Title

Minimum Time Reorientation Of An Arbitrary Rigid Body

Abstract

The nature of time optimal rotations of a rigid spacecraft with distinct principal moments of inertia is discussed. In particular, the effect of the gyroscopic coupling terms in Euler's equations on the control switch times is discussed. A method for recursively generating coefficients for a truncated Taylor series solution of Euler's equations and the differential equations for the Euler parameter state transition matrix is shown. These solutions are used to solve for the optimal control switch times.

Publication Date

12-1-1993

Publication Title

Advances in the Astronautical Sciences

Volume

85

Issue

pt 3

Number of Pages

1889-1903

Document Type

Article; Proceedings Paper

Identifier

scopus

Personal Identifier

scopus

Socpus ID

0027718836 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/0027718836

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