Minimize Swarm

Swarm (Geomagnetic LEO Constellation)

Space segment concept     Launch    Swarm's Orbits    Mission Status     Sensor Complement 
Ground Segment    References

Swarm is a minisatellite constellation mission within the Earth Explorer Opportunity Program of ESA, proposed under the lead of DNSC (Danish National Space Center) of Copenhagen, Denmark (formerly DSRI). In January 2007, DNSC became DTU Space, an institute at the Technical University of Denmark. The Swarm mission will be the 4th mission in ESA's Earth Explorer Program, following GOCE, SMOS, and CryoSat-2.

The first mission to ever map the Earth's magnetic field vector at LEO was the NASA MagSat spacecraft (launch Oct. 30 1979). Due to the low perigee (perigee=350 km, apogee=551 km), MagSat remained in orbit for only seven and a half months until June 11, 1980. About 20 years later, the Danish Ørsted micro satellite (1999-), the German CHAMP (2000-), the Argentine SAC-C (2000-) have been designed specifically for mapping the LEO magnetic field. Common to these recent missions is the magnetometry package, which utilizes a vector field magnetometer co-mounted with a star tracker (2 in the case of CHAMP) on an optical bench. As the accuracy of the instrument package has constantly increased, as well as the modelling methods have been improved towards optimized signal decomposition, it has been realized that simultaneous data from several points in space is needed, if the ultimate modelling barrier, the spatial-temporal ambiguity, has to be broken.

The overall objective of the Swarm mission is to build on the Ørsted and CHAMP mission experiences and to provide the best ever survey of the geomagnetic field (multi-point measurements) and its temporal evolution, to gain new insights into the Earth system by improving our understanding of the Earth's interior and climate. 1) 2) 3) 4) 5) 6) 7) 8) 9) 10) 11) 12) 13) 14) 15) 16) 17) 18)

This will be done by a constellation of three satellites, two will fly at a lower altitude, measuring the East-West gradient of the magnetic field, and one satellite will fly at a higher altitude in a different local time sector. Other measurements will also be made to complement the magnetic field measurements. Together these multipoint measurements will allow the deduction of information on a series of solid-Earth processes responsible for the creation of the fields measured.

Background on the discovery of electromagnetism:

The history of magnetic discovery goes back to about 110 B.C., when the earliest magnetic compass was invented by the Chinese. They noticed hat if a "lodestone" (natural magnets of iron-rich ore) was suspended so it could turn freely, it would always point in the same direction, toward the magnetic poles. This directional pointing property of magnetic material was eventually introduced into the making of an early compass and used for maritime navigation . By the 13th century, the directive property of magnetism was widely recognized and used in navigation. The mariner's magnetic compass is the first technological application of magnetism and, one of the oldest scientific instruments.

Until 1820, the only magnetism known was that of iron magnets and of lodestones. It was the Danish physicist Hans Christian Ørsted, professor at the University of Copenhagen, who, in 1820, was first to discover the relationship between the hitherto separate fields of electricity and magnetism. Ørsted showed that a compass needle was deflected when an electric current passed through a wire, before Faraday had formulated the physical law that carries his name: the magnetic field produced is proportional to the intensity of the current. Magnetostatics is the study of static magnetic fields, i.e. fields which do not vary with time. 19) 20)

Magnetic and electric fields together form the two components of electromagnetism. Electromagnetic waves can move freely through space, and also through most materials at pretty much every frequency band (radio waves, microwaves, infrared, visible light, ultraviolet light, X-rays and gamma rays). Electromagnetic fields therefore combine electric and magnetic force fields that may be natural (the Earth's magnetic field) or man-made (low frequencies such as electric power transmission lines and cables, or higher frequencies such as radio waves (including cell phones) or television (Ref. 21).

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Figure 1: The early history of electromagnetic discovery made by scientists throughout the centuries (image credit: ESA, Ref. 15)

 

Background on the Earth's magnetic field:

The Earth has its own magnetic field, which acts like a giant magnet. Geomagnetism is the name given to the study of this field, which can be roughly described as a centered dipole whose axis is offset from the Earth's axis of rotation by an angle of about 11.5º. This angle varies over time in response to movements in the Earth's core. The angle between the direction of the magnetic and geographic north poles, called the magnetic declination, varies at different points on the Earth's surface. The angle that the magnetic field vector makes with the horizontal plane at any point on the Earth's surface is called the magnetic inclination.

This centered dipole exhibits magnetic field lines that run between the north and south poles. These field lines convergent and lie vertical to the Earth's surface at two points known as the magnetic poles, which are currently located in Canada and Adélie Land. Compass needles align themselves with the magnetic north pole (which corresponds to the south pole of the 'magnet' at the Earth's core).

The Earth's magnetic field is a result of the dynamo effect generated by movements in the planet's core, and is fairly weak at around 0.5 gauss, i.e. 5 x 10-5 tesla (this is the value in Paris, for example). The magnetic north pole actually 'wanders' over the surface of the Earth, changing its location by up to tens of km every year. Despite its weakness, the Earth's dipolar field nevertheless screen the Earth from charged particles and protect all life on the planet from the harmful effects of cosmic radiation. In common with other planets in our solar system, the Earth is surrounded by a magnetosphere that shields its surface from solar wind, although this solar wind does manage to distort the Earth's magnetic field lines.

The Earth's magnetic field shows deviations, called anomalies, from the idealized field of a centered bar magnet. These anomalies can be quite large, affecting areas on a regional scale. One example is the SAA (South Atlantic Anomaly), which affects the amount of cosmic radiation reaching the passengers and crew of any plane and spacecraft led to cross it (Ref. 21).

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Figure 2: Artist's view of solar wind interacting with Earth's magnetic field (image credit: DTU Space)

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Figure 3: Schematic view of the geomagnetic field, produced mainly by a self-sustaining dynamo in the outer fluid core (image credit: GFZ)

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Figure 4: Map of the geomagnetic field strength at the surface of the Earth derived from the model produced using data from the Oersted satellite (image credit: LETI) 21)

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Figure 5: Magnetic field contributions (image credit: ESA) 22)

 

The primary research topics to be addressed by the Swarm mission include: 23)

• Core dynamics, geodynamo processes, and coremantle interaction. - The goal is to improve the models of the core field dynamics by ensuring long-term space observations with an even better spatial and temporal resolution. Combining existing Ørsted, CHAMP and future Swarm observations will also more generally allow the investigation of all magnetohydrodynamic phenomena potentially affecting the core on sub-annual to decadal scales, down to wavelengths of about 2000 km. Of particular interest are those phenomena responsible for field changes that cannot be accounted for by core surface flow models. 24)

• Lithospheric magnetization and its geological interpretation. - The increased resolution of the Swarm satellite constellation will allow, for the first time, the identification from satellite altitude of the oceanic magnetic stripes corresponding to periods of reversing magnetic polarity. Such a global mapping is important because the sparse data coverage in the southern oceans has been a severe limitation regarding our understanding of plate tectonics in the oceanic lithosphere. Another important implication of improved resolution of the lithospheric magnetic field is the possibility to derive global maps of heat flux. 25) 26)

• 3-D electrical conductivity of the mantle. - Our knowledge of the physical and chemical properties of the mantle can be significantly improved if we know its electrical conductivity. Due to the sparse and inhomogeneous distribution of geomagnetic observatories, with only few in oceanic regions, a true global picture of mantle conductivity can only be obtained from space.

• Currents flowing in the magnetosphere and ionosphere. - Simultaneous measurements at different altitudes and local times, as foreseen with the Swarm mission, will allow better separation of internal and external sources, thereby improving geomagnetic field models. In addition to the benefit of internal field research, a better description of the external magnetic field contributions is of direct interest to the science community, in particular for space weather research and applications. The local time distribution of simultaneous data will foster the development of new methods of co-estimating the internal and external contributions.

The secondary research objectives include:

• Identification of the ocean circulation by its magnetic signature. - Moving sea-water produces a magnetic field, the signature of which contributes to the magnetic field at satellite altitude. Based on state-of-the-art ocean circulation and conductivity models it has been demonstrated that the expected field amplitudes are well within the resolution of the Swarm satellites. 27)

• Quantification of the magnetic forcing of the upper atmosphere. - The geomagnetic field exerts a direct control on the dynamics of the ionized and neutral particles in the upper atmosphere, which may even have some influence on the lower atmosphere. With the dedicated set of instruments, each of the Swarm satellites will be able to acquire high-resolution and simultaneous in-situ measurements of the interacting fields and particles, which are the key to understanding the system.

Historic background of Swarm: Ref. 13)

• The first Swarm proposal was made in 1998, prior to launch of the Ørsted mission.

• In early 2002, the Swarm mission was proposed to ESA by Eigil Friis-Christensen of DNSC (Copenhagen, Denmark), Hermann Lühr of GFZ (GeoForschungszentrum, Potsdam, Germany), and Gauthier Hulot of IPG (Institut de Physique du Globe, Paris, France) with support from scientists in seven European countries and the USA. In the meantime, the Swarm team comprises participation of 27 institutes on a global scale. The mission was selected for feasibility studies in 2002. The initial mission proposal considered a Swarm constellation of 4 spacecraft. 28)

• In May 2002 there were three mission candidates: ACE+, EGPM and Swarm; they were chosen for a feasibility study.

• At the end of two parallel feasibility studies, the Swarm mission was selected as the 5th mission in ESA's Earth Explorer Program in May 2004. Phase A was completed in Nov. 2005, resulting in a constellation of 3 spacecraft.

New Concept – Constellation to characterize external sources:

- The external contributions are highly influenced by solar activity and local time

- Simultaneous satellites in different orbital planes are necessary in order to overcome the time-space ambiguity in the measurements. The optimum constellation depends on the scientific objectives.

- But, measurements of high accuracy are not sufficient! A better understanding of the various sources is equally important, in particular when doing measurements with unprecedented precision, where new phenomena appear in the data. For this, additional and independent key information is needed: a) electric field, b) ionospheric conductivity.

• In 2006, the Swarm project was in Phase B, ending with the PDR (Preliminary Design Review) in the summer 2007.

The construction of the Swarm constellation commenced in November 2007 with the Phase C/D kick-off meeting. The Swarm project CDR (Critical Design Review) took place on Oct. 14, 2008 at ESA/ESTEC. 29)

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Figure 6: Schematic view of Earth's magnetic field (image credit: ESA/ATG Medialab) 30)

Legend to Figure 6: The magnetic field and electric currents near Earth generate complex forces that have immeasurable impact on our everyday lives. Although we know that the magnetic field originates from several sources, exactly how it is generated and why it changes is not yet fully understood. ESA's Swarm mission will help untangle the complexities of the field.



 

Space segment concept:

The Swarm mission architecture is driven by the requirement for separation of the various sources contributing to the Earth's magnetic field. Hence, the space segment concept employs a three-minisatellite constellation with the following characteristics:

- Three spacecraft in two different orbital planes, with two satellites in a plane of 84.7º inclination and with one satellite in a plane of 88º inclination

- The two satellites in the 87.4º inclination orbit will fly at a mean altitude of 450 km, their east-west separation will be 1-1.5º, and the maximum differential delay in orbit will be about 10 s.

- The satellite in the higher inclination orbit (88º) will fly at a mean altitude of 530 km.

- The spacecraft require some degree of active orbit maintenance to control the relative positions in the constellation (this is an element of formation flight to support flight operations). 31) 32)

In November 2005, ESA selected EADS Astrium GmbH, Friedrichshafen, Germany as the prime contractor for the Swarm spacecrafts. The Swarm consortium (main subcontractors) consists of: 33)

- EADS Astrium Ltd., UK (mechanical, thermal, AIV)

- GFZ Potsdam, Germany (end-to-end system simulator, calibration & validation)

- DTU Space, Copenhagen, Denmark [level 1b processor and instruments (VFM magnetometer and STR star tracker)]

The spacecraft design is governed by the following requirements:

1) Magnetic cleanliness: magnetometers on deployable boom, non-magnetic materials and caution during handling

2) Magnetic field vector attitude knowledge: ultra-stable connection between VFM (Vector Field Magnetometer) and STR (Star Tracker) assembly on the optical bench

3) Ballistic coefficient: small ram surface in flight direction to minimize air drag

4) Accelerometer proof-mass vs satellite CoG (Center of Gravity) location.

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Figure 7: Artist's rendition of the Swarm constellation (image credit: ESA)

An important design measure is the accommodation of the magnetometer package at a distance from the main body/platform sufficient to minimize any magnetic disturbance. A boom ensures a magnetically 'clean' environment and provides very stable accommodation for the magnetometer package. Due to envelope constraints of the launcher fairing, the boom must be deployable. 34)

Optical bench: The vector magnetometer is mounted on an ultra-stable silicon carbide-carbon fiber compound structure (the SWARM optical bench). Both optical bench and scalar magnetometer are installed on a deployable conical tube of square cross section. The position tolerance of the optical bench to its tube interface has to be fixed within 0.2 mm. 35) 36)

The design driver of the composite tube assembly of Swarm is thermal stability. The main cause for observed thermal distortion is the non-uniformity of the cross-sections arising from the different adaptations of the filament winding process in order to manufacture the carbon fiber reinforced structure. The manufacture of the structure required use of thermally controlled high precision bonding jigs to join the composite tubes to the metallic fittings.

The scalar magnetometer and optical bench are fixed to a deployable large beam of square cross section, the SWARM (Carbon-fiber Tube Assembly (CTA) which fulfils the following main functions (Figure 8):

• Separate the sensitive instruments from the spacecraft to comply with the very high magnetic cleanliness requirements

• Provide a suitable stable structure for the fixation of instruments.

The chosen manufacturing technology for the SWARM tube was filament winding. The SWARM tube has a conical taper. Since the amount of fibers in a cross section is constant the tube had two main characteristics: the wall thickness increased linearly from the root to the tip and due to nature of the winding process the fiber angle became steeper at the tip than at the root. The overall effect is a variation of properties along the length of the tube.

The Swarm carbon-fiber tube assembly was subjected to various tests: Thermal distortion was measured by establishing a 65ºC gradient between the tip and the hinge and a 10ºC gradient between opposite sides of the CTA. The hole pattern of the optical bench was accurate to within 0.2 mm (Ref. 35).

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Figure 8: The Swarm optical bench, carbon-fiber tube assembly (image credit: RUAG)

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Figure 9: Configuration and performance requirements of a Swarm spacecraft (image credit: EADS Astrium)

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Figure 10: Configuration details of a Swarm spacecraft (image credit: EADS Astrium)

The three identical Swarm minisatellites consist of the payload and the platform elements. The platform comprises the following subsystems: structure/mechanisms, power, RF communications, AOCS (Attitude and Orbit Control Subsystem), thermal control, and onboard data handling.

The AOCS design is based to a maximum extent on the CryoSat AOCS design of EADS Astrium. The gyro-less AOCS provides 3-axis stabilization with an Earth pointing attitude control in all modes. The requirements call for: 37)

- An attitude pointing control within a band of < 5º about all axis (roll, pitch, and yaw), the pointing stability is < 0.1º/s

- Provision of a sufficient torque capability for launcher tip-off rate damping and attitude acquisition

- Minimize acceleration and magnetic stray field disturbances to scientific instruments

- Provision of a high ΔV capability for orbit & attitude control maneuvers.

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Figure 11: Functional architecture of AOCS (image credit: EADS Astrium)

The AOCS is tightly coupled with the propulsion subsystem. Actuation is provided by a cold gas propulsion subsystem, referred to as OCS (Orbit Control Subsystem), and magnetic torquers (used for ΔV maneuvers and to complement the magnetic torquers). The cold gas propulsion system is provided by AMPAC-ISP, UK. - Attitude sensing is provided by a star tracker assembly (3 star tracker heads), 3 magnetometers, and a CESS (Coarse Earth and Sun Sensor) assembly used in safe mode situations and in initial acquisition sequences, respectively (CESS is of CHAMP, GRACE, and TerraSAR-X heritage). A dual frequency GPS receiver (GPSR) is used to provide PPS (Precise Positioning Service) to the OBC and instruments for on-board datation.

Note: the star tracker (STR) assembly and optical bench are described below under a separate heading.

The nominal attitude has a nadir orientation. Rotation maneuvers of S/C about roll, pitch and yaw are used for instrument calibration and orbit Control. The safe mode is Earth-oriented. Pointing requirements are 2º about all axes, with limitations on use of actuators.

The Swarm rate damping design, in support of the critical spacecraft deployment phase, employs magnetic rate damping - magnetometers in combination with magnetic torquers and thrusters - to provide a significantly cheaper implementation than with the use of gyroscopes. From a control theory point-of-view, rate damping with magnetometers using 2-axis measurement is as "safe" as with gyroscopes using 3-axis measurement: Global asymptotical stability is achieved except for the case when the magnetic field does not change. This is only in near-equator orbits possible with perfect field symmetry which is in practice not realistic. The result is confirmed by the evaluation of the observability criterion where no loss of this property could be detected except for the mentioned case. Since SWARM is in a polar inclination orbit, the control concept is considered "clean". 38)

Rate damping design: The RDM controller is a simple proportional controller on the S/C rate with reference rate zero. The S/C rate is computed by processing and derivation of the FGM measurements. The controller outputs the torque commands for the torquer and the thruster. A dead band for the thruster inhibits the thruster activation for low rates which can be covered by the torque rod.

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Figure 12: Schematic of the Swarm RDM controller (image credit: EADS Astrium)

 

Each spacecraft features 2 propellant tanks, each with a capacity of 30 kg of N2. The thrusters provide thrust levels of 20 and 40 mN. The cold gas thruster system was developed and space qualified by Ampec-ISP, Cheltenham, UK consisting of 24 OCT (Orbit Control Trusters) and 48 ACT (Attitude Control Thrusters) for the Swarm constellation. The assembly and test of Ampac's SVT01 series of cold gas thrusters has included design modifications, full qualification and verification of suitability to operate with a new propellant. In 2010, a set of 72 units has been supplied and integrated into the constellation of three Swarm spacecraft. 39)

A GPS receiver provides the functions of timing and position determination. The spacecraft dry mass is about 370 kg.

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Figure 13: Software architecture of AOCS (image credit: EADS Astrium)

EPS (Electrical Power Subsystem): The two body-mounted solar arrays and the varying orbits of the satellites require a MPPT (Maximum Power Point Tracking) system. Important requirements are related to the magnetic cleanliness of the satellites and result in following specific PCDU (Power Conditioning and Distribution Unit) design requirements: 40)

- Minimization of magnetic moment i.e. minimizing of magnetic materials and current loops

- Selection of switching frequencies outside the ‘forbidden' frequency ranges

- Minimizing spacecraft surface charging by use of negative bus voltage concept (battery + is connected to spacecraft structure).

The PCU part of the PCDU covers all tasks to control the power flow in the unit from the different sources and performs the communication with the OBC (On Board Computer).
During eclipse and battery recharge mode, the bus voltage varies with the state of charge of the battery. In taper charge mode, the bus is controlled by the MEA (Main Error Amplifier) to a predefined (commandable) value.

The main power requirements for the PCDU are defined as follows:

- Solar array input: 0 to -125 V, max. 21 A (each of 2 panels)

- Maximum power per panel: 750 W

- Main bus voltage range -22 V to -34 V

- Maximum battery charge current 24 A

- Continuous discharge current 0 to 14 A.

Maximum discharge current/power up to 0.5 h: 20 A / 440 W.

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Figure 14: Architecture of the PCDU (image credit: EADS Astrium)

Negative bus voltage concept: The Swarm satellite requires the positive line of the power system connected to structure. This implies that all bus protection functions have to be allocated in the ‘hot' negative line. As all essential functions, ( i.e. bus voltage control) need to be independent from the auxiliary supplies, they have to be supplied by the negative bus voltage. Figure 15 shows a principle grounding/power supply diagram of the main functional blocks in the PCDU.

Power control concept: The PCDU uses a simple concept for control of the battery state of charge and the bus voltage:

- Whenever the bus voltage and the charge current are below the limits, the MPPTs are active

- When the either the bus voltage attains the ‘battery end-of-charge voltage or the battery attains the charge current limit, the MEA (Main Error Amplifier) supersedes the tracker operation.

A bus overvoltage detection logic has been implemented in the PCDU, which performs a rapid ramp-down of the solar regulator current by using hysteresis control.

The MEA is composed of 3 identical separated control stages and a majority voter. Each control stage has a dedicated set of sensors and receives the relevant set commands for the bus voltage via redundant internal control busses. The charge current limitation is implemented in a ‘cascade configuration', using the output of the current error amplifier as a set signal for the voltage amplifier. This assures a low and constant bus impedance during all MEA control modes. The implementation of the regulation concept is given in Figure 16.

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Figure 15: Grounding scheme of the Swarm PCDU (image credit: EADS Astrium)

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Figure 16: Schematic of the bus control concept (image credit: EADS Astrium)

Spacecraft mass

Dry mass of ~369 kg
Cold gas propellant: 99 kg of CF4 (Freon)
Total mass = 468 kg

Spacecraft dimensions

Length: 9.1 m; width: 1.5 m (S/C body); height: 0.85 m; ram surface: ~0.7 m2

Boom length

5.1 m

AOCS

- 3-axis stabilized; magnetometers; CESS; GPS; STR, magnetorquers; thrusters
- 3D position better than 20 m (3σ)
- 3D velocity better than 1 m/s (3σ)
- UTC time with respect to GPS system time
- Datation of PPS signal better than 0.5 µs (3σ)

AOCS sensors


AOCS actuators

- STR (Star Tracker) with 3 sensor heads
- 1 CESS (Coarse Earth & Sun Sensor) with 6 heads placed orthogonal on the S/C
and 3 Magnetometers (FGM) which can be used for rates up to 0.5º/s.
- 3 MTQ (Magnetic Torquer), each 10 Am2
- 24 Cold Gas Thruster (THR), of which 2 x 8 for attitude control in all 3 axes, each 20 mN
force and 2 x 4 for orbit control, placed in -x and +y direction, each 50 mN force
- MTQs and THRs are used by each control mode

AOCS control modes

- Rate damping: rates are measured by the FGMs, main actuation by THR
- Coarse pointing: power and thermal safe Earth pointing attitude using CESS
- Fine pointing: STR and GPSR are used for attitude and position knowledge
- Orbit Control: similar to FPM, additionally performing slews for instrument calibration
and for orbit change and maintenance which requires using orbit control thruster.

EPS (Electrical Power Subsystem)

Total power: 608 W nominal; solar cells: GaAs triple junction; solar panel positive grounding; a set of batteries: Li-ion with a capacity of 48 Ah

RF communications

S-band; downlink data rate: 6 Mbit/s; 4 kbit/s uplink, data volume: 1.8 Gbit/day; 1 dump/day to Kiruna ground station, data storage capability: 2 x 16 Gbit

Mission duration

3 months of commissioning followed by 4 years of nominal operations

Table 1: Overview of spacecraft parameters

RF communications: S-band for TT&C spacecraft monitoring services and for science data transmission.

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Figure 17: Artist's rendition of the Swarm constellation in orbit (image credit: EADS Astrium)

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Figure 18: Photo of the three Swarm satellites at the launch site (image credit: ESA)

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Figure 19: The Swarm satellites separated by a few centimeters (image credit: ESA, M. Shafiq)

Legend to Figure 19: Attached to the tailor-made launch adapter, the three Swarm satellites sit just centimeters apart. This novel part of the rocket keeps the satellites upright within the fairing during launch and allows them to be injected simultaneously into orbit. 41)

DBA (Deployable Boom Assembly): The Swarm DBA, consisting of a 4.3m long CFRP tube and a hinge assembly, is designed to perform this function by deploying the CFRP tube plus the instruments mounted on it. mounted on a 4.3m long deployable boom. Deployment is initiated by releasing 3 HDRMs (Hold Down Release Mechanisms) , once released the boom oscillates back and forth on a pair of pivots, similar to a restaurant kitchen door hinge, for around 120 seconds before coming to rest on 3 kinematic mounts which are used to provide an accurate reference location in the deployed position. The motion of the boom is damped through a combination of friction, spring hysteresis and flexing of the 120+ cables crossing the hinge. Considerable development work and accurate numerical modelling of the hinge motion was required to predict performance across a wide temperature range and ensure that during the 1st overshoot the boom did not damage itself, the harness or the spacecraft. - Due to the magnetic cleanliness requirements of the spacecraft, no magnetic materials could be used in the design of the hardware. 42)


Launch: The Swarm constellation was launched on Nov. 22, 2013 (12:02:29 UTC) on a Rockot vehicle from the Plesetsk Cosmodrome, Russia. The launch was provided by Eurockot Launch Services. Some 91 minutes after liftoff, the Breeze-KM upper stage released the three satellites into a near-polar circular orbit at an altitude of 490 km. 43) 44) 45) 46) 47)

The launch was planned for the fall of 2012, but due to the recent Breeze-M (Briz-M) failure the launch was postponed to permit proper investigations of the cause. In Nov. 2012, ESA is still expecting, from the Russian Ministry of Defence, the launch manifest for the year 2012/13 for Rockot launchers indicating the launch date for Swarm. 48) 49)

Note: Rockot, a converted SS-19 ballistic missile, has been grounded since February 1, 2011 when the Rockot vehicle with the Breeze-KM upper stage failed to place the Russian government's GEO-IK2 geodesy satellite of 1400 kg (Kosmos 2470) into its intended orbit of 1000 km. However, in the meantime, the Rockot/Breeze-KM vehicle demonstrated its reliability by lifting 4 Russian spacecraft (Gonets-M No.3, Gonets-M No.4, Strela-3/Rodnik, and Yubileiny-2/MiR) successfully into orbit on July 28, 2012.

On April 9, 2010, ESA awarded a contract to Eurockot, for the launch of two of its Earth observation missions. The contract covers the launch of ESA's Swarm magnetic-field mission and a 'ticket' for one other mission, yet to be decided. Both will take place from the Plesetsk Cosmodrome in northern Russia using a Rockot/Breeze-KM launcher. Eurockot is based in Bremen, Germany and is a joint venture between Astrium and the Khrunichev Space Center, Moscow. 50) 51) 52) 53)

After release from a single launcher, a side-by-side flying lower pair of satellites at an initial altitude of 460 km and a single higher satellite at 530 km will form the Swarm constellation. The constellation deployment and maintenance require a total ΔV effort of about 100 m/s.

In LEOP (Launch and Early Orbit Phase), at least three ground stations will be involved. LEOP is expected to last 3 days for the full activation of the satellites, followed by an orbit acquisition phase of up to three months. In parallel with the orbit acquisition phase, the commissioning phase will start in order to check out all satellite subsystems and the payload. The commissioning phase is currently expected to last three months. After the commissioning phase the nominal mission phase of 4 year starts.



 

Orbits of the Swarm constellation:

Accurate determination and separation of the large-scale magnetospheric field, which is essential for better separation of core and lithospheric fields, and for induction studies, requires that the orbital planes of the spacecraft are separated by 3 to 9 hours in local time. For improving the resolution of lithospheric magnetization mapping, the satellites should fly at low altitudes - thus experiencing some drag, but commensurate with the goals of a multi-year mission lifetime. The three satellites are being flown in 3 orbital planes with 2 different near-polar inclinations to provide a mutual orbital drift over time (Figure 20 and 21).

• Two satellites (Swarm A+B) are in a similar plane of 87.4º inclination. The satellite pair of 87.4º inclination will fly at a mean altitude of 450 km, their east-west separation shall be 1-1.4º, and the maximal differential delay in orbit shall be about 10 s. The formation-flying aspects concern the satellite pair, a side-by-side formation, requiring some formation maintenance.

• One higher orbit satellite (Swarm C) in a circular orbit with 88º inclination at an initial altitude of 530 km. The right ascension of the ascending node is drifting somewhat slower than the two other satellites, thus building up a difference of 9 hours in local time after 4 years.

Note: Due to ASM instrument problems on Swarm-C (Charlie), it was decided prior to launch to place Charlie with Alpha on the lower orbit, and Bravo on the higher orbit.

Parameter

Swarm-A (Alpha)

Swarm-C (Charlie)

Swarm-B (Bravo)

Orbital altitude

≤ 460 km (initial altitude of satellite pair)

≤ 530 km

Orbital inclination

87.4º

88º

ΔRAAN (Right Ascension of Ascending Node)

1.4º difference between A and B

~0-135º difference
wrt mean plane of A/B
(continuous drift)

Mean anomaly at epoch

Δt = 2-10 s difference between A and B

N/A

LTAN evolution (Figure 20, right-hand side)

24 hours of local time coverage every 7-10 months
9 hours of separation between lower pair and upper satellite at end of life

Table 2: Overview of the Swarm orbit configuration

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Figure 20: Orbit altitude projection over mission time (left); Local time evolution of the S/C in two orbital planes (right), image credit: DTU Space

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Figure 21: Equatorial projection of the Swarm orbit configuration over time (image credit: DTU Space) 54) 55)

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Figure 22: Polar projection of the Swarm orbit configuration over time (image credit: ESA)

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Figure 23: The Swarm tandem pair provides a stereo view (image credit: DTU Space)

 

Swarm mission orbit update information as of March 2017

The following 8 Figures (Figure 24 to 32), dealing with the Swarm constellation flight dynamics, were provided by Detlef Sieg of ESA. They were presented at the 4th Swarm Science Meeting & Geodetic Workshop in Banff, Canada. 56)

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Figure 24: Swarm mission orbit update as of March 2017 (image credit: ESA)

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Figure 25: LTAN evolution: Rotation of the orbital plane (image credit: ESA)

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Figure 26: Predicted Solar Activity: Solar radiative flux and geomagnetic activity, past and predicted (image credit: NASA/MSFC)

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Figure 27: Observed and Predicted Altitude Evolution (image credit: ESA)

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Figure 28: ΔLTAN A/C versus B (image credit: ESA)

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Figure 29: Lower pair satellites, along track separation (image credit: ESA)

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Figure 30: Lower pair satellites, semi major axis difference (image credit: ESA)

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Figure 31: Fuel consumption of the Swarm constellation (image credit: ESA)

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Figure 32: Orbit change fuel cost of the Swarm constellation (image credit: ESA)