SDS-4 Attitude Control System: In-Flight Results of Three Axis Attitude Control for Small Satellites

2013 ◽  
Vol 46 (19) ◽  
pp. 283-288 ◽  
Author(s):  
Y. Nakajima ◽  
N. Murakami ◽  
T. Ohtani ◽  
Y. Nakamura ◽  
K. Hirako ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Small Satellites

scholarly journals Optimal Control for Combined Energy Storage and Attitude Control System (CEACS) in Small Satellites

2011 ◽  
Vol 110-116 ◽  
pp. 3587-3592 ◽  
Author(s):  
Ban Ying Siang ◽  
Renuganth Varatharajoo
Keyword(s):  
Control System ◽  
Energy Storage ◽  
Attitude Control ◽  
Control Methods ◽  
Attitude Control System ◽  
H Infinity ◽  
Small Satellites ◽  
Satellite Attitude Control ◽  
H Infinity Control ◽  
Control Modules

The combined energy storage and attitude control system (CEACS) combines both energy storage and attitude control modules via the flywheel technology. Previously only the conventional control methods were tested for CEACS. In this paper, H2 and H-infinity control methods are implemented in CEACS. The satellite attitude control performances show that both control options can be employed for a good attitude pointing accuracy. (Abstract)

scholarly journals Closed Relative Trajectories for Formation Flying with Single-Input Control

2012 ◽  
Vol 2012 ◽  
pp. 1-20 ◽  
Author(s):  
Anna Guerman ◽  
Michael Ovchinnikov ◽  
Georgi Smirnov ◽  
Sergey Trofimov
Keyword(s):  
Control System ◽  
Relative Motion ◽  
Attitude Control ◽  
Shape Control ◽  
Formation Flying ◽  
Linear Equations ◽  
Attitude Control System ◽  
Small Satellites ◽  
Orbit Control ◽  
Input Control

We study the problem of formation shape control under the constraints on the thrust direction. Formations composed of small satellites are usually subject to serious limitations for power consumption, mass, and volume of the attitude and orbit control system (AOCS). If the purpose of the formation flying mission does not require precise tracking of a given relative trajectory, AOCS of satellites may be substantially simplified; however, the capacity of AOCS to ensure a bounded or even periodic relative motion has to be studied first. We consider a formation of two satellites; the deputy one is equipped with a passive attitude control system that provides one-axis stabilization and a propulsion system that consists of one or two thrusters oriented along the stabilized axis. The relative motion of the satellites is modeled by the Schweighart-Sedwick linear equations taking into account the effect ofJ2perturbations. We prove that both in the case of passive magnetic attitude stabilization and spin stabilization for all initial relative positions and velocities of satellites there exists a control guaranteeing their periodic relative motion.

Double Fail-Safe Attitude Control System for Artificial Meteor Microsatellite ALE-1

2021 ◽  
Vol 19 (1) ◽  
pp. 9-16
Author(s):  
Shinya FUJITA ◽  
Yuji SATO ◽  
Toshinori KUWAHARA ◽  
Yuji SAKAMOTO ◽  
Yoshihiko SHIBUYA ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Fail Safe
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