scholarly journals A Design Method for an Attitude Control System of a Large Satellite Based on I-PD Control

1991 ◽  
Vol 27 (2) ◽  
pp. 242-244
Author(s):  
Shuichi ADACHI ◽  
Takashi SHIGEMASA ◽  
Takashi KIDA
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Design Method ◽  
Attitude Control System ◽  
Pd Control ◽  
Large Satellite

scholarly journals High Accuracy Attitude Control System Design for Satellite with Flexible Appendages

2014 ◽  
Vol 2014 ◽  
pp. 1-6 ◽  
Author(s):  
Wenya Zhou ◽  
Haixu Wang ◽  
Zhengwei Ruan ◽  
Zhigang Wu ◽  
Enmei Wang
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Design Method ◽  
Notch Filter ◽  
Vibration Signal ◽  
High Accuracy ◽  
Frequency Variation ◽  
Attitude Control System ◽  
The Impact ◽  
Flexible Appendages

In order to realize the high accuracy attitude control of satellite with flexible appendages, attitude control system consisting of the controller and structural filter was designed. When the low order vibration frequency of flexible appendages is approximating the bandwidth of attitude control system, the vibration signal will enter the control system through measurement device to bring impact on the accuracy or even the stability. In order to reduce the impact of vibration of appendages on the attitude control system, the structural filter is designed in terms of rejecting the vibration of flexible appendages. Considering the potential problem of in-orbit frequency variation of the flexible appendages, the design method for the adaptive notch filter is proposed based on the in-orbit identification technology. Finally, the simulation results are given to demonstrate the feasibility and effectiveness of the proposed design techniques.

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

Flight performance of the LES-8/9 three-axis attitude control system

1980 ◽  
Author(s):  
F. FLOYD ◽  
C. MUCH ◽  
N. SMITH ◽  
J. VERNAU ◽  
J. WOODS
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Flight Performance ◽  
Attitude Control System

Design of attitude control system for ASRTU microsatellite

2020 ◽  
Vol 28 (10) ◽  
pp. 2192-2202
Author(s):  
Feng WANG ◽  
◽  
Shi-bo NIU ◽  
Cheng-fei YUE ◽  
Fan WU ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System

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.

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