Minimize BRITE Austria

BRITE (BRIght-star Target Explorer) Constellation / BRITE Austria, UniBRITE

BRITE (BRIght-star Target Explorer) / CanX-3 (Canadian Advanced Nanosatellite eXperiment-3) is a low-cost Austrian/Canadian constellation of nanosatellites - a collaborative science demonstration mission of the University of Toronto, Institute for Aerospace Studies/Space Flight Laboratory (UTIAS/SFL), the Graz University of Technology (TU Graz), and the Institute of Astronomy at the University of Vienna, both of Austria, with Sinclair Interplanetary, and Ceravolo Optical Systems Ltd., Ontario, as subcontractors. 1) 2) 3) 4) 5) 6) 7) 8) 9)

The objective is to make photometric observations of some of the apparently brightest stars in the sky and to examine these stars for variability (low-level oscillations and temperature variations). The observations will have a precision at least 10 times better than achievable using ground-based observations; the paylaod will be packaged inside a CanX-class nanosatellite (CanX-3). The mission's science team includes collaborators from Canada and Austria: the University of British Columbia (UBC), l'Université de Montréal, the University of Toronto, and the University of Vienna (Universität Wien).

The BRITE constellation aims to be a modest sized instrument operating in low Earth orbit, above the effects of the atmosphere, capable of fulfilling the science objectives. It consists of a maximum of two nanosatellites, each equipped with a small-lens telescope, able to observe the brightest stars in the sky to visual magnitude 3.5, over a FOV of 24º, with a sampling time of up to 15 minutes once per satellite orbit (typically 100 minutes), and with a differential brightness measurement accurate to at least 0.1% per sample (all numbers are minimum requirements; actual performance may be better). A cluster of four satellites is needed to improve the duty cycle and would obtain color information (with two satellites having blue and two having red filters).

Science requirement

Minimum requirement

Visual magnitude limit

+ 3.5

Positional constraints

None except for Sun, Earth, and Moon exclusion zones

FOV (Field of View)

24º diameter

Differential photometry error/single observation

< 0.1%

Error of amplitude spectrum for > month

< 2x10-5 (20 ppm)

Cadence (repeat of the same field)

< 100 minutes

Duration of the mission

> 2 years

Table 1: Science requirements for a bright star photometry mission

Selection of a constellation: There are many reasons for using a constellation of nanosatellites over a single satellite. For one, each telescope will be optimized to work with only one color filter. By collecting color and intensity data from at least two different BRITE satellites, each with a different filter, the science capacity of BRITE is greatly enhanced. Color provides temperature information that helps astronomers to better identify modes of oscillation.

The BRITE telescope is being designed to have no moving parts (low cost amd risk mitigation). This implies that filter changes cannot be done by using one BRITE telescope in orbit. In having two nanosatellites in the same orbit, each with a different filter, the development costs can be minimized by keeping each BRITE satellite identical except for the telescope and by reducing nonrecurring engineering costs.

Another reason to have a constellation of nanosatellites is that multiple satellites observing the same region of interest can increase the overall duty cycle of observation beyond what a single nanosatellite can provide. Since the stars of interest are located in all parts of the sky, a continuous viewing zone for all targets of interest is not possible. - Having two pairs of BRITE satellites in two slightly different orbits that have different viewing times for the same region of interest doubles the duty cycle and significantly improves the spectral window.

A final reason for using a constellation of nanosatellites is the mitigation of risk. By having multiple, low cost satellites instead of a single large satellite, the associated launch risk is greatly reduced. Additionally, the failure of any single BRITE satellite would not end the mission and the other satellites in the BRITE-Constellation would still achieve all the primary science objectives (Ref 3).

The primary satellite design requirement calls for attitude control. The strict photometric error-tolerance places a high precision requirement on the ADCS system to ensure BRITE will always keep regions of interest surrounding each star within the same pixel areas on the imager.

Mission requirement

Minimum requirement

Field of acquisition

< 30 arcminutes

Field re-acquisition accuracy

1.5 arcminutes

Attitude error during observation

1.6 arcmin over 15 minutes

Data transfer/day

> 180 kB

Onboard memory storage

> 360 kB

Window of observation per orbit

> 15 minutes

Detector temperature

< 20ºC

Table 2: Minimum mission requirements for the BRITE-Constellation platform (Ref. 3)

The BRITE constellation will be the world‘s first nanosatellite constellation dedicated to an astronomy mission.

 


 

Extension of the Nanosatellite Constellation:

In 2011, the BRITE constellation consists of a group of six nanosatellites with the following participants of the BRITE consortium: 10) 11)

1) The University of Vienna and FFG/ALR (Austria’s space agency) are financing the development of two BRITE satellites and development is nearing completion.

2) SRC/PAS (Space Research Center/ Polish Academy of Sciences of Warsaw, Poland will be preparing two additional satellites. The first Polish satellite, BRITE -PL 1, will be a modified version of the original SFL design. The second Polish satellite, BRITE-PL 2, will include the significant changes to be implemented by SRC PAS.

The Polish technical participation in the BRITE project is supported by the Ministry of Science and High Education. The participation in the BRITE consortium gives Poland the possibility to launch its first Polish scientific satellite into space. The Polish participation in the BRITE consortium was established in October 2009 by SRC/PAS and NCAC/PAS (Nicolaus Copernicus Astronomical Center/ Polish Academy of Sciences). 12)

3) The CSA (Canadian Space Agency) is also funding two satellites in the constellation. In January 2011, CSA signed an agreement to support the BRITE constellation by contributing two satellites targeting a launch in 2012. The two Canadian satellites will join the four other satellites funded by the Austrian and Polish governments. 13)

The operation of three pairs of BRITE nanosats will significantly improve the coverage of the parameter space addressed in this proposal (compared to only one BRITE), and in particular the statistical significance of the science conclusions to be drawn. The best configuration would be to have two launches, each with a pair of BRITE nanosats with each kind of filter, and each orbit pair separated in the sky as much as possible. This is the rationale behind the BRITE constellation of four individual satellites.

Each BRITE satellite utilizes a number of innovative technologies including miniature reaction wheels, star tracker and optical telescope, all sized and designed around the generic CanX (Canadian Advanced Nanosatellite Experiment) bus of UTIAS/SFL (University of Toronto, Institute for Aerospace Studies/Space Flight Laboratory).

For a better overview of the BRITE constellation, the eoPortal will create a separate file for the spacecraft of each consortium participant when the information becomes available — with this file being the description of the BRITE Austria constellation.

The initial BRITE constellation is based on pioneering Canadian space technology, built in partnership (joint venture) with Austrian institutions. The Austrian share of the project (BRITE-Austria and UniBRITE) is funded by the Austrian Space Program - representing the first Austrian satellites.

• The University of Vienna (Austria) has funded UTIAS/SFL to build one satellite, called UniBRITE.

• The Graz University of Technology (TU Graz) is also cooperating with UTIAS/SFL to produce a further nanosatellite of the constellation, called BRITE-Austria, funded by FFG/ALR.

Each of these two BRITE satellites will have a different filter, one will be equipped with a 390-460 nm (blue-spectrum) bandpass filter and the other will be equipped with a 550-700 nm (red spectrum) bandpass filter.

Country

No of Satellites

Nanosatellite Designation

Austria

2

TUGSAT-1/BRITE-Austria & UniBRITE

Poland

2

BRITE-PL1 (LEM) & BRITE-PL2

Canada

2

BRITE/CanX-3A & BRITE/CanX-3B

Table 3: BRITE constellation consisting of 6 nanosatellites operating in pairs, all are based on GNB of UTIAS/SFL

 

 

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Figure 1: Artist's rendition of the BRITE-Austria nanosatellite in orbit (image credit: TU Graz) 14)

Spacecraft:

All spacecraft in the constellation use the GNB (Generic Nanosatellite Bus) platform, also referred to as CanX-3, developed at UTIAS/SFL (of CanX-2 heritage). The first BRITE satellite, UniBRITE, is being built by SFL for the University of Vienna. The second BRITE satellite, BRITE-Austria, is being developed by the Graz University of Technology with assistance (components) from SFL. The BRITE team has asked the Canadian Space Agency (CSA) to complete the BRITE constellation with funding for two Canadian BRITE nanosatellites.

Note: The Graz University of Technology, abbreviated as TUG, refers to its BRITE-Austria nanosatellite also as TUGSat-1. 15) 16)

The GNB is a modular spacecraft bus designed around a 20 cm x 20 cm x 20 cm cube form factor that provides all basic functional capabilities for a wide range of nanosatellite missions (up to 12 kg and potentially bigger), and provides a platform for state-of-the-art, high-performance applications not previously achievable with nanosatellites. A typical GNB consists of one ARM7 housekeeping computer, two ARM7 computers for attitude/propulsion control and payload operations, CMOS imagers, a power system with triple-junction solar cells and Lithium-ion batteries, passive thermal control, UHF uplink, a 32-256 kbit/s S-band downlink, and a 1 arcmin three-axis attitude control system consisting of tiny reaction wheels, sun sensors, magnetometer and star tracker. 17) 18)

EPS (Electrical Power Subsystem): The GNB design incorporates a direct energy-transfer power system utilizing between four and eight solar cells on each face and battery storage to supply 10 W peak and 5.6 W nominal for the satellite.

Each BRITE nanosatellite contains three processor boards, the OBC board handles the housekeeping and communications, a second computer is used for all ADCS support functions, while the third board is used for the science payload and its data handling. Communications between the boards occurs through serial peripheral interfaces. Each processor board is based around an ARM7TDMI processor with a code memory of 256 kB and triple-vote 2 MB of hardware EDAC (Error Detection And Correction) protected SRAM memory to store program variables and data. Longer term payload data storage is provided in 256 MB of flash memory. The on-board computer uses a multi-threaded operating system developed at SFL.

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Figure 2: Illustration of the CanX-3/BRITE spacecraft (image credit: UTIAS/SFL)

ADCS (Attitude Determination and Control Subsystem). The spacecraft is 3-axis stabilized with 1 arcmin stability. The altitude control software implements an Extended Kalman Filter that uses the various attitude sensors to predict and correct the attitude of the spacecraft.

The attitude sensor suite in each GNB spacecraft comprises of a three-axis magnetometer, six sun sensors (each consists of a phototransistor and digital pixel arrays for coarse and fine attitude determination), and a star tracker. Three magnetorquers are employed to provide coarse attitude control and momentum dumping capability. Three orthogonal reaction wheels perform fine attitude controls.

A reaction wheel for nanosatellites was developed by Sinclair Interplanetary of Toronto in collaboration with SFL. The wheel fits within a box of 5 cm x 5 cm x 4 cm, has a mass of 185 g, and consumes only 100 mW of power at nominal speed. A max torque of 2 mNm is provided (30 mNms momentum capacity). No pressurized enclosure is required, and the motor is custom made in one piece with the flywheel. The reaction wheel technology is scalable. CanX-3/BRITE is the first mission to use this actuator (3 wheels). 19) 20)

UniBRITE and BRITE-Austria use the ComTech/AeroAstro MST (Miniature Star Tracker) as their primary attitude sensor for attitude determination. The update rate of the MST limits the cadence of the attitude determination and control cycle to 0.5 Hz. This slow cadence has a significant impact on the overall attitude performance, but this can be mitigated through the use of high bandwidth attitude filter and controller. 21)

The attitude subsystem of the BRITE satellites is among the most critical spacecraft systems in ensuring mission success. For massive stars, the period of light variations are on the scale of hours to months, therefore the satellites will perform 15 minute observations of multiple target star fields each orbit. Upon returning to a previously imaged target, the attitude system is required to hold the point-spread-function of the imaged stars to within 3 pixels of the original point locations, in order to trim out the pixel-to-pixel variations of the telescope detector. This stringent requirement implies a one arc-minute pointing control with long duration attitude stability and rapid reacquisition. Until recent advances in the miniaturization of attitude hardware, these requirements were insurmountable on a nanosatellite scale. Despite these advancements, a major challenge for the BRITE satellites was to characterize and tune these attitude components (reaction wheels and star trackers, in particular), as they operate at the edge of the required performance envelope. Further, novel attitude estimation and control techniques were applied, which were essential, given both the hardware compliment and their limitations (Ref. 21).

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Figure 3: Photo of the MST Star Tracker (image credit: TU Graz)

Reaction wheels: The BRITE satellites make use of the Sinclair-SFL 30 mNms reaction wheels. These highly capable reaction wheels have over five years of flight heritage onboard the CanX-2 satellite, and an additional three year of heritage aboard the AISSat-1 satellite and continue to operate without incident. The reaction wheels are capable of storing more than 30 mNms of angular momentum and delivering torques up to 2 mNm.

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Figure 4: Photo of three GNB miniature reaction wheels (image credit: Sinclair Interplanetary)

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Figure 5: Photo of the magnetometer (image credit: TU Graz)

RF communications: Each CanX-3/BRITE nanosatellite is capable of full duplex communications with the ground. The uplink uses UHF while an S-band transmitter with BPSK modulation is used in the downlink. Each satellite can also support a VHF beacon. The expected data volume is 2-8 MB/day.

Spacecraft mass, volume, total power

6.5 kg, 20 cm x 20 cm x 20 cm, 5.4-11 W (6 W average)

Bus voltage

4.0 V (nominal, unregulated)

Solar cells

Triple junction solar cells (face mounted)

Battery type, capacity

Li-ion, 5.3 Ah

Attitude determination

10 arcsec

Attitude control accuracy, stability

< 1.0º, 1 arcmin rms (or FWHM of ~2.2 arcmin)

Onboard payload data storage

Up to 256 MByte

RF communications
Downlink (S-band) data rate
Uplink (UHF) data rate
Data volume/day
S-band frequency
UHF-band frequency
VHF beacon
Transmit power


32 to 256 kbit/s
up to 4 kbit/s
2 MByte (typical)
2234.4 MHz
437.365 MHz
145.89 MHz
0.5 W (S-band downlink), 0.1 W (VHF beacon)

Mission duration

2 years (min)

Table 4: Summary of the CanX-3 / BRITE-Austria / TUGSat-1 spacecraft bus specifications

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Figure 6: Block diagram of the BRITE/CanX-3 nanosatellite (image credit: UTIAS/SFL, TU Graz)

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Figure 7: Exploded view of the CanX-3 nanosatellite showing the structural elements (image credit: UTIAS/SFL, TU Graz)

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Figure 8: Photo of the TUGSat-1 / BRITE-Austria nanosatellite (image credit: TU Graz)

 

Launch: The first two nanosatellites of the BRITE/CanX-3 constellation [Austrian mission: BRITE-Austria (CanX-3B) and UniBRITE (CanX-3A) were launched as secondary payloads on Feb. 25, 2013 on the PSLV-C20 vehicle of ISRO/Antrix from Shriharikota/India. The primary payload on this mission was SARAL (Satellite with Argos and AltiKa), a collaborative mission of ISRO and CNES. 22) 23) 24)

To facilitate rapid launches, SFL has adopted an approach to build customizable separation systems for any nanosatellite. These separation systems can be integrated with the satellites prior to launch site delivery and hence, make launch coordination easier. The SFL XPOD (Experimental Push Out Deployer) separation system interfaces the GNB-based spacecraft to practically any launch vehicle. Spacecraft up to 12 kg may be accommodated in existing XPOD designs.

UTIAS/SFL refers to the XPOD launch of the nanosatellites as NLS-8 (Nanosatellite Launch Service-8). UniBRITE (NLS-8.1), BRITE-Austria (NLS-8.2) and AAUSAT3 (NLS-8.3).

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Figure 9: Illustration of the nanosatellite (GNB) separation system (XPOD Duo), image credit: UTIAS/SFL

The six secondary payloads manifested on this flight were:

• Sapphire (Space Surveillance Mission of Canada), a minisatellite with a mass of 148 kg.

• NEOSSat (Near-Earth Object Surveillance Satellite), a microsatellite of Canada with a mass of 74 kg.

• BRITE-Austria/TUGSat-1 (Graz University of Technology), Austria, a nanosatellite with a mass of ~6.5 kg.

• UniBRITE (Technical University of Vienna), Austria, a nanosatellite with a mass of ~ 6.5 kg.

• AAUSat-3 (Aalborg University CubeSat-3), a student-developed nanosatellite (1U CubeSat) of AAU, Aalborg, Denmark. The project is sponsored by DaMSA (Danish Maritime Safety Organization).

• STRaND-1 (Surrey Training, Research and Nanosatellite Demonstrator), a 3U CubeSat (nanosatellite) of SSTL (Surrey Satellite Technology Limited) and the USSC (University of Surrey Space Centre), Guildford, UK. STRaND-1 has a mass of ~ 4.3 kg.

Orbit: Sun-synchronous near-circular orbit, mean altitude = ~775 km, inclination = 98.6295º, orbital period of 100.32 minutes, LTAN (Local Time on Ascending Node) = 6:00 hours.

Note: SARAL (and also the BRITE constellation) will fly on the same orbit as Envisat, to ensure a continuity of altimetry observations in the long term. On the other hand, the local time of passage over the equator will be different due to specific cover requirements for the instruments constellation of the Argos system.

BRITE_AutoA

Figure 10: This image shows the various spacecraft on the PSLV-C20 upper stage (image credit: UTIAS/SFL, Ref. 24)

 


 

Mission status of TUGSat-1 (BRITE-Austria) and UniBRITE:

• Feb. 2014: The BRITE constellation is the world‘s first nanosatellite constellation dedicated to an astronomy mission. 25)

- The first 3 members of the BRITE constellation are on orbit, operating nominally

- The planned constellation will be completed this year

- Scientific & mission requirements fully met

- Scientific data collection under way.

• Activities in the period summer – fall 2013 (Ref. 25).

- Payload characterization (TUGSAT-1): Verification of PSF (Point Spread Function), CCD sensitivity, identifications of hot pixels on CCD (removal by software).

- Attitude control system optimization (UniBRITE)

- Reduction of commissioning time

- Fine pointing achieved in November 2013, performance better than specification

- Science data collection since November.

• October 1, 2013: Calibration of attitude sensors of BRITE-Austria is ongoing to increase the fine pointing performance. In addition payload characterization and hot pixel variations of the instrument's CCD sensor are investigated (Ref. 29).

Arc-minute level pointing with small satellites is a challenging but a demonstrated objective. This level of precision is made possible thanks to recent advancements in star tracker technology. The AeroAstro MST (Miniature Star Tracker) as well as other high performance sensors tailored to nanosatellites, are enabling fine determination for small satellite missions.

Another important technology enabling fine pointing of nanosatellites are reaction wheels. Jitter caused by torque output oscillation and to a lesser extent, rotor imbalance can cause significant pointing degradation. The Sinclair-SFL reaction wheels have been shown to produce very low amounts of jitter.

Small satellites are very susceptible to disturbance torques. With small moments of inertia, a given torque can cause significant angular disturbance. This susceptibility can be mitigated by the use of a high bandwidth state estimator and controller. It is also advisable to estimate the disturbances and apply the appropriate correction to the state estimator and controller a priori.

The first two BRITE constellation nanosatellites are currently on orbit, commissioned, and are now operationally tasked to carry out their science objectives. The novel, high-performance attitude subsystem design of the generic nanosatellite bus, of which the BRITE mission is based on, has proven to be successful in arc-minute level pointing.

Table 5: On-orbit attitude performance of a nanosatellite telescope (Ref. 21)

• In Sept. 2013, UniBRITE and BRITE-Austria have started to observe stars in the Orion constellation. While testing and optimization efforts are still ongoing science data are also collected regularly. In Figure 11, the exposure time was set to 1 second. The outer circle marks the unvignetted field of view of the instrument which has has a diameter of about 24º.

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Figure 11: UniBRITE full-frame image of the constellation Orion acquired on Sept. 24, 2013 (image credit: University of Vienna)

• In September 2013, the commissioning of BRITE-Austria is not yet completed, as the fine tuning and in-orbit calibration of sensor parameters, as well as performance characterization of the instrument is still ongoing. 26)

- Nevertheless, the ground station network and distributed software concept has already been used and validated. On the one hand, contacts to UniBRITE were successfully established from Graz, on the other hand during a breakdown of the ground station in Graz, the communication with BRITE-Austria was commanded through the ground station in Warsaw/Poland.

- Furthermore, during commissioning it was successfully shown, that the station in Graz is able to run autonomously and the remote access enables operators to monitor and control the ground station’s and satellite’s behavior although off-site.

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Figure 12: Ground coverage of BRITE-Austria for the ground station network (image credit: TU Graz)

• July 15, 2013: BRITE-Austria is currently performing the transition to fine pointing. The overall satellite is in a good health state and is looking forward to start observations of bright stars (Ref. 29).

• On March 28, 2013, the UniBRITE nanosatellite of the University of Vienna experienced a very close encounter with OSCAR-15 [aka UoSat-4, a microsatellite of SSTL which was launched on January 22, 1990 as a secondary payload to SPOT-2 of CNES from Kourou. OSCAR-15 experienced an on-board electronics failure shortly after launch, and is not operational anymore]. The UniBRITE project team experienced some anxious moments during the predicted close flyby of OSCAR-15. 27)

• March 23, 2013: After successful detumbling the TUGSat-1 spacecraft was put into coarse pointing mode. During the 404th orbit the first star image was taken by the scientific instrument (telescope) in coarse 3-axis pointing. The first star image showing Delta Corvus B9V (magnitude 2.95) was downloaded and analyzed by the experts from the Institute of Astrophysics in Vienna. Initial assessment of the payload performance indicates that the specifications are met. 28)

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Figure 13: Image of Delta Corvus B9V mag=2.95 (left); point spread function of the brightness distribution (right), image credit: TU Graz, University of Vienna (Ref. 25)

• March 5, 2013: TUGSAT-1 completed its 100th orbit. All subsystems tested so far show excellent health status. At present the attitude control system is checked out. Detumbling of the spacecraft is planned for the next days.

• A successful contact with the TUGSat-1 (BRITE-Austria) nanosatellite was established during the first orbital pass over Graz (3 hours after launch). This constituted the start of the commissioning phase of the satellite which is expected to last for 3 months. 29)

 


 

Sensor complement:

The objective is to examine the apparently brightest stars in the sky for variability using the technique of precise differential photometry in time scales of hours and more. The constellation of four nanosatellites is divided into two pairs, with each member of a pair having a different optical filter. The requirements call for observation of a region of interest by each nanosatellite in the constellation for up to 100 days or longer. 30)

Photometer:

The science payload of each nanosatellite consists of a five-lens telescope with an aperture of 30 mm and the interline transfer progressive scan CCD detector KAI 11002-M from Kodak with 11 M pixels, along with a baffle to reduce stray light. The optical elements are housed inside the optical cell and are held in place by spacers. The photometer has a resolution of 26.52 arcsec/pixel and a field-of-view of 24º. The mechanical design for the blue and for the red instrument is nearly identical; only the dimensions of the lenses are different (Ref. 6) and Ref. 7).

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Figure 14: Illustration of the BRITE telescope and baffle (image credit: UTIAS/SFL, TU Graz)

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Figure 15: The optics design of the photometer (image credit: UTIAS/SFL, Ceravolo)

The effective wavelength range of the instrument is limited in the red by the sensitivity of the detector and in the blue by the transmission properties of the glass used for the lenses. The filters were designed such that for a star of 10,000 K (average temperature for all BRITE target stars) both filters would generate the same amount of signal on the detector. The blue filter covers a wavelength range of 390-460 nm and the red filter 550-700 nm; both are assumed to have a maximum transmission of 95%.

Image size

37.25 mm x 25.70 mm

No of pixels

4008 x 2672

Pixel size

9.0 µm x 9.0 µm

Peak quantum efficiency

50%

Full well charge (saturation signal)

60,000 e-

Dark current (at 20ºC)
Readout current

4 e-/s/pixel
13 e-/pixel

Power consumption

1 W

Table 6: Characteristics of the Kodak KAI 11002-M CCD detector

The photometer instrument has a mass of ≤ 0.9 kg and a power consumption of ≤ 3.5 W. The instrument uses a custom set of electronics to operate the imager. The electronics include four A/D converters (14 bit) to convert the analog pixel values, and 32 MB of memory to temporarily hold a full frame image. The imager and memory timing and signals are being controlled using a CPLD (Complex Programmable Logic Device).

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Figure 16: Schematic layout of the CMOS detector array (image credit: University of Vienna)

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Figure 17: The BRITE photometer and star tracker (image credit: TU Graz)

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Figure 18: Photo of the CCD detector (image credit: TU Graz)

 


 

Ground segment of the BRITE constellation:

All participants in the BRITE constellation will have their own ground station. 31)

• Graz, Austria, TUG (Mission Control for BRITE-Austria and UniBRITE)

• TUV (Technical University Vienna), a second station is located at the ITC of TUV

• Toronto, Canada, UTIAS/SFL (Mission Control for BRITE/CanX-3). A ground station at UTIAS-SFL has already been established since early 2003. It has served as a technical template design and concept for two other ground stations (one in Vienna and one in Vancouver) which communicate with the MOST satellite. Furthermore, this station has been used now regularly for broadcasting with three other satellites in orbit. This well-proven, equipement is also the baseline for BRITE-Constellation ground-space communications. At UTIAS/SFL , an additional ground station will be installed in 2011 which will also support BRITE-Constellation operations.

• Warsaw, Poland (Mission Control for BRITE-PL). The ground station is located at the CAC (Nicolaus Copernicus Astrophysical Center) in Warsaw.

All stations will track and collect data from all BRITE nanosatellites.

• Distributed automatic ground station operations

• Science teams can retrieve verified raw data from servers.

Ground Station Network: For operating the BRITE constellation, a ground station network is used. The advantages of the network are the increased availability and redundancy (Ref. 32).

The general operations concept foresees that each master ground station is in charge of its own satellite(s) and tracks other satellites only in case of unavailability of the correspondent master station or in case of emergency.

The master station is responsible for its own satellite(s) and is the only one actually controlling the spacecraft. If other stations attempt contacting a satellite, they normally act as relay stations, up-linking incoming commands from the master station and forwarding downlinked data to the master station. In case of failure of a master station, its duties can be temporarily taken over by another station in the network.

An example of ground station network operations and data flow for BRITE-Austria is shown in Figure 19. While all stations can establish contact with the satellite, the entire data flow is handled by the Graz ground station as the satellite’s master station. The data flow is handled by a distributed ground software concept.

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Figure 19: BRITE ground station network and operations concept for the BRITE-Austria satellite (image credit: TU Graz)

 

BRITE-Austria ground station: A major driver for the ground station design is the amount of science data to be downloaded. For BRITE-Austria, the data amount to be downloaded is up to 10 MByte/day. The contact times with the satellite are limited to about 10-12 minutes/pass and a total contact time of roughly 1 hour/ day. A downlink data rate of 32 kbit/s allows to download the daily data in about 42 minutes, providing sufficient margins. 32)

In addition, the ground station in Graz serves as mission control for BRITE-Austria. It is responsible for the spacecraft and shall guarantee data integrity and storage of raw satellite data.

The ground station antennas are a 3 m parabolic meshed antenna for S-band (35 dBi gain) and an 18 element, circular polarized cross-Yagi antenna for UHF (16 dBi gain). Both antenna are mounted on the same tower and are controlled by the same azimuth and elevation rotators, allowing to achieve the same tracking performance for uplink and downlink.

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Figure 20: Block diagram of the BRITE-Austria ground (image credit:TU Graz)


1) A. F. J. Moffat, W. W. Weiss, S. M. Rucinski, R. E. Zee, M. H. van Kerkwijk, S. W. Mochnacki, J. M. Matthews, J. R. Percy, P. Ceravolo, C. C. Grant, “The Canadian BRITE NanoSatellite Mission,” Proceedings of ASTRO 2006 - 13th CASI (Canadian Aeronautics and Space Institute) Canadian Astronautics Conference, Montreal, Quebec, Canada, April 25-27, 2006, URL: http://www.utias-sfl.net/docs/brite-astro-2006.pdf

2) N. C. Deschamps, C. C. Grant, D. G. Foisy, R. E. Zee, A. F. J. Moffat, W. W. Weiss, ”The BRITE Space Telescope: A Nanosatellite Constellation for High-Precision Photometry of Bright Stars,” Proceedings of the 20th Annual AIAA/USU Conference on Small Satellites, Logan, UT, Aug. 14-17, 2006, paper: SSC06-X-1, URL: http://www.utias-sfl.net/docs/brite-ssc-2006.pdf

3) N. C. Deschamps, C. C. Grant, D. G. Foisy, R. E. Zee, A. F. J. Moffat, W. W. Weiss, ”The BRITE Space Telescope: Using a Nanosatellite Constellation to Measure Stellar Variability in the Most Luminous Stars,,” Proceedings of the 57th IAC/IAF/IAA (International Astronautical Congress), Valencia, Spain, Oct. 2-6, 2006, IAC-06-B5.2.7, URL: http://www.utias-sfl.net/docs/brite-iac-2006.pdf

4) O. Koudelka, G. Egger, B. Josseck, N. Deschamps, C. Grant, D. Foisy, R. Zee, W. Weiss, R. Kuschnig, A. Scholtz, W. Keim, “TUGSAT-1 / BRITE-Austria - The First Austrian Nanosatellite,” Proceedings of the 57th IAC/IAF/IAA (International Astronautical Congress), Valencia, Spain, Oct. 2-6, 2006, IAC-06-B5.2.06, URL: http://www.utias-sfl.net/docs/brite-iac-2006b.pdf

5) http://www.utias-sfl.net/nanosatellites/CanX3/

6) http://www.brite-constellation.at/

7) http://www.tugsat.tugraz.at/project/mission

8) O. Koudelka, G. Egger, B. Josseck, N. Deschamps, C. Grant, D. Foisy, R. Zee, W. Weiss, R. Kuschnig, A. Scholtz, W. Keim, “TUGSAT-1 / BRITE-Austria - The First Austrian Nanosatellite,” Acta Astronautica, Vol. 64, 2009, pp. 1144-1149

9) Otto F. Koudelka, “The BRITE Nanosatellite Constellation,” Proceedings of the 50th Session of Scientific & Technical Subcommittee of UNCOPUOS, Vienna, Austria, Feb. 11-22, 2013, URL: http://www.oosa.unvienna.org/pdf/pres/stsc2013/tech-61E.pdf

10) Piotr Orleanski, Rafa¿ Graczyk, Miros¿aw Rataj, Aleksander Schwarzenberg-Czerny, Tomasz Zawistowski, Robert E.Zee, “BRITE-PL – the first Polish scientific satellite,” Proceeding of the 4th Microwave & Radar Week, MRW-2010, Vilnius, Lithuania, June 14-18, 2010

11) Otto Koudelka, Werner Weiss, “BRITE-Austria, TUGSat-1,” UN/Austria/ESA Symposium on Small Satellite Programs for Sustainable Development: Payloads for Small Satellite Programs, Sept. 21-24, 2010, Graz, Austria

12) “The first Polish scientific satellite BRITE-PL will help in understanding the inner structure of brightest stars in our galaxy,” URL: http://www.sciencenewsline.com/space/2010052400006625.html

13) “Canada adds two satellites to BRITE Constellation,” January 19, 2011, URL: http://www.utias-sfl.net/RecentNews/news-20110119.html

14) Otto F. Koudelka, “The BRITE Nanosatellite Constellation,” Proceedings of the 49th Session of UNCOPUOS-STSC (UN Committee on the Peaceful Uses of Outer Space-Scientific and Technical Subcommittee), Vienna, Austria, Feb. 6-17, 2012, URL: http://www.oosa.unvienna.org/pdf/pres/stsc2012/tech-47E.pdf

15) http://www.tugsat.tugraz.at/tugsat-1

16) “Der erste österreichische Satellit - TUGSAT-1 / BRITE-Austria,” URL: http://www.tugsat.tugraz.at/info/press/press-release

17) F. M. Pranajaya, Robert E. Zee, “Generic Nanosatellite Bus for Responsive Mission,” 5th Responsive Space Conference, Los Angeles, CA, USA, April 23-26, 2007, AIAA-RS5 2007-5005, URL: http://www.responsivespace.com/.../5005P.pdf

18) Guy de Carufel, “Assembly, Integration and Thermal Testing of the Generic Nanosatellite Bus,” Thesis submitted for the degree of Master of Applied Science, University of Toronto, 2009, URL: https://tspace.library.utoronto.ca/bitstream/1807/18271/1/deCarufel_Guy_200911_MASc_thesis.pdf

19) D. Sinclair, C. C. Grant, R. E. Zee, “Developing, Flying and Evolving a Canadian Microwheel Reaction Wheel - Lessons Learned,” Proceedings of ASTRO 2010, 15th CASI (Canadian Aeronautics and Space Institute) Conference, Toronto, Canada, May 4-6, 2010

20) D. Sinclair, C. C. Grant, R. E. Zee, “Enabling Reaction Wheel Technology for High Performance Nanosatellite Attitude Control,” Proceedings of the 21st Annual AIAA/USU Conference on Small Satellites, Logan, UT, USA, Aug. 13-16, 2007, SSC07-X-3, URL: http://www.sinclairinterplanetary.com/SSC07-X-3.pdf

21) Bryan Johnston-Lemke, Karan Sarda, Cordell C. Grant, Robert E. Zee, “BRITE-Constellation: On-Orbit Attitude Performance of a Nanosatellite Telescope,” Proceedings of the 64th International Astronautical Congress (IAC 2013), Beijing, China, Sept. 23-27, 2013, paper: IAC-13-C1.1.4

22) “PSLV - C20 successfully launches Indo-French satellite SARAL and six other commercial payloads into the orbit,” ISRO, Feb. 25, 2013, URL: http://www.isro.org/pslv-c20/c20-status.aspx

23) “TUGSAT-1/BRITE-Austria,” TUG, Feb. 25, 2013, URL: http://www.tugsat.tugraz.at/

24) “Nanosatellite Launch Service 8,” UTIAS/SFL, Feb. 2013, URL: https://www.utias-sfl.net/NLS-8/?m=201302

25) O. Koudelka, M. Unterberger, P. Romano, W. Weiss, R. Kuschnig, “BRITE – One Year in Orbit,” Proceedings of the 51st Session of Scientific & Technical Subcommittee of UNCOPUOS, Vienna, Austria, Feb. 11-22, 2014, URL: http://www.unoosa.org/pdf/pres/stsc2014/tech-45E.pdf

26) Manuela Unterberger, Patrick Romano, Michael Bergmann, Rainer Kuschnig, Otto Koudelka, “Experience in Commissioning and Operations of the BRITE-Austria Nanosatellite Mission,” Proceedings of the 64th International Astronautical Congress (IAC 2013), Beijing, China, Sept. 23-27, 2013, paper: IAC-13-B6.2.9

27) “UniBRITE nach Schrecksekunde in bester Verfassung!,” March 28, 2013, URL: http://medienportal.univie.ac.at/uniview/forschung/detailansicht/artikel/unibrite-nach-schrecksekunde-in-bester-verfassung/

28) “23 March 2013 - Historic First Picture from TUGSAT-1,” TU Graz, URL: http://www.tugsat.tugraz.at/news-1

29) http://www.tugsat.tugraz.at/news-1

30) A. Kaiser, S. Mochnacki, W. W. Weiss, “BRITE-Constellation: Simulation of Photometric Performance,” Communications in Asteroseismology, Volume 152, January, 2008

31) Alexander M. Beattie, Daniel D. Kekez, Andrew Walker, Robert E. Zee, “Evolution of Multi-Mission Nanosatellite Ground Segment Operations,” Proceedings of SpaceOps 2012, The 12th International Conference on Space Operations, Stockholm, Sweden, June 11-15, 2012, URL: http://www.spaceops2012.org/proceedings/documents/id1292362-Paper-001.pdf

32) Patrick Romano, Manuela Unterberger, Otto Koudelka, “BRITE-Austria Ground Segment and Distributed Operations Concept,” Proceedings of the 63rd IAC (International Astronautical Congress), Naples, Italy, Oct. 1-5, 2012, paper: IAC-12-B4.3.9


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.

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