Design and implementation of active Attitude Determination and Control Subsystem for ISRASAT1 cube satellite

2017 ◽  
Author(s):  
Moutaman Mirghani Daffalla ◽  
Asia Saeed Kajo ◽  
Ahmed TagElsir
Keyword(s):  
Attitude Determination ◽  
Control Subsystem ◽  
Design And Implementation ◽  
And Control

Closed Loop Dynamic Testing of The Intelsat V Attitude Determination and Control Subsystem Hardware

1979 ◽  
Vol 12 (4) ◽  
pp. 383-404
Author(s):  
H. Bittner ◽  
E. Brüderle ◽  
Α. Brauch ◽  
H. Pfefferl ◽  
A. Scheit ◽  
...  
Keyword(s):  
Closed Loop ◽  
Attitude Determination ◽  
Dynamic Testing ◽  
Control Subsystem ◽  
And Control

CLOSED LOOP DYNAMIC TESTING OF THE INTELSAT V ATTITUDE DETERMINATION AND CONTROL SUBSYSTEM HARDWARE

1980 ◽  
pp. 383-404 ◽  
Author(s):  
H. Bittner ◽  
E. Brüderle ◽  
A. Brauch ◽  
H. Pfefferl ◽  
A. Scheit ◽  
...  
Keyword(s):  
Closed Loop ◽  
Attitude Determination ◽  
Dynamic Testing ◽  
Control Subsystem ◽  
And Control

scholarly journals Microsatellite Attitude Determination and Control Subsystem Design and Implementation: Software-in-the-Loop Approach

2014 ◽  
Vol 2014 ◽  
pp. 1-12 ◽  
Author(s):  
Ho-Nien Shou
Keyword(s):  
Angular Velocity ◽  
Normal Mode ◽  
Attitude Control ◽  
Attitude Determination ◽  
Control Method ◽  
Measurement Data ◽  
Low Earth Orbit ◽  
Control Subsystem ◽  
Institute Of Technology ◽  
And Control

The paper describes the development of a microsatellite attitude determination and control subsystem (ADCS) and verification of its functionality by software-in-the-loop (SIL) method. The role of ADCS is to provide attitude control functions, including the de-tumbling and stabilizing the satellite angular velocity, and as well as estimating the orbit and attitude information during the satellite operation. In Taiwan, Air Force Institute of Technology (AFIT), dedicating for students to design experimental low earth orbit micro-satellite, called AFITsat. For AFITsat, the operation of the ADCS consists of three modes which are initialization mode, detumbling mode, and normal mode, respectively. During the initialization mode, ADCS collects the early orbit measurement data from various sensors so that the data can be downlinked to the ground station for further analysis. As particularly emphasized in this paper, during the detumbling mode, ADCS implements the thrusters in plus-wide modulation control method to decrease the satellite angular velocity. ADCS provides the attitude determination function for the estimation of the satellite state, during normal mode. The three modes of microsatellite adopted Kalman filter algorithm estimate microsatellite attitude. This paper will discuss using the SIL validation ADCS function and verify its feasibility.

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