Hostname: page-component-78c5997874-xbtfd Total loading time: 0 Render date: 2024-11-04T00:29:45.428Z Has data issue: false hasContentIssue false
  • English
  • Français

An analytical approach to attitude determination of a spinning satellite

Published online by Cambridge University Press:  04 July 2016

Belur V. Dasarathy
Belur V. Dasarathy*
Affiliation:
School of Automation, Indian Institute of Science, Bangalore
Get access Rights & Permissions [Opens in a new window]

Extract

The attitude of a spinning satellite, specified in terms of the three Eulerian angles, is related to the angular velocity components in body-fixed co-ordinates by three coupled first-order non-linear differential equations. In general, these equations, being complex, are not amenable to analytical techniques. This study presents a new analytical approach to the analysis of these equations by first reducing the problem to the study of a single second-order non-linear differential equation and then establishing its equivalence with a second-order linear differential equation for the case of the satellite spinning with constant angular velocity components. The solution of this equivalent linear equation is then used to obtain the Eulerian angles.

Type
Technical notes
Information
The Aeronautical Journal , Volume 78 , Issue 762 , June 1974 , pp. 256 - 257
Copyright
Copyright © Royal Aeronautical Society 1974 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Jorgenson, P. S. Chapter 2 of Gyroscopes: Theory and design (edited by Savet, P. H.). McGraw-Hill, New York, 1961.Google Scholar
2. Dasarathy, B. V. Analysis of a class of non-linear systems. Journal of Sound and Vibration, Vol 11, No 1, pp 139–144, 1970.Google Scholar