This chapter presents several introductory concepts of attitude manoeuvres commonly used by spacecraft. The attitude of a spacecraft is described by the orientation of the body‐fixed principal frame (oxyz) with the axes i1, I2, I3, respectively. The torque impulse causes an instantaneous change in the angular momentum, equal to the value of the torque at the instant of impulse application, and is therefore said to produce an impulsive manoeuvre. The repeated use of an attitude thruster‐based reaction‐control system for manoeuvring a spacecraft entails a large propellant expenditure. Since the cost of a space mission greatly depends upon the propellant mass to be carried by the spacecraft, a saving of the propellant by employing other means of attitude manoeuvring is much sought after. One such method is the use of rotors mounted on the spacecraft.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Attitude Manoeuvres


    Contributors:

    Published in:

    Publication date :

    2021-02-01


    Size :

    15 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




    Optimal Trajectory Attitude Manoeuvres for Lunar Missions

    Ercoli Finzi, A. / Vasile, M. / International Astronomical Federation | British Library Conference Proceedings | 1998


    Satellite attitude slew manoeuvres using inverse control

    McInnes, C.R. | Online Contents | 1998


    Optimal sliding mode controllers for spacecraft attitude manoeuvres

    Pukdeboon, C. / Zinober, A.S.I. | Tema Archive | 2009


    Non-Linear Control for Large Angle Attitude Slew Manoeuvres

    McInnes, C. R. | British Library Online Contents | 1997