The derivation of the equations describing the vibration of a flexible spacecraft is presented in the context of a perturbation method permitting a maneuver strategy independent of the vibration control. A straightforward open-loop minimum-time rotational maneuver strategy is developed for the spacecraft regarded as a rigid body. Actuator dynamics are considered in the formulation. A maneuver force distribution is developed which excites the least amount of elastic deformation of the flexible parts of the spacecraft. An efficient technique for simulating structural vibrations during a maneuver is presented. Numerical results demonstrate the maneuver strategy and highlight the vibration caused by rotational maneuvers.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Equations for the vibration of a slewing flexible spacecraft


    Contributors:

    Publication date :

    1986-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Slewing and Vibration Control of a Nonlinear Flexible Spacecraft

    Malekzadeh, M. / Naghash, A. / Talebi, H.A. | Tema Archive | 2010


    Time-optimal slewing of flexible spacecraft

    BEN-ASHER, JOSEPH / BURNS, JOHN A. / CLIFF, EUGENE M. | AIAA | 1992