," GNC 2014: 9th International ESA Conference on Guidance, Navigation Control Systems, Porto, Protugal, June 2-6, 2014, URL: http://elib.dlr.de/90209/1/1425_Schlotterer.pdf

62) Christian Ziach, Volodymyr Baturkin, Tra-Mi Ho, Christian Grimm, Jan Thimo Grundmann, Caroline Lange, Nawarat Termtanasombat, Elisabet Wejmo, Ross Findly, Josef Reill, Michael Lange, Olaf Mierheim, Jens Biele, Christian Krause, Stephan Ulamec, Belinda Borgs, Matthias Grott, Ralf Jaumann, Muriel Deleuze, Jean-Pierre Bibring, Hans-Ulrich Auster and the MASCOT Project Team, "MASCOT, the small mobile asteroid landing package on its piggyback journey to 1999 JU3: pre-launch and post-launch activities," Proceedings of the 66th International Astronautical Congress (IAC 2015), Jerusalem, Israel, Oct.12-16, 2015, paper: IAC-15-A3.4.6

63) Michael Lange, Christian Hühne, Olaf Mierheim, "Detailed structural design and corresponding manufacturing techniques of the MASCOT Landing Module for the Hayabusa2 mission," Proceedings of the 66th International Astronautical Congress (IAC 2015), Jerusalem, Israel, Oct.12-16, 2015, paper: IAC-15-C2.9.9

64) Aurélie Moussi, Laurence Lorda, Céline Cénac-Morthé, David Granena, Clement Dudal, Elisabet Canalias, Thierry Martin, Muriel Deleuze, Jean-Pierre Bibringb, Vincent Hamm, Cédric Pilorget,Tra-Mi Ho, Christian Ziach, Jan Thimo Grundmann , Nawarat Termtanasombat, Christian Krause, Cinzia Fantinati, Michael Maibaum, Barbara Cozzoni , Jens Biele, Yuya Mimasu, Tatsuaki Okada, Takanao Saiki, Sathoshi Tanaka, Fuyuto Terui, Yuichi Tsuda, Tomohiro Yamaguchi, Tetsuo Yoshimitsu, Seiichiro Watanabe, "French Contributions to HAYABUSA-2-MASCOT: Philae mission's inheritance?," Proceedings of the 68th IAC (International Astronautical Congress), Adelaide, Australia, 25-29 Sept. 2017, paper: IAC-17-A3.4.8

65) Federico Cordero, Johan Marx, Eduard Baumstark, Kağan Kayal, Tra-Mi Ho, Christian Ziach, Caroline Lange, Nawarat Termtanasombat, Jan Thimo Grundmann, Christian Krause, "MASCOT Lander Operational Concept and its Autonomy, General Services and Resource Optimisation Implementation in the On-Board Software," Proceedings of the 14th International Conference on Space Operations (SpaceOps 2016), Daejeon, Korea, May 16-20, paper: AIAA 2016 2016 2386, URL: http://arc.aiaa.org/doi/pdf/10.2514/6.2016-2386

66) Tetsuya Yamada, Keisuke Yoshihara, "Design review of Hayabusa-2 reentry capsule and further technology development for future missions," Proceedings of the 65th International Astronautical Congress (IAC 2014), Toronto, Canada, Sept. 29-Oct. 3, 2014, paper: IAC-14.A3.4.6
 


The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates (herb.kramer@gmx.net).

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