Formally Verified Run Time Assurance Architecture of a 6U CubeSat Attitude Control System

2016 ◽  
Author(s):  
Kerianne H. Gross ◽  
Matthew Clark ◽  
Jonathan A. Hoffman ◽  
Aaron Fifarek ◽  
Kuldip Rattan ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Run Time

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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