A Computer Based System for On-Ground Testing of the Attitude Control System of Small Satellites**Presented at COSPAR Colloquium on Small Scientific Microsatellites: Microsatellites as Research Tools, 14–17 December, 1997, National Cheng Kung University, Tainan, Taiwan. © 1997 by authors. All rights reserved.

1999 ◽  
pp. 307-313
Author(s):  
V. Alexandrov ◽  
M. Ovchinnikov ◽  
D. Bugrov ◽  
S. Lemak ◽  
S. Mirer ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Small Satellites ◽  
Ground Testing ◽  
Computer Based ◽  
Research Tools

scholarly journals Design, Ground Testing and On-Orbit Performance of a Sun Sensor Based on COTS Photodiodes for the UPMSat-2 Satellite

Sensors ◽  
2021 ◽  
Vol 21 (14) ◽  
pp. 4905
Author(s):  
Angel Porras-Hermoso ◽  
Daniel Alfonso-Corcuera ◽  
Javier Piqueras ◽  
Elena Roibás-Millán ◽  
Javier Cubas ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Response Curve ◽  
The Sun ◽  
Space Systems ◽  
Attitude Control System ◽  
Ground Testing ◽  
Sun Sensor ◽  
Early Results ◽  
Red Leds

This paper presents the development of the UPMSat-2 sun sensor, from the design to on-orbit operation. It also includes the testing of the instrument, one of the most important tasks that needs to be performed to operate a sensor with precision. The UPMSat-2 solar sensor has been designed, tested, and manufactured at the Universidad Politécnica de Madrid (UPM) using 3D printing and COTS (photodiodes). The work described in this paper was carried out by students and teachers of the Master in Space Systems (Máster Universitario en Sistemas Espaciales—MUSE). The solar sensor is composed of six photodiodes that are divided into two sets; each set is held and oriented on the satellite by its corresponding support printed in Delrin. The paper describes the choice of components, the electrical diagram, and the manufacture of the supports. The methodology followed to obtain the response curve of each photodiode is simple and inexpensive, as it requires a limited number of instruments and tools. The selected irradiance source was a set of red LEDs and halogen instead of an AM0 spectrum irradiance simulator. Some early results from the UPMSat-2 mission have been analyzed in the present paper. Data from magnetometers and the attitude control system have been used to validate the data obtained from the sun sensor. The results indicate a good performance of the sensors during flight, in accordance with the data from the ground tests.

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.

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
Sign in / Sign up

Export Citation Format

Share Document