AbstractIn this paper, we propose a quaternion based spacecraft model that describes the nadir pointing spacecraft with momentum wheel under gravity gradient torque disturbance. This state space model uses only three components of the quaternion. From this nonlinear model, we derive a linearized state space model for the spacecraft system. We show that unlike all existing quaternion models, this linearized state space model is fully controllable. Therefore, all modern control system design methods can be directly applied to the attitude control system design for momentum biased nadir pointing spacecraft.
Quaternion based model for momentum biased nadir pointing spacecraft
Aerospace Science and Technology ; 14 , 3 ; 199-202
2009-12-17
4 pages
Article (Journal)
Electronic Resource
English
Quaternion based model for momentum biased nadir pointing spacecraft
Online Contents | 2010