Title

Time Optimal Attitude Control Of Asymmetric Rigid Spacecraft

Keywords

Bang-bang; Rest-to-rest; Time optimal control

Abstract

Time optimal rest-to-rest reorientation of a rigid spacecraft with an arbitrary initial attitude and distinct principal moments of inertia is discussed. The effect of the gyroscopic coupling terms in Euler's equations on the control switch times is shown. 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

1-1-1996

Publication Title

JVC/Journal of Vibration and Control

Volume

2

Issue

1

Number of Pages

17-32

Document Type

Article

Personal Identifier

scopus

DOI Link

https://doi.org/10.1177/107754639600200102

Socpus ID

0030081611 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/0030081611

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