This chapter addresses the attitude dynamics of rigid spacecraft. Attitude dynamics consists of two parts: attitude kinematics and attitude kinetics. Both of these aspects of attitude dynamics are discussed in this chapter. The stability analyses presented in the chapter range from torque‐free motion of both axisymmetric and asymmetric spacecraft to gravity‐gradient satellites. Stability in torque‐free rotation is necessary in order to maintain an equilibrium state in the presence of small torque perturbations arising out of the neglected dynamics when deriving Euler's equations. The stability analysis detailed in the chapter has revealed an important result, namely that it is possible to have a stable rotational state of a rigid spacecraft by spinning it about either the major axis or the minor axis. The chapter describes the procedures for deriving solution for precession and nutation rates.
Dokumentinformationen
Attitude Dynamics
Foundations of Space Dynamics ; 285-322
2021-02-01
38 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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| Springer Verlag | 2022
Springer Verlag | 2007
| Wiley | 2015
| SLUB | 1986
| TIBKAT | 1986