Star-tracker-based, all-sky, autonomous attitude determination

1993 ◽  
Author(s):  
Luisa DeAntonio ◽  
Gabriel Udomkesmalee ◽  
James W. Alexander ◽  
Randel C. Blue ◽  
Edwin W. Dennison ◽  
...  
Keyword(s):  
Attitude Determination ◽  
Star Tracker

CCD star tracker for attitude determination and control of a satellite for a space VLBI mission

1996 ◽  
Author(s):  
Kazuhide Noguchi ◽  
Koshi Sato ◽  
Ryouichi Kasikawa ◽  
Naoto Ogura ◽  
Keiken Ninomiya ◽  
...  
Keyword(s):  
Attitude Determination ◽  
Star Tracker ◽  
And Control

Attitude Measurement Low Frequency Error Identification and Compensation for Star Tracker with Gyros

2014 ◽  
Vol 664 ◽  
pp. 298-303
Author(s):  
Yu Wang Lai ◽  
De Feng Gu ◽  
Jun Hong Liu ◽  
Wen Ping Li ◽  
Dong Yun Yi
Keyword(s):  
Attitude Determination ◽  
Low Frequency ◽  
Euler Angle ◽  
High Accuracy ◽  
Star Tracker ◽  
Attitude Motion ◽  
Frequency Error ◽  
Attitude Measurement ◽  
Novel Approach ◽  
Critical Problems

The low-frequency error (LFE) of star tracker is the most critical problems in the high accuracy attitude determination for the satellite. In this paper a novel approach is proposed to identify and compensate the attitude measurement LFE of the star trackers. The main difficulty in the attitude LFE identification is to distinguish the attitude LFE from the attitude motion. To overcome this difficulty, the gyro data, which is sensitive to the attitude motion, was used to fit the measurement attitude data to obtain the reference attitude. It is shown that, the LFE can be identified by comparing the measurement attitude and the reference attitude. The attitude LFE repeated feature is characterized well by the proposed method. By utilizing the orbital repeated feature, the LFE of the star trackers can be estimated. Finally, a LFE compensation strategy is presented base on the LFE estimation results. The validity and efficiency of the proposed approach are demonstrated by the relative Euler angle results from two test star trackers on-board the STECE satellite.

In-orbit results from the attitude determination and control system of ALSAT-2B

2021 ◽  
pp. 1-26
Author(s):  
H. Benzeniar
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Determination ◽  
Lessons Learned ◽  
Control Mode ◽  
Star Tracker ◽  
Orbit Control ◽  
Space Agency ◽  
Pyramidal Configuration ◽  
And Control

ABSTRACT The Algerian Space Agency has been active in the field of microsatellite engineering for more than 15 years and has successfully developed microsatellites under several know-how transfer technology programs, six to date. This paper presents the flight results and lessons learned from the attitude determination and control system (ADCS) flown on the ALSAT-2B satellite, an Earth observation microsatellite, by analysing the behaviour of the satellite from the initial attitude acquisition through the coarse pointing mode then the nominal mode, where the payload is first tested, and finally the orbit control mode. The spacecraft was launched on 26 September 2016 and placed into a 670km Sun-synchronous orbit with a solar local time at an ascending node of 22:15. The ADCS performance presented here mainly focuses on the launch and early operation results. ALSAT-2B includes four reaction wheels in a pyramidal configuration, three gyros, three Sun sensors, three magneto-torquers, one magnetometer, and one star tracker for agile and accurate attitude control. In addition, a propulsion system based on four 1N hydrazine thrusters is also used on board the microsatellite. The main new development in this platform compared with previous ones of the same type is the fusion of the star tracker and measurements by the three gyroscopes into one gyrostellar estimator that was implemented for the first time on ALSAT-2B, and the pyramidal configuration of the wheels, aiming to increase the angular momentum. The results obtained from the early launch operations for different ADCS modes are very encouraging and fulfil all the requirements set during design and testing. Currently, the satellite has accomplished its fourth year in orbit and is still operational and producing high-quality images.

scholarly journals Real Sky Tests of Star-Tracker-Based Attitude Determination System for Earth Pointing Spacecraft

2008 ◽  
Vol 56 (657) ◽  
pp. 480-491
Author(s):  
Takanori IWATA ◽  
Eiji HIROKAWA ◽  
Hiroki HOSHINO ◽  
Takeshi YOSHIZAWA ◽  
Koshi SATO ◽  
...  
Keyword(s):  
Attitude Determination ◽  
Star Tracker ◽  
Determination System
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