System Integration of a Star Sensor for the Small Earth Observation Satellite RISING-2

Kuwahara, Toshinori; Battazzo, Steve; Tomioka, Y.; Fukuda, Kazuhiko; Sakamoto, Yuji; Yoshida, Kazuya

doi:10.2322/tastj.10.td_1

Cited by 9 publications

(7 citation statements)

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“…The attitude control system of the RISESAT is three‐axis stabilized by utilizing two star trackers developed by SRL (Kuwahara et al ) and four reaction wheels in a 4‐skew configuration. RISESAT is capable of various attitude control modes: nadir‐pointing, target pointing, rim pointing and inertial pointing modes.…”

Section: Risesatmentioning

confidence: 99%

RISEPix—A Timepix‐based radiation monitor telescope onboard the RISESAT satellite

et al. 2019

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Rapid International Scientific Experiment Satellite (RISESAT) is a small Japanese experimental Earth-observing, science and technology demonstration satellite. One of the scientific instruments onboard is a miniature radiation monitor telescope RISEPix with two Timepix detectors, developed and built at the Institute of Experimental and Applied Physics, Czech Technical University in Prague. After its successful launch in January 2019, RISESAT joined two other still operational satellites with our Timepix-based radiation monitors, SATRAM onboard the ESA satellite Proba-V (launched in 2013) and the Czech VZLUSAT-1 cubesat (launched 2017). In this work, we present general technical and scientific details about the RIS-ESAT satellite mission and the RISEPix module, and a basic comparison of space weather monitoring from SATRAM and VZLUSAT-1 radiation monitors. K E Y W O R D elementary particles -instrumentation: detectors -ISM: cosmic rays -space vehicles: instruments 1

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Section: Risesatmentioning

confidence: 99%

RISEPix—A Timepix‐based radiation monitor telescope onboard the RISESAT satellite

et al. 2019

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“…Then the angular distance between stars is calculated using Equation 21. The centroiding coordinates two stars ( 1 , 1 ), ( 2 , 2 ) and focal length ( ) in pixels are required to measure angular distance between stars in cos " [40]. In order to evaluate the measurement error of APST the actual angular distance between stars from catalog cos ′ and measured angular distance from image cos ′′ is compared using Equation 22.…”

Section: Angular Distance Measurement Error Analysismentioning

confidence: 99%

Star Selection algorithm for Arcsecond Pico Star Tracker

Muruganandan

Park

Lee

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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The star tracker estimates pointing knowledge of a satellite in arcsecond accuracy in three axes without apriori knowledge. But star trackers are larger in size, heavier, power hungry and expensive for nanosatellite missions. The Arcsecond Pico Star Tracker (APST) is designed based on the limitations of nanosatellites and estimated to provide pointing knowledge in arcsecond. The APST is developed using fully COTS components because it's affordable, and less development time. A theoretical model is developed to estimate the performance of the COTS components (image sensor, lens, and baffle) used in the APST. Using this model, it's possible to validate if the components meet the requirements of the star tracker. But COTS component decreases the overall performance due to the errors in image sensor noise, lens distortion, and aberration etc. In APST, the lens distortion and inaccurate centroiding are the dominant error sources. The radial lens distortion causes an error in angular distance measurement, which leads misidentifying or identification of stars and high processing time. This leads to functional failure of APST. To overcome this, the relative star selection method is iv developed which selects the stars based on the angular distance information. Based on the fact that star pair with low angular distance has minimum measurement error, the relative star selection selects the four stars with low measurement error. It's compared with conventional bright star selection method, whereas stars are selected based on brightness. The relative selection algorithm is tested with 75-star constellation in star simulator and it has delivered 100% success rate and accuracy of 71 arcseconds in boresight. Whereas the conventional bright star selection delivered low success rate of 28% because the star pairs are not selected based on angular distance separation. Hence the relative star selection algorithm is efficient for APST.

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“…7) In this simulation environment, star sensors take images of the monitor and process the position of the stars, and consequently the attitude of the star sensor in the inertial coordinate system. The information processed in the star sensor is sent to the satellite's attitude control unit for further processing.…”

Section: Star Simulatormentioning

confidence: 99%

Low-Cost Simulation and Verification Environment for Micro-Satellites

Kuwahara

Fukuda

Sugimura

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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The Space Robotics Laboratory (SRL) of Tohoku University has been developing micro-satellites for years and has gained experience in their development, verification, integration, and operation. The SRL has recently started the development of model-based simulation, verification, and integration environment to realize rapid and cost-effective development of reliable micro-satellites. The conceptual design and its functionality have been verified through the real-life 50-kg-class micro-satellite projects RISING-2 and RISESAT. The developed environment can be utilized in different configurations such as full-software simulation, hardware-in-the-loop simulation, and even flight operation, depending on demands in each satellite development phase. This environment is designed to be modular and flexible. The minimum hardware configuration can be a single personal computer, which enables low-cost introduction of a satellite system simulator for a wide range of projects in a variety of project phases. It can be utilized for general micro-satellite missions and possibly even much smaller space systems in the future. Micro-satellite RISING-2 is the first satellite tested by means of this environment. Functionality of the developed simulation and verification environment was evaluated by comparing the ground simulation results and flight data obtained by RISING-2.

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System Integration of a Star Sensor for the Small Earth Observation Satellite RISING-2

Cited by 9 publications

References 0 publications

RISEPix—A Timepix‐based radiation monitor telescope onboard the RISESAT satellite

RISEPix—A Timepix‐based radiation monitor telescope onboard the RISESAT satellite

Star Selection algorithm for Arcsecond Pico Star Tracker

Low-Cost Simulation and Verification Environment for Micro-Satellites

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