Energy-momentum-wheel for satellite power and attitude control systems

2000 ◽  
Author(s):  
Mukund Patel
Keyword(s):  
Control Systems ◽  
Attitude Control

Control moment gyroscopes for spacecraft attitude control systems: Current status and prospects

2015 ◽  
Vol 6 (3) ◽  
pp. 236-240 ◽  
Author(s):  
A. R. Mkrtychyan ◽  
N. I. Bashkeev ◽  
D. O. Yakimovskii ◽  
D. I. Akashev ◽  
O. B. Yakovets
Keyword(s):  
Control Systems ◽  
Attitude Control ◽  
Current Status ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment ◽  
Control Moment Gyroscopes

scholarly journals Design of High Pointing Accuracy NPSAT-1 Satellite Attitude Systems of Armature Controlled DC Motor with utilization for PD Controller

2020 ◽  
Vol 12 (1) ◽  
pp. 145-156
Author(s):  
M. RAJA ◽  
O. PRAKASH
Keyword(s):  
Control System ◽  
Control Systems ◽  
Attitude Control ◽  
Settling Time ◽  
Pd Controller ◽  
Reference Orbit ◽  
Satellite Attitude ◽  
Satellite Attitude Control ◽  
Leo Satellites ◽  
Pointing Accuracy

An Attitude control system plays the important role to maintain the satellite to desired attitude orientations. The intended application of NANO satellite in low earth orbits (LEO) helps find transient responses with and without controllers. LEO satellites typically orbit at an altitude ranging between160-2000 km. LEO satellites are widely used for remote sensing, navigation, and military surveillance applications. The Nano NPSAT-1 satellite attitude control systems (ACS) are described in this research work. The high pointing accuracy attitude estimation and feedback control systems are presented. The design specifications have been taken to meet the accuracy requirements (desired value ≤ 0.2 seconds) of Nano satellite attitude control. The feedback signal from on-board sensors compared with reference orbit trajectory and implementation of the Proportional Derivative (PD) controller is constructed. An algorithm of Nano satellite (NPSAT-1) attitude control is implemented using MATLAB Tools. In addition, the closed loop poles help find the gain of the system using Root Locus (RL) methods. The satellite control system is used to improve the transient response like overshoot and settling time of the system. Thus, the design of attitude control to improve the rise time, the settling time, the maximum overshoot, and no steady state error was carried out.

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