Modeling and Simulation of Active Attitude Control for Satellites
One of the most important problem in satellite design is that of attitude stabilization and control, which is the combination of mathematics, dynamics, and control theory. Basic types of control systems are spin control, where the entire satellite is spun, dual-spin control, where the major porti...
Saved in:
| Main Author: | |
|---|---|
| Format: | Thesis |
| Language: | English English |
| Published: |
2004
|
| Subjects: | |
| Online Access: | http://psasir.upm.edu.my/id/eprint/252/1/549509_FK_2004_64.pdf |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| Summary: | One of the most important problem in satellite design is that of attitude stabilization and
control, which is the combination of mathematics, dynamics, and control theory. Basic
types of control systems are spin control, where the entire satellite is spun, dual-spin
control, where the major portion spun while only the payload despun, three-axis active
control, where the major part of satellite despun, and gravity gradient control.
Different attitude control strategies of satellite in Low Earth Orbit (LEO) are presented in
this thesis as well as their simulation with the MATLAB® software. Firstly the linear
mathematical model of the satellite is derived for the gravity gradient (GG) control
method, which represents a passive control design. The advantages of this control method
are long life, simplicity of design, no mass or energy expenditure, and low cost. The
simulation results show the main disadvantage of this technique, which is a marginally
stable response of the satellite to initial conditions. In other words, a poor pointing
accuracy with respect to the orbiting reference frame. The second phase of this thesis focuses on the design of a control algorithm used to damp the satellite oscillations around
its equilibrium position with a simple hardware setting added to the satellite. The system
stability of the model has been checked by using Routh Hurwitz method. The
mathematical model of the new system is developed and simulation about the roll and
yaw axes are realized. A consequent amelioration in the satellite response can be
observed |
|---|