The spacecraft is 3-axis stabilized (Ref. 22) 23) 24). The 383kg satellite was decommissioned on Oct 1, 2019. Table 3: Specification of the optical camera, The objective is to provide GRB (Gamma-Ray Burst) observations with the agile Tsubame spacecraft. The WBM is always monitoring half the sky and observing the count rate of hard X-ray photons. 3) Standby mode: A nominal mode used prior to an observation engagement (also used for control of the spacecraft). WBMs are flat plate CsI scintillators 6 by 6 centimeters in size and 0.5 centimeters in depth. Subsequently, the following procedure occurred - power generation that supports the satellites’ operation by the deployed solar array wings, ground communications and sound attitude control that maintains those operations. The objective of WBM is to detect a burst occurrence and to determine the event (GRB transient) direction within a beam width of ±10º. Then, TSUBAME entered the safe-hold mode on December 12, while S-band uplinks were prepared in the ground station. The goal of the optical camera is to provide the following EO (Earth Observation) missions: One is landmark tracking to collect sufficient information of target regions of interest. 1) 2) The name Tsubame means "swift" in Japanese, referring to the fast spacecraft attitude changes for event monitoring; it also connotes a certain relationship to NASA's gamma-ray mission, Swift. Legend to Figure 22: The scintillators and detectors are accommodated in an upward direction, the passive shields surround them. The Tsubame project is sponsored by MEXT (Ministry of Education, Culture, Sports, Science and Technology) of Japan in the context of "small satellite research and development projects. Tsubame means ‘swift’ – a name chosen to reflect on the mission’s objective of demonstrating a quick attitude control system and due to parallels with NASA’s Swift mission that also studies gamma-rays. TSUBAME is a satellite developed by the Tokyo Institute of Technology designed to test gyroscopes for pointing control while conducting X-ray astronomy observations and demonstrate a compact camera to look down on Earth. Thermal and structural subsystems: The spacecraft structure offers such functions as a paddle deployment and separation mechanisms. Tsubame.

Tsubame is equipped with two payloads – an Optical Camera and a Gamma-Ray Observation System, GROS. 1) 2). The S-Band system uses BPSK modulation and reaches downlink data rates of 100kbit/s. Launch: A launch of Tsubame as a secondary payload on a Dnepr vehicle is planned for August 2014 from Yasny, Russia. When an increase in count rates is sensed, basic centoid calculations can be made to determine the direction of the event by using data provided by all five sensors. Le, Saburo Matunaga, "Fine-tuning Kalman filters using star trackers data for microsatellite attitude estimation," Proceedings of i-SAIRAS (International Symposium on Artificial Intelligence, Robotics and Automation in Space), Turin, Italy, Sept. 4-6, 2012, 13) Ting Hao, Saburo Matunaga, "Analysis and Precision Attitude Control using Control Moment Gyro for Rapid Multi-target Observation," Proceedings of the 6th International Conference on Recent Advances in Space Technologies (RAST), Istanbul, Turkey, June 12-14, 2013, 14) "Dnepr Launch of ASNARO and 4 piggyback microsatellites," ISC Kosmotras, Nov. 6, 2014, URL: http://www.kosmotras.ru/en/Launch18/, 15) "Japanese Microsatellites Launched," AMSAT, Nov. 6, 2014, URL: http://amsat-uk.org/2014/11/06/japanese-microsatellites-launched/, 16) Shota Kawajiri, Hao Ting, Masanori Matsushita, KyosukeTawara, Saburo Matunaga, "Pointing Accuracy and Stability Analysis of CMG Control for Nano-satellite TSUBAME," 10th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 20-24, 2015, paper: IAA-B10-1402, URL of presentation: http://www.dlr.de/iaa.symp/Portaldata/49/Resources/dokumente/archiv10/pdf/1402_kawajiri.pdf, 17) Masanori Matsushita, Shota Kawajiri, Takashi Nagasu, Eugene Kim, Kazuyoshi Miyasato, Sota Suzuki, Kyosuke Tawara, Kei Ohta, Masaya Koga, Hao Ting, Shin Kurita, Nagahisa Moriyama, Makoto Arimoto, Yoichi Yatsu, Shinichi Kimura, Saburo Matunaga, and the TSUBAME development team, "Flight Model Development of the Microsatellite TSUBAME," 10th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 20-24, 2015, paper: IAA-B10-1008P, 18) "Successful Launch and Commencement of Operation for University-Developed Micro-satellite TSUBAME," TITech, Jan. 15, 2015, URL: http://www.titech.ac.jp/english/news/2015/029409.html, 19) Kuniyuki Omagari, Kota Fujihashi, Saburo Matunaga, "CMG Configuration and Control for Rapid Attitude Maneuver of Small Spacecraft", 9th International Symposium on Artificial Intelligence, Robotics and Automation in Space, Los Angels, USA, Feb. 26-29 2008, URL: http://robotics.estec.esa.int/i-SAIRAS/isairas2008/Proceedings/SESSION%2025/m096-Omagari.pdf, 20) Kyohei Akiyama, Kota Fujihashi, Saburo Matunaga, "High-Speed Attitude Control Syystem for Small Satellite with Micro-CMGs", 27th ISTS (International Symposium on Space Technology and Science), Tsukuba, Japan, July 5-12, 2009, 21) Ting Hao, Saburo Matunaga, "Singular Steering Logic Analysis using Control Moment Gyros for Nanosatellite TSUBAME," Proceedings of the 64th International Astronautical Congress (IAC 2013), Beijing, China, Sept. 23-27, 2013, paper: IAC-13-C1.4.9, 22) Takahiro Enomoto , Kosuke Kawakami, Kazuki Tokoyoda, Takahiro Toizumi, Yoichi Yatsu, Nobuyuki Kawai,, Saburo Matunaga, Takeshi Nakamori, Jun Kataoka, Shin Kubo, "Development of hard X-ray polarimeter aboard nano-satellite TSUBAME," Proceedings of the 28th ISTS (International Symposium on Space Technology and Science), Okinawa, Japan, June 5-12, 2011, paper: 2011-h-03, 23) Takahiro Toizumi, Takahiro Enomot1, Ryuichi Usui, Takeshi Nakamori, Yoich Yatsu, Nobuyuki Kawai, Jun Kataoka, Kuniyuki Omagari, Junichi Nishida, Shinichi Inagawa, Saburo Matsunaga, "X-ray Polarimetry Small Satellite TSUBAME," JAXA Special Publication, JAXA-SP-09-008E, URL: https://repository.exst.jaxa.jp/dspace/bitstream/a-is/16268/1/64574174.pdf, 24) Takahiro Toizumi,, Jun Kataoka, Yoshihiro Tsubuku, Mitsuyoshi Kobayashi, Yoichi Yatsu, Makoto Arimoto, Takashi Shimokawabe, Nobuyuki Kawai, Kuniyuki Omagari, Ken Fujiwara, Hiroki Ashida, Junichi Nishida, Kota Fujihashi, Shinich Inagawa), Yoshiyuki Miura, Saburo Matsunaga, "Transactions of the JSASS (Japan Society for Aeronautical and Space Sciences), Space Technology, Japan, Vol.
The small optical camera module is developed by the Kimura laboratory at the Tokyo University of Science.

In fact, the depth of discharge was no more than 50% in the flight operation. An ion engine is the most appropriate type of space engine, when considering these conditions. The launch is planned for either 2011 or 2012. - In addition to these laboratories, LSS collaborates with two companies: Tamagawa Seiki Co., Ltd. develops the CMG hardware. 0950_6ICSANE_LXHUY_FINAL.pdf, 9) Takashi Kamiya, Saburo Matunaga, and The TSUBAME Development Team, "Development of Micro-satellite TSUBAME Flight Model," Proceedings of the 29th ISTS (International Symposium on Space Technology and Science), Nagoya-Aichi, Japan, June 2-8, 2013, paper: 2013-f-04, 10) Yuta Komiya, Meng Tao, Kyohei Akiyama, Ishizaka Kazuya, Le Xuan Huy, Saburo Matunaga, "Initial Sun-Pointing Operation Analysis for Technology Demonstration Small Satellite TSUBAME," Proceedings of the 28th ISTS (International Symposium on Space Technology and Science), Okinawa, Japan, June 5-12, 2011, paper: 2011-d-04, 11) Huy X. Background rejection is also optimized by the shielding of HXCP consisting of lead, tin and copper. A Li-Po (Lithium-Polymer) battery (6 cells) is used in the eclipse phases of the orbit. Tsubame features a high-resolution optical camera, which has a size of 90 mm x 100 mm x 200 mm, a mass of 1kg and a spatial resolution of 14 m from an orbit of 500 km altitude. Tsubame features a high-resolution optical camera, which has a size of 90 mm x 100 mm x 200 mm, a mass of 1kg and a spatial resolution of 14 m from an orbit of 500 km altitude. The camera has a focal length of 17.5 centimeters and uses a detector of 2,210 by 3,002 pixels that can operate at a read-out speed of up to 5 images per second. In addition, a CW beacon is used (GMSK 9.6 kbit/s / AFSK 1.2 kbit/s). The Optical Camera is 9 by 10 by 20 centimeters in size with a total instrument mass of 1 Kilogram and a power demand of 3 Watts or less. A GPS receiver provides the real-time orbit and spacecraft timing. Tsubame maintained seven different orbital altitudes, and operated […]

More than 40 temperature sensors are used to keep track of temperatures in various positions of the satellite. 11): 1) Detumbling mode (occurs after spacecraft deployment). The WBM device functions as the GBR detector while the HXCP device functions as the observer. The primary payload on this flight is the ASNARO minisatellite of USEF, Japan. 1). 19) 20) 21). Thermal and structural subsystems: The spacecraft structure offers such functions as a paddle deployment and separation mechanisms. SpaceLink Co. Ltd. helps the Tsubame project in terms of the development of EPS (Electrical Power Subsystem) and the OBC (Onboard Computer). By comparing the count rate of each detector, the source position can be estimated by using the barycentric method.

1) Engineering mission - involving the following objectives: • A goal is to demonstrate the satellite bus technology for the 50 kg microsatellite class and to verify COTS (Commercial Off The Shelf) components such as microprocessors, memory, and Li-ion batteries in the space. For a super low altitude satellite, strong thrusters are not required, although atmospheric resistance increases. The standby mode is used to check out the spacecraft subsystems and to test for instance the capabilities of the new CMG device. Figure 19: Accommodation of the Gamma-ray observation sensors (image credit: TITECH), Figure 20: Block diagram of the GRB (Gamma-Ray Burst) system (image credit: Kawai Lab). Furthermore, we are developing a compact satellite to minimize air resistance, and will verify that our technology can support orbiting at super low altitudes over an extended period of time. The goal of HXCP is to detect photons in the 30 – 200 keV band using the azimuthal angle anisotropy of Compton scattering. The lowest battery voltage during the experiment was 23.2 V as shown in Figure 4. Tsubame is a microsatellite project of Matunaga LSS (Laboratory for Space System) at the Tokyo Institute of Technology that combines technical and scientific mission objectives. The other one is panorama shooting service to obtain broad imagery from the high resolution camera, which has a narrow FOV (Field of View). - The Tokyo University of Science Kimura laboratory is responsible for the development of the optical camera module. The scatterer consists of 64 plastic scintillators (6.5 mm x 6.5 mm x 49 mm) placed at the center of the detector. S-band Tx, BPSK, 5~100kbit/s, 0.07 W, patch antenna, Table 1: Key parameters of the TSUBAME microsatellite, Launch: The Tsubame microsatellite was launched as a secondary payload on November 6, 2014 (07:35:49 UTC) on a Dnepr-1 vehicle from the Yasny Cosmodrome, Russia. Each WBM weighs 260 grams and has a minimum energy threshold of 30keV and a minimum count rate of 10 Hz. The re-orientation is completed within 15 seconds from the event trigger. A special 16 channel MAPMT was developed for the Tsubame mission which provides quite a high quantum efficiency; it uses mechanically strengthened electrodes that survived the H-IIA QT level. Consequently, this type of satellite will require a greater amount of fuel than conventional satellites. 16), 1) The communications rate can be more than 10 kbit/s usually, though it is difficult to achieve 100 kbit/s stably, 2) TSUBAME was able to endure the Dnepr rocket vibrations. Experiment/Sensor complement: (CMG, Optical Camera, GROS), The CMG is a joint development project of LSS (software) and Tamagawa Seiki Co. (hardware). - The gamma-ray observation sensors are developed by the Tokyo Institute of Technology, Kawai laboratory. Tsubame is the fourth satellite project of TITECH, after CUTE-1 (launch June 30, 2003), Cute-1.7+APD (launch Feb. 21, 2006), and Cute-1.7+APD II (launch April 28, 2008). The HXCP requirements call for the polarimeter to observe the GRB event (i.e., point into the proper direction) within 10-20 seconds after the event detection by the coarse calibration sensor. Figure 19: Schematic view of an observation sequence during a GRB event (image credit: TITech). The wheel is rotated by a synchronous motor to generate an angular momentum of 0.053 Nms. Tsubame is the fourth satellite project of TITECH, after CUTE-1 (launch June 30, 2003), Cute-1.7+APD (launch Feb. 21, 2006), and Cute-1.7+APD II (launch April 28, 2008). Use of COTS components to keep the development within budget (Ref. The other one is panorama shooting service to obtain broad imagery from the high resolution camera, which has a narrow FOV (Field of View). Their signals are read by the MAPMTs (Multi-Anode Photo Multiplier Tubes) and the Si APDs (Avalanche Photodiodes), respectively. window.dataLayer = window.dataLayer || []; The Attitude Determination and Control System uses CMGs and Magnetic Torquers for attitude actuation and a series of sensors for navigation and attitude control. For redundancy, each subsystem is connected through a UART (Universal Asynchronous Receiver/Transmitter) link with Comm/C&DH subsystems - in case any communication failures on the CAN bus. A special 16 channel MAPMT was developed for the Tsubame mission which provides quite a high quantum efficiency; it uses mechanically strengthened electrodes that survived the H-IIA QT level.

Le, Takashi Kamiya, Ting Hao, Shota Kawajiri, Saburo Matunaga, "Tsubame Microsatellite: Design, Development and Verification of Attitude Determination and Control System," ICSANE 2013 (International Conference on Space, Aeronautical and Navigational Electronics), Hanoi, Vietnam, Dec. 2-3, 2013, URL: http://www.aprsaf.org/annual_meetings/aprsaf20/pdf/working_groups/csa_day1/ In order to reject those events, a coincidence technique is applied. Figure 18: Engineering model of the optical camera (image credit: TITech). The 430MHz UHF downlink channel reaches data rates of 9.6kbit/s while the 144MHz VHF uplink is done at 1.2kbit/s.

For redundancy, each subsystem is connected through a UART (Universal Asynchronous Receiver/Transmitter) link with Comm/C&DH subsystems - in case any communication failures on the CAN bus. Figure 17: Accommodation of the Gamma-ray observation sensors (image credit: TITECH), Figure 18: Block diagram of the GRB (Gamma-Ray Burst) system (image credit: Kawai Lab). The SAPs are needed in support of the high power (130 W max, 86 W average) requirements of the mission. Using high performance and ultra low-power analog VLSIs that can processes multi signals simultaneously, the signal processing system could be downsized. Each CMG used on Tsubame is 7.35 centimeters in diameter with a total length per assembly of 15 centimeters and a mass of 1 Kilogram per wheel. 430 MHz-band Tx, CW, 0.1W, whip antenna In order to solve the atmospheric drag issue, JAXA has adopted an ion engine.
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The spacecraft is 3-axis stabilized (Ref. 22) 23) 24). The 383kg satellite was decommissioned on Oct 1, 2019. Table 3: Specification of the optical camera, The objective is to provide GRB (Gamma-Ray Burst) observations with the agile Tsubame spacecraft. The WBM is always monitoring half the sky and observing the count rate of hard X-ray photons. 3) Standby mode: A nominal mode used prior to an observation engagement (also used for control of the spacecraft). WBMs are flat plate CsI scintillators 6 by 6 centimeters in size and 0.5 centimeters in depth. Subsequently, the following procedure occurred - power generation that supports the satellites’ operation by the deployed solar array wings, ground communications and sound attitude control that maintains those operations. The objective of WBM is to detect a burst occurrence and to determine the event (GRB transient) direction within a beam width of ±10º. Then, TSUBAME entered the safe-hold mode on December 12, while S-band uplinks were prepared in the ground station. The goal of the optical camera is to provide the following EO (Earth Observation) missions: One is landmark tracking to collect sufficient information of target regions of interest. 1) 2) The name Tsubame means "swift" in Japanese, referring to the fast spacecraft attitude changes for event monitoring; it also connotes a certain relationship to NASA's gamma-ray mission, Swift. Legend to Figure 22: The scintillators and detectors are accommodated in an upward direction, the passive shields surround them. The Tsubame project is sponsored by MEXT (Ministry of Education, Culture, Sports, Science and Technology) of Japan in the context of "small satellite research and development projects. Tsubame means ‘swift’ – a name chosen to reflect on the mission’s objective of demonstrating a quick attitude control system and due to parallels with NASA’s Swift mission that also studies gamma-rays. TSUBAME is a satellite developed by the Tokyo Institute of Technology designed to test gyroscopes for pointing control while conducting X-ray astronomy observations and demonstrate a compact camera to look down on Earth. Thermal and structural subsystems: The spacecraft structure offers such functions as a paddle deployment and separation mechanisms. Tsubame.

Tsubame is equipped with two payloads – an Optical Camera and a Gamma-Ray Observation System, GROS. 1) 2). The S-Band system uses BPSK modulation and reaches downlink data rates of 100kbit/s. Launch: A launch of Tsubame as a secondary payload on a Dnepr vehicle is planned for August 2014 from Yasny, Russia. When an increase in count rates is sensed, basic centoid calculations can be made to determine the direction of the event by using data provided by all five sensors. Le, Saburo Matunaga, "Fine-tuning Kalman filters using star trackers data for microsatellite attitude estimation," Proceedings of i-SAIRAS (International Symposium on Artificial Intelligence, Robotics and Automation in Space), Turin, Italy, Sept. 4-6, 2012, 13) Ting Hao, Saburo Matunaga, "Analysis and Precision Attitude Control using Control Moment Gyro for Rapid Multi-target Observation," Proceedings of the 6th International Conference on Recent Advances in Space Technologies (RAST), Istanbul, Turkey, June 12-14, 2013, 14) "Dnepr Launch of ASNARO and 4 piggyback microsatellites," ISC Kosmotras, Nov. 6, 2014, URL: http://www.kosmotras.ru/en/Launch18/, 15) "Japanese Microsatellites Launched," AMSAT, Nov. 6, 2014, URL: http://amsat-uk.org/2014/11/06/japanese-microsatellites-launched/, 16) Shota Kawajiri, Hao Ting, Masanori Matsushita, KyosukeTawara, Saburo Matunaga, "Pointing Accuracy and Stability Analysis of CMG Control for Nano-satellite TSUBAME," 10th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 20-24, 2015, paper: IAA-B10-1402, URL of presentation: http://www.dlr.de/iaa.symp/Portaldata/49/Resources/dokumente/archiv10/pdf/1402_kawajiri.pdf, 17) Masanori Matsushita, Shota Kawajiri, Takashi Nagasu, Eugene Kim, Kazuyoshi Miyasato, Sota Suzuki, Kyosuke Tawara, Kei Ohta, Masaya Koga, Hao Ting, Shin Kurita, Nagahisa Moriyama, Makoto Arimoto, Yoichi Yatsu, Shinichi Kimura, Saburo Matunaga, and the TSUBAME development team, "Flight Model Development of the Microsatellite TSUBAME," 10th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 20-24, 2015, paper: IAA-B10-1008P, 18) "Successful Launch and Commencement of Operation for University-Developed Micro-satellite TSUBAME," TITech, Jan. 15, 2015, URL: http://www.titech.ac.jp/english/news/2015/029409.html, 19) Kuniyuki Omagari, Kota Fujihashi, Saburo Matunaga, "CMG Configuration and Control for Rapid Attitude Maneuver of Small Spacecraft", 9th International Symposium on Artificial Intelligence, Robotics and Automation in Space, Los Angels, USA, Feb. 26-29 2008, URL: http://robotics.estec.esa.int/i-SAIRAS/isairas2008/Proceedings/SESSION%2025/m096-Omagari.pdf, 20) Kyohei Akiyama, Kota Fujihashi, Saburo Matunaga, "High-Speed Attitude Control Syystem for Small Satellite with Micro-CMGs", 27th ISTS (International Symposium on Space Technology and Science), Tsukuba, Japan, July 5-12, 2009, 21) Ting Hao, Saburo Matunaga, "Singular Steering Logic Analysis using Control Moment Gyros for Nanosatellite TSUBAME," Proceedings of the 64th International Astronautical Congress (IAC 2013), Beijing, China, Sept. 23-27, 2013, paper: IAC-13-C1.4.9, 22) Takahiro Enomoto , Kosuke Kawakami, Kazuki Tokoyoda, Takahiro Toizumi, Yoichi Yatsu, Nobuyuki Kawai,, Saburo Matunaga, Takeshi Nakamori, Jun Kataoka, Shin Kubo, "Development of hard X-ray polarimeter aboard nano-satellite TSUBAME," Proceedings of the 28th ISTS (International Symposium on Space Technology and Science), Okinawa, Japan, June 5-12, 2011, paper: 2011-h-03, 23) Takahiro Toizumi, Takahiro Enomot1, Ryuichi Usui, Takeshi Nakamori, Yoich Yatsu, Nobuyuki Kawai, Jun Kataoka, Kuniyuki Omagari, Junichi Nishida, Shinichi Inagawa, Saburo Matsunaga, "X-ray Polarimetry Small Satellite TSUBAME," JAXA Special Publication, JAXA-SP-09-008E, URL: https://repository.exst.jaxa.jp/dspace/bitstream/a-is/16268/1/64574174.pdf, 24) Takahiro Toizumi,, Jun Kataoka, Yoshihiro Tsubuku, Mitsuyoshi Kobayashi, Yoichi Yatsu, Makoto Arimoto, Takashi Shimokawabe, Nobuyuki Kawai, Kuniyuki Omagari, Ken Fujiwara, Hiroki Ashida, Junichi Nishida, Kota Fujihashi, Shinich Inagawa), Yoshiyuki Miura, Saburo Matsunaga, "Transactions of the JSASS (Japan Society for Aeronautical and Space Sciences), Space Technology, Japan, Vol.
The small optical camera module is developed by the Kimura laboratory at the Tokyo University of Science.

In fact, the depth of discharge was no more than 50% in the flight operation. An ion engine is the most appropriate type of space engine, when considering these conditions. The launch is planned for either 2011 or 2012. - In addition to these laboratories, LSS collaborates with two companies: Tamagawa Seiki Co., Ltd. develops the CMG hardware. 0950_6ICSANE_LXHUY_FINAL.pdf, 9) Takashi Kamiya, Saburo Matunaga, and The TSUBAME Development Team, "Development of Micro-satellite TSUBAME Flight Model," Proceedings of the 29th ISTS (International Symposium on Space Technology and Science), Nagoya-Aichi, Japan, June 2-8, 2013, paper: 2013-f-04, 10) Yuta Komiya, Meng Tao, Kyohei Akiyama, Ishizaka Kazuya, Le Xuan Huy, Saburo Matunaga, "Initial Sun-Pointing Operation Analysis for Technology Demonstration Small Satellite TSUBAME," Proceedings of the 28th ISTS (International Symposium on Space Technology and Science), Okinawa, Japan, June 5-12, 2011, paper: 2011-d-04, 11) Huy X. Background rejection is also optimized by the shielding of HXCP consisting of lead, tin and copper. A Li-Po (Lithium-Polymer) battery (6 cells) is used in the eclipse phases of the orbit. Tsubame features a high-resolution optical camera, which has a size of 90 mm x 100 mm x 200 mm, a mass of 1kg and a spatial resolution of 14 m from an orbit of 500 km altitude. Tsubame features a high-resolution optical camera, which has a size of 90 mm x 100 mm x 200 mm, a mass of 1kg and a spatial resolution of 14 m from an orbit of 500 km altitude. The camera has a focal length of 17.5 centimeters and uses a detector of 2,210 by 3,002 pixels that can operate at a read-out speed of up to 5 images per second. In addition, a CW beacon is used (GMSK 9.6 kbit/s / AFSK 1.2 kbit/s). The Optical Camera is 9 by 10 by 20 centimeters in size with a total instrument mass of 1 Kilogram and a power demand of 3 Watts or less. A GPS receiver provides the real-time orbit and spacecraft timing. Tsubame maintained seven different orbital altitudes, and operated […]

More than 40 temperature sensors are used to keep track of temperatures in various positions of the satellite. 11): 1) Detumbling mode (occurs after spacecraft deployment). The WBM device functions as the GBR detector while the HXCP device functions as the observer. The primary payload on this flight is the ASNARO minisatellite of USEF, Japan. 1). 19) 20) 21). Thermal and structural subsystems: The spacecraft structure offers such functions as a paddle deployment and separation mechanisms. SpaceLink Co. Ltd. helps the Tsubame project in terms of the development of EPS (Electrical Power Subsystem) and the OBC (Onboard Computer). By comparing the count rate of each detector, the source position can be estimated by using the barycentric method.

1) Engineering mission - involving the following objectives: • A goal is to demonstrate the satellite bus technology for the 50 kg microsatellite class and to verify COTS (Commercial Off The Shelf) components such as microprocessors, memory, and Li-ion batteries in the space. For a super low altitude satellite, strong thrusters are not required, although atmospheric resistance increases. The standby mode is used to check out the spacecraft subsystems and to test for instance the capabilities of the new CMG device. Figure 19: Accommodation of the Gamma-ray observation sensors (image credit: TITECH), Figure 20: Block diagram of the GRB (Gamma-Ray Burst) system (image credit: Kawai Lab). Furthermore, we are developing a compact satellite to minimize air resistance, and will verify that our technology can support orbiting at super low altitudes over an extended period of time. The goal of HXCP is to detect photons in the 30 – 200 keV band using the azimuthal angle anisotropy of Compton scattering. The lowest battery voltage during the experiment was 23.2 V as shown in Figure 4. Tsubame is a microsatellite project of Matunaga LSS (Laboratory for Space System) at the Tokyo Institute of Technology that combines technical and scientific mission objectives. The other one is panorama shooting service to obtain broad imagery from the high resolution camera, which has a narrow FOV (Field of View). - The Tokyo University of Science Kimura laboratory is responsible for the development of the optical camera module. The scatterer consists of 64 plastic scintillators (6.5 mm x 6.5 mm x 49 mm) placed at the center of the detector. S-band Tx, BPSK, 5~100kbit/s, 0.07 W, patch antenna, Table 1: Key parameters of the TSUBAME microsatellite, Launch: The Tsubame microsatellite was launched as a secondary payload on November 6, 2014 (07:35:49 UTC) on a Dnepr-1 vehicle from the Yasny Cosmodrome, Russia. Each WBM weighs 260 grams and has a minimum energy threshold of 30keV and a minimum count rate of 10 Hz. The re-orientation is completed within 15 seconds from the event trigger. A special 16 channel MAPMT was developed for the Tsubame mission which provides quite a high quantum efficiency; it uses mechanically strengthened electrodes that survived the H-IIA QT level. Consequently, this type of satellite will require a greater amount of fuel than conventional satellites. 16), 1) The communications rate can be more than 10 kbit/s usually, though it is difficult to achieve 100 kbit/s stably, 2) TSUBAME was able to endure the Dnepr rocket vibrations. Experiment/Sensor complement: (CMG, Optical Camera, GROS), The CMG is a joint development project of LSS (software) and Tamagawa Seiki Co. (hardware). - The gamma-ray observation sensors are developed by the Tokyo Institute of Technology, Kawai laboratory. Tsubame is the fourth satellite project of TITECH, after CUTE-1 (launch June 30, 2003), Cute-1.7+APD (launch Feb. 21, 2006), and Cute-1.7+APD II (launch April 28, 2008). The HXCP requirements call for the polarimeter to observe the GRB event (i.e., point into the proper direction) within 10-20 seconds after the event detection by the coarse calibration sensor. Figure 19: Schematic view of an observation sequence during a GRB event (image credit: TITech). The wheel is rotated by a synchronous motor to generate an angular momentum of 0.053 Nms. Tsubame is the fourth satellite project of TITECH, after CUTE-1 (launch June 30, 2003), Cute-1.7+APD (launch Feb. 21, 2006), and Cute-1.7+APD II (launch April 28, 2008). Use of COTS components to keep the development within budget (Ref. The other one is panorama shooting service to obtain broad imagery from the high resolution camera, which has a narrow FOV (Field of View). Their signals are read by the MAPMTs (Multi-Anode Photo Multiplier Tubes) and the Si APDs (Avalanche Photodiodes), respectively. window.dataLayer = window.dataLayer || []; The Attitude Determination and Control System uses CMGs and Magnetic Torquers for attitude actuation and a series of sensors for navigation and attitude control. For redundancy, each subsystem is connected through a UART (Universal Asynchronous Receiver/Transmitter) link with Comm/C&DH subsystems - in case any communication failures on the CAN bus. A special 16 channel MAPMT was developed for the Tsubame mission which provides quite a high quantum efficiency; it uses mechanically strengthened electrodes that survived the H-IIA QT level.

Le, Takashi Kamiya, Ting Hao, Shota Kawajiri, Saburo Matunaga, "Tsubame Microsatellite: Design, Development and Verification of Attitude Determination and Control System," ICSANE 2013 (International Conference on Space, Aeronautical and Navigational Electronics), Hanoi, Vietnam, Dec. 2-3, 2013, URL: http://www.aprsaf.org/annual_meetings/aprsaf20/pdf/working_groups/csa_day1/ In order to reject those events, a coincidence technique is applied. Figure 18: Engineering model of the optical camera (image credit: TITech). The 430MHz UHF downlink channel reaches data rates of 9.6kbit/s while the 144MHz VHF uplink is done at 1.2kbit/s.

For redundancy, each subsystem is connected through a UART (Universal Asynchronous Receiver/Transmitter) link with Comm/C&DH subsystems - in case any communication failures on the CAN bus. Figure 17: Accommodation of the Gamma-ray observation sensors (image credit: TITECH), Figure 18: Block diagram of the GRB (Gamma-Ray Burst) system (image credit: Kawai Lab). The SAPs are needed in support of the high power (130 W max, 86 W average) requirements of the mission. Using high performance and ultra low-power analog VLSIs that can processes multi signals simultaneously, the signal processing system could be downsized. Each CMG used on Tsubame is 7.35 centimeters in diameter with a total length per assembly of 15 centimeters and a mass of 1 Kilogram per wheel. 430 MHz-band Tx, CW, 0.1W, whip antenna In order to solve the atmospheric drag issue, JAXA has adopted an ion engine.
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By Uncategorized October 27, 2020

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The spacecraft is 3-axis stabilized (Ref. 22) 23) 24). The 383kg satellite was decommissioned on Oct 1, 2019. Table 3: Specification of the optical camera, The objective is to provide GRB (Gamma-Ray Burst) observations with the agile Tsubame spacecraft. The WBM is always monitoring half the sky and observing the count rate of hard X-ray photons. 3) Standby mode: A nominal mode used prior to an observation engagement (also used for control of the spacecraft). WBMs are flat plate CsI scintillators 6 by 6 centimeters in size and 0.5 centimeters in depth. Subsequently, the following procedure occurred - power generation that supports the satellites’ operation by the deployed solar array wings, ground communications and sound attitude control that maintains those operations. The objective of WBM is to detect a burst occurrence and to determine the event (GRB transient) direction within a beam width of ±10º. Then, TSUBAME entered the safe-hold mode on December 12, while S-band uplinks were prepared in the ground station. The goal of the optical camera is to provide the following EO (Earth Observation) missions: One is landmark tracking to collect sufficient information of target regions of interest. 1) 2) The name Tsubame means "swift" in Japanese, referring to the fast spacecraft attitude changes for event monitoring; it also connotes a certain relationship to NASA's gamma-ray mission, Swift. Legend to Figure 22: The scintillators and detectors are accommodated in an upward direction, the passive shields surround them. The Tsubame project is sponsored by MEXT (Ministry of Education, Culture, Sports, Science and Technology) of Japan in the context of "small satellite research and development projects. Tsubame means ‘swift’ – a name chosen to reflect on the mission’s objective of demonstrating a quick attitude control system and due to parallels with NASA’s Swift mission that also studies gamma-rays. TSUBAME is a satellite developed by the Tokyo Institute of Technology designed to test gyroscopes for pointing control while conducting X-ray astronomy observations and demonstrate a compact camera to look down on Earth. Thermal and structural subsystems: The spacecraft structure offers such functions as a paddle deployment and separation mechanisms. Tsubame.

Tsubame is equipped with two payloads – an Optical Camera and a Gamma-Ray Observation System, GROS. 1) 2). The S-Band system uses BPSK modulation and reaches downlink data rates of 100kbit/s. Launch: A launch of Tsubame as a secondary payload on a Dnepr vehicle is planned for August 2014 from Yasny, Russia. When an increase in count rates is sensed, basic centoid calculations can be made to determine the direction of the event by using data provided by all five sensors. Le, Saburo Matunaga, "Fine-tuning Kalman filters using star trackers data for microsatellite attitude estimation," Proceedings of i-SAIRAS (International Symposium on Artificial Intelligence, Robotics and Automation in Space), Turin, Italy, Sept. 4-6, 2012, 13) Ting Hao, Saburo Matunaga, "Analysis and Precision Attitude Control using Control Moment Gyro for Rapid Multi-target Observation," Proceedings of the 6th International Conference on Recent Advances in Space Technologies (RAST), Istanbul, Turkey, June 12-14, 2013, 14) "Dnepr Launch of ASNARO and 4 piggyback microsatellites," ISC Kosmotras, Nov. 6, 2014, URL: http://www.kosmotras.ru/en/Launch18/, 15) "Japanese Microsatellites Launched," AMSAT, Nov. 6, 2014, URL: http://amsat-uk.org/2014/11/06/japanese-microsatellites-launched/, 16) Shota Kawajiri, Hao Ting, Masanori Matsushita, KyosukeTawara, Saburo Matunaga, "Pointing Accuracy and Stability Analysis of CMG Control for Nano-satellite TSUBAME," 10th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 20-24, 2015, paper: IAA-B10-1402, URL of presentation: http://www.dlr.de/iaa.symp/Portaldata/49/Resources/dokumente/archiv10/pdf/1402_kawajiri.pdf, 17) Masanori Matsushita, Shota Kawajiri, Takashi Nagasu, Eugene Kim, Kazuyoshi Miyasato, Sota Suzuki, Kyosuke Tawara, Kei Ohta, Masaya Koga, Hao Ting, Shin Kurita, Nagahisa Moriyama, Makoto Arimoto, Yoichi Yatsu, Shinichi Kimura, Saburo Matunaga, and the TSUBAME development team, "Flight Model Development of the Microsatellite TSUBAME," 10th IAA Symposium on Small Satellites for Earth Observation, Berlin, Germany, April 20-24, 2015, paper: IAA-B10-1008P, 18) "Successful Launch and Commencement of Operation for University-Developed Micro-satellite TSUBAME," TITech, Jan. 15, 2015, URL: http://www.titech.ac.jp/english/news/2015/029409.html, 19) Kuniyuki Omagari, Kota Fujihashi, Saburo Matunaga, "CMG Configuration and Control for Rapid Attitude Maneuver of Small Spacecraft", 9th International Symposium on Artificial Intelligence, Robotics and Automation in Space, Los Angels, USA, Feb. 26-29 2008, URL: http://robotics.estec.esa.int/i-SAIRAS/isairas2008/Proceedings/SESSION%2025/m096-Omagari.pdf, 20) Kyohei Akiyama, Kota Fujihashi, Saburo Matunaga, "High-Speed Attitude Control Syystem for Small Satellite with Micro-CMGs", 27th ISTS (International Symposium on Space Technology and Science), Tsukuba, Japan, July 5-12, 2009, 21) Ting Hao, Saburo Matunaga, "Singular Steering Logic Analysis using Control Moment Gyros for Nanosatellite TSUBAME," Proceedings of the 64th International Astronautical Congress (IAC 2013), Beijing, China, Sept. 23-27, 2013, paper: IAC-13-C1.4.9, 22) Takahiro Enomoto , Kosuke Kawakami, Kazuki Tokoyoda, Takahiro Toizumi, Yoichi Yatsu, Nobuyuki Kawai,, Saburo Matunaga, Takeshi Nakamori, Jun Kataoka, Shin Kubo, "Development of hard X-ray polarimeter aboard nano-satellite TSUBAME," Proceedings of the 28th ISTS (International Symposium on Space Technology and Science), Okinawa, Japan, June 5-12, 2011, paper: 2011-h-03, 23) Takahiro Toizumi, Takahiro Enomot1, Ryuichi Usui, Takeshi Nakamori, Yoich Yatsu, Nobuyuki Kawai, Jun Kataoka, Kuniyuki Omagari, Junichi Nishida, Shinichi Inagawa, Saburo Matsunaga, "X-ray Polarimetry Small Satellite TSUBAME," JAXA Special Publication, JAXA-SP-09-008E, URL: https://repository.exst.jaxa.jp/dspace/bitstream/a-is/16268/1/64574174.pdf, 24) Takahiro Toizumi,, Jun Kataoka, Yoshihiro Tsubuku, Mitsuyoshi Kobayashi, Yoichi Yatsu, Makoto Arimoto, Takashi Shimokawabe, Nobuyuki Kawai, Kuniyuki Omagari, Ken Fujiwara, Hiroki Ashida, Junichi Nishida, Kota Fujihashi, Shinich Inagawa), Yoshiyuki Miura, Saburo Matsunaga, "Transactions of the JSASS (Japan Society for Aeronautical and Space Sciences), Space Technology, Japan, Vol.
The small optical camera module is developed by the Kimura laboratory at the Tokyo University of Science.

In fact, the depth of discharge was no more than 50% in the flight operation. An ion engine is the most appropriate type of space engine, when considering these conditions. The launch is planned for either 2011 or 2012. - In addition to these laboratories, LSS collaborates with two companies: Tamagawa Seiki Co., Ltd. develops the CMG hardware. 0950_6ICSANE_LXHUY_FINAL.pdf, 9) Takashi Kamiya, Saburo Matunaga, and The TSUBAME Development Team, "Development of Micro-satellite TSUBAME Flight Model," Proceedings of the 29th ISTS (International Symposium on Space Technology and Science), Nagoya-Aichi, Japan, June 2-8, 2013, paper: 2013-f-04, 10) Yuta Komiya, Meng Tao, Kyohei Akiyama, Ishizaka Kazuya, Le Xuan Huy, Saburo Matunaga, "Initial Sun-Pointing Operation Analysis for Technology Demonstration Small Satellite TSUBAME," Proceedings of the 28th ISTS (International Symposium on Space Technology and Science), Okinawa, Japan, June 5-12, 2011, paper: 2011-d-04, 11) Huy X. Background rejection is also optimized by the shielding of HXCP consisting of lead, tin and copper. A Li-Po (Lithium-Polymer) battery (6 cells) is used in the eclipse phases of the orbit. Tsubame features a high-resolution optical camera, which has a size of 90 mm x 100 mm x 200 mm, a mass of 1kg and a spatial resolution of 14 m from an orbit of 500 km altitude. Tsubame features a high-resolution optical camera, which has a size of 90 mm x 100 mm x 200 mm, a mass of 1kg and a spatial resolution of 14 m from an orbit of 500 km altitude. The camera has a focal length of 17.5 centimeters and uses a detector of 2,210 by 3,002 pixels that can operate at a read-out speed of up to 5 images per second. In addition, a CW beacon is used (GMSK 9.6 kbit/s / AFSK 1.2 kbit/s). The Optical Camera is 9 by 10 by 20 centimeters in size with a total instrument mass of 1 Kilogram and a power demand of 3 Watts or less. A GPS receiver provides the real-time orbit and spacecraft timing. Tsubame maintained seven different orbital altitudes, and operated […]

More than 40 temperature sensors are used to keep track of temperatures in various positions of the satellite. 11): 1) Detumbling mode (occurs after spacecraft deployment). The WBM device functions as the GBR detector while the HXCP device functions as the observer. The primary payload on this flight is the ASNARO minisatellite of USEF, Japan. 1). 19) 20) 21). Thermal and structural subsystems: The spacecraft structure offers such functions as a paddle deployment and separation mechanisms. SpaceLink Co. Ltd. helps the Tsubame project in terms of the development of EPS (Electrical Power Subsystem) and the OBC (Onboard Computer). By comparing the count rate of each detector, the source position can be estimated by using the barycentric method.

1) Engineering mission - involving the following objectives: • A goal is to demonstrate the satellite bus technology for the 50 kg microsatellite class and to verify COTS (Commercial Off The Shelf) components such as microprocessors, memory, and Li-ion batteries in the space. For a super low altitude satellite, strong thrusters are not required, although atmospheric resistance increases. The standby mode is used to check out the spacecraft subsystems and to test for instance the capabilities of the new CMG device. Figure 19: Accommodation of the Gamma-ray observation sensors (image credit: TITECH), Figure 20: Block diagram of the GRB (Gamma-Ray Burst) system (image credit: Kawai Lab). Furthermore, we are developing a compact satellite to minimize air resistance, and will verify that our technology can support orbiting at super low altitudes over an extended period of time. The goal of HXCP is to detect photons in the 30 – 200 keV band using the azimuthal angle anisotropy of Compton scattering. The lowest battery voltage during the experiment was 23.2 V as shown in Figure 4. Tsubame is a microsatellite project of Matunaga LSS (Laboratory for Space System) at the Tokyo Institute of Technology that combines technical and scientific mission objectives. The other one is panorama shooting service to obtain broad imagery from the high resolution camera, which has a narrow FOV (Field of View). - The Tokyo University of Science Kimura laboratory is responsible for the development of the optical camera module. The scatterer consists of 64 plastic scintillators (6.5 mm x 6.5 mm x 49 mm) placed at the center of the detector. S-band Tx, BPSK, 5~100kbit/s, 0.07 W, patch antenna, Table 1: Key parameters of the TSUBAME microsatellite, Launch: The Tsubame microsatellite was launched as a secondary payload on November 6, 2014 (07:35:49 UTC) on a Dnepr-1 vehicle from the Yasny Cosmodrome, Russia. Each WBM weighs 260 grams and has a minimum energy threshold of 30keV and a minimum count rate of 10 Hz. The re-orientation is completed within 15 seconds from the event trigger. A special 16 channel MAPMT was developed for the Tsubame mission which provides quite a high quantum efficiency; it uses mechanically strengthened electrodes that survived the H-IIA QT level. Consequently, this type of satellite will require a greater amount of fuel than conventional satellites. 16), 1) The communications rate can be more than 10 kbit/s usually, though it is difficult to achieve 100 kbit/s stably, 2) TSUBAME was able to endure the Dnepr rocket vibrations. Experiment/Sensor complement: (CMG, Optical Camera, GROS), The CMG is a joint development project of LSS (software) and Tamagawa Seiki Co. (hardware). - The gamma-ray observation sensors are developed by the Tokyo Institute of Technology, Kawai laboratory. Tsubame is the fourth satellite project of TITECH, after CUTE-1 (launch June 30, 2003), Cute-1.7+APD (launch Feb. 21, 2006), and Cute-1.7+APD II (launch April 28, 2008). The HXCP requirements call for the polarimeter to observe the GRB event (i.e., point into the proper direction) within 10-20 seconds after the event detection by the coarse calibration sensor. Figure 19: Schematic view of an observation sequence during a GRB event (image credit: TITech). The wheel is rotated by a synchronous motor to generate an angular momentum of 0.053 Nms. Tsubame is the fourth satellite project of TITECH, after CUTE-1 (launch June 30, 2003), Cute-1.7+APD (launch Feb. 21, 2006), and Cute-1.7+APD II (launch April 28, 2008). Use of COTS components to keep the development within budget (Ref. The other one is panorama shooting service to obtain broad imagery from the high resolution camera, which has a narrow FOV (Field of View). Their signals are read by the MAPMTs (Multi-Anode Photo Multiplier Tubes) and the Si APDs (Avalanche Photodiodes), respectively. window.dataLayer = window.dataLayer || []; The Attitude Determination and Control System uses CMGs and Magnetic Torquers for attitude actuation and a series of sensors for navigation and attitude control. For redundancy, each subsystem is connected through a UART (Universal Asynchronous Receiver/Transmitter) link with Comm/C&DH subsystems - in case any communication failures on the CAN bus. A special 16 channel MAPMT was developed for the Tsubame mission which provides quite a high quantum efficiency; it uses mechanically strengthened electrodes that survived the H-IIA QT level.

Le, Takashi Kamiya, Ting Hao, Shota Kawajiri, Saburo Matunaga, "Tsubame Microsatellite: Design, Development and Verification of Attitude Determination and Control System," ICSANE 2013 (International Conference on Space, Aeronautical and Navigational Electronics), Hanoi, Vietnam, Dec. 2-3, 2013, URL: http://www.aprsaf.org/annual_meetings/aprsaf20/pdf/working_groups/csa_day1/ In order to reject those events, a coincidence technique is applied. Figure 18: Engineering model of the optical camera (image credit: TITech). The 430MHz UHF downlink channel reaches data rates of 9.6kbit/s while the 144MHz VHF uplink is done at 1.2kbit/s.

For redundancy, each subsystem is connected through a UART (Universal Asynchronous Receiver/Transmitter) link with Comm/C&DH subsystems - in case any communication failures on the CAN bus. Figure 17: Accommodation of the Gamma-ray observation sensors (image credit: TITECH), Figure 18: Block diagram of the GRB (Gamma-Ray Burst) system (image credit: Kawai Lab). The SAPs are needed in support of the high power (130 W max, 86 W average) requirements of the mission. Using high performance and ultra low-power analog VLSIs that can processes multi signals simultaneously, the signal processing system could be downsized. Each CMG used on Tsubame is 7.35 centimeters in diameter with a total length per assembly of 15 centimeters and a mass of 1 Kilogram per wheel. 430 MHz-band Tx, CW, 0.1W, whip antenna In order to solve the atmospheric drag issue, JAXA has adopted an ion engine.

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