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Canon Electronics Inc. developed its third microsatellite to demonstrate optical systems and in-house developed components in orbit. The 35 kg microsatellite CE-SAT-IIB can capture night-time color images of moon lit earth surface as well as city lights with a newly-designed camera using an ultra-high sensitivity image sensor developed by Canon. CE-SAT-IIB was launched in October 2020 as a payload on the Rocket LabsElectron15and has been performing experiments to validate optical systems and the bus using in-house components. CE-SAT-IIB has three types of cameras. The first camera is a 20 cm Cassegrain telescope with the ultra-high sensitivity detector previously described. Exposure is controllable through shutter speed, CMOS gain, and ND filters. The sensitivity is equivalent to approximately 4 million in ISO by maximizing the gain and detaching all the ND filters. Focus can be adjusted via a stepper motor on the detector, and observable area is approximately 3.5 km x 2.3 km on the ground with theoretical ground sampling distance (GSD) 5m from a 500 km orbit. The second camera is 8.7 cm Cassegrain telescope with a commercial off-the-shelf (COTS)detector using24.2 MP CMOS sensor. Exposure is controllable through shutter speed and ISO, and focus can be adjusted by controlling the temperature of the telescope. The Effective focal length of this camera is809 mm, which enables to capture ground images of approximately 5.6 km x 3.7kmwith theoretical GSD2.3m. The third camera is also a COTS compact digital camera. Exposure is controllable through shutter speed, ISO, and F-number. In addition, adjustable focal length provides wide range of images from approximately 215 km x 145 km to 645 km x 435km in ground distance. The bus of CE-SAT-IIB mainly consists of in-house components such as sun aspect sensors, a geomagnetic aspect sensor, an inertial reference unit, a star tracker, magnetorquers, and reaction wheels to shorten the delivery time and guarantee quality for mass-manufacturing. All of these components have worked as designed in orbit, and the satellite has achieved 3-axis attitude control such as ground tracking, and inertial pointing. Canon Electronics has demonstrated three sizes of Cassegrain telescopes and validated two size of bus systems by CE-SAT-I and CE-SAT-IIB. We are going to start providing high quality telescopes, detectors, bus systems, components, and integrated satellite systemin a short delivery time.

第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎, 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan, In this study, an inner-cylinder-replaceable rotating detonation rocket engine is tested in a vacuum environment for various inner-cylinder radii r(sub i) ranging from 31 mm (typical lab scale) to 0 mm (no inner cylinder). As a result, it was clarified that there exists a critical inner-cylinder radius to sustain adequate thrust performance in the engine. Detonation waves attached to the inner-cylinder wall for r(sub i) = 23 and 31 mm (supercritical cases), whereas detachment of detonation waves from the inner-cylinder wall was observed for r(sub i) = 0 and 9 mm (subcritical cases), and 15 mm (critical case). In the cases of r(sub i) = 0, 9 mm (subcritical), and 15 mm (critical), strong chemical luminescence was observed significantly in the exhaust plume. For r(sub i) = 15 mm (critical cases), and 23 and 31 mm (supercritical cases), the measured specific impulses were greater than 80% of theoretical values. However, for r(sub i) = 0 and 9 mm (subcritical cases), the measured specific impulses were below 80% of the theoretical values. This is to be attributed to the imperfect detonation combustion observed significantly in the subcritical cases. From these results, we have concluded that the inner-cylinder radius is, at 15 mm, close to the critical condition to keep rotating detonation waves in a favorable state in the combustor., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830029005, レポート番号: JAXA-SP-18-005

平成29年度衝撃波シンポジウム (2018年3月7日-9日. 東北大学片平さくらホール ）仙台市, 宮城県, (2018年3月7日-9日. 宇宙航空研究開発機構角田宇宙センター ）角田市, 宮城県, Symposium on Shock Waves in Japan, FY2017 (March 7-9, 2018. Sakura Hall), Sendai, Miyagi, (March 7-9, 2018. Kakuda Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC)), Kakuda, Miyagi, 資料番号: SA6000119049, レポート番号: 1C3-5【若】