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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Quaternion based model for momentum biased nadir pointing spacecraft


    Contributors:

    Published in:

    Publication date :

    2009-12-17


    Size :

    4 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Quaternion Based Optimal Controller for Momentum Biased Nadir Pointing Satellite

    Salahudden / Kumar, Praful / Dwivedi, Vijay Shankar et al. | IEEE | 2020


    Velocity-Free Attitude Stabilization of a Nadir-Pointing Underactuated Rigid Spacecraft

    Frias, Alexander / de Ruiter, Anton H. J. / Kumar, Krishna Dev | AIAA | 2017



    Modeling And Simulation of Spacecraft Pointing Modes Using Quaternion-Based Nonlinear Control Laws

    Bel, Hady / Aly, Amgad M. / Youssef, Ahmed M. et al. | AIAA | 2016