Design and Verification of Attitude and Orbit Control System Based on Integrated Electronic Technology for Micro-small Satellite

2018 ◽  
pp. 95-101
Author(s):  
Wenlan Tang
Keyword(s):  
Control System ◽  
Small Satellite ◽  
Electronic Technology ◽  
Orbit Control

On-orbit control system performance of the ROSAT spacecraft

1991 ◽  
Vol 25 (8-9) ◽  
pp. 487-495 ◽  
Author(s):  
M. Bollner
Keyword(s):  
Control System ◽  
System Performance ◽  
Orbit Control

Design of Semi-Physical Simulation for Small Satellite by Virtual Display

2011 ◽  
Vol 130-134 ◽  
pp. 2684-2687 ◽  
Author(s):  
Kai Xu ◽  
Yan Lv ◽  
Guang Jin
Keyword(s):  
Control System ◽  
Real Time ◽  
Attitude Control ◽  
Physical Simulation ◽  
Simulation System ◽  
Space Environment ◽  
Small Satellite ◽  
Attitude Control System ◽  
Actual Environment ◽  
Virtual Display

Semi-physical simulation of attitude control system is the more synthetically test and verify for designing of small satellite control system. It is an important means of small satellite development. However, the results of current semi-physical simulation system have a lot of non-intuitive. Compare with the actual environment, the simulation environment still has striking disparity. So the shortcomings affect precision of simulation. Based on the virtual display technology, the group semi-physical simulation system has been constructed for attitude control of small satellite due to the combination with xPC real-time environment, the simulation computer, high-precision single-axis air-bearing turntable, reaction wheel, air thrust device, fiber gyroscopes, sensors synchronizer, power subsystem and wireless devices virtual display computer etc. Semi-physical simulation achieved the visual simulation in orbit and tracked new information of virtual environment of space into real-time simulation computer. Simulation results show that the simulation system for real-time attitude and orbit position of small satellite semi-physical simulation has an excellent display effect. At the same time, Real-time transfuse of orbit information provides a more accurate space environment simulation. The simulation system of small satellite attitude control to design and evaluate the more direct and convenient.

scholarly journals Optimal Factorization of the State-Dependent Riccati Equation Technique in a Satellite Attitude and Orbit Control System

2021 ◽  
Vol 20 ◽  
pp. 98-107
Author(s):  
Alessandro Gerlinger Romero ◽  
Luiz Carlos Gadelha De Souza
Keyword(s):  
Control System ◽  
Riccati Equation ◽  
The State ◽  
Linear Control ◽  
Control Techniques ◽  
Orbit Control ◽  
Satellite Attitude ◽  
Modified Rodrigues Parameters ◽  
State Dependent ◽  
Attitude Maneuver

The satellite attitude and orbit control system (AOCS) can be designed with success by linear control theory if the satellite has slow angular motions and small attitude maneuver. However, for large and fast maneuvers, the linearized models are not able to represent all the perturbations due to the effects of the nonlinear terms present in the dynamics and in the actuators (e.g., saturation). Therefore, in such cases, it is expected that nonlinear control techniques yield better performance than the linear control techniques. One candidate technique for the design of AOCS control law under a large maneuver is the State-Dependent Riccati Equation (SDRE). SDRE entails factorization (that is, parameterization) of the nonlinear dynamics into the state vector and the product of a matrix-valued function that depends on the state itself. In doing so, SDRE brings the nonlinear system to a (nonunique) linear structure having state-dependent coefficient (SDC) matrices and then it minimizes a nonlinear performance index having a quadratic-like structure. The nonuniqueness of the SDC matrices creates extra degrees of freedom, which can be used to enhance controller performance, however, it poses challenges since not all SDC matrices fulfill the SDRE requirements. Moreover, regarding the satellite's kinematics, there is a plethora of options, e.g., Euler angles, Gibbs vector, modified Rodrigues parameters (MRPs), quaternions, etc. Once again, some kinematics formulation of the AOCS do not fulfill the SDRE requirements. In this paper, we evaluate the factorization options (SDC matrices) for the AOCS exploring the requirements of the SDRE technique. Considering a Brazilian National Institute for Space Research (INPE) typical mission, in which the AOCS must stabilize a satellite in three-axis, the application of the SDRE technique equipped with the optimal SDC matrices can yield gains in the missions. The initial results show that MRPs for kinematics provides an optimal SDC matrix.

Attitude Determination and Control System for a LEO Debris Chaser Small Satellite

2022 ◽  
Author(s):  
Raunak Srivastava ◽  
Roshan Sah ◽  
Kaushik Das
Keyword(s):  
Control System ◽  
Attitude Determination ◽  
Small Satellite ◽  
And Control

System Analysis Graphic Instruments Application in Satellites On-Board Attitude and Orbit Control System Software Development

2016 ◽  
Vol 7 (8) ◽  
pp. 373-382
Author(s):  
N. V. Ryabogin ◽  
◽  
M. А. Shatsky ◽  
M. U. Kosinsky ◽  
V. N. Sokolov ◽  
...  
Keyword(s):  
Control System ◽  
Software Development ◽  
System Analysis ◽  
System Software ◽  
Orbit Control

Development, Test and Flight of the SMART-1 Attitude and Orbit Control System

2005 ◽  
Author(s):  
Per Bodin ◽  
Stan Berge ◽  
Martin Bjork ◽  
Anders Edfors ◽  
Joakim Kugelberg ◽  
...  
Keyword(s):  
Control System ◽  
Orbit Control
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