By Topic

Nonlinear Study of an Attitude Control System for Orbital Space Vehicles

Sign In

Cookies must be enabled to login.After enabling cookies , please use refresh or reload or ctrl+f5 on the browser for the login options.

Formats Non-Member Member
$31 $13
Learn how you can qualify for the best price for this item!
Become an IEEE Member or Subscribe to
IEEE Xplore for exclusive pricing!
close button

puzzle piece

IEEE membership options for an individual and IEEE Xplore subscriptions for an organization offer the most affordable access to essential journal articles, conference papers, standards, eBooks, and eLearning courses.

Learn more about:

IEEE membership

IEEE Xplore subscriptions

2 Author(s)
Crow, R.K. ; Autonetics, A Division of North American Aviation Inc. 3330 East Anaheim Road, Box Y-1 Anaheim, California ; Horwitz, H.P.

For the present decade it appears the most precise and accurate technique for attitude control of space vehicles consists of actuation with momentum devices. The majority of investigations using this form of attitude control generally assume a zero motor lag, linearized approximation of the equations of motion and control, elimination of the first order gyroscopic cross-coupling effects, and complete indiference to the second order gyroscopic cross-coupling effects. In some cases these assumptions are justified; in other cases they are not. This investigation is concerned with precise three-axis attitude control of an orbital space vehicle. The equations of motion are general and designed to encompass many of the parameters that will influence an orbital space flight and will not be constrained by specific vehicle geometry, construction, orientation or trajectory. The primary source of actuation is a set of three orthogonal reaction wheels which provide control torques and integrate the disturbance torques along each axis. Because of the gyroscopic effects of the rotating masses an interdependency exists between the various axes. The extent of these effects are investigated. In addition to wheel control, the system features a reaction jet system for desaturation of the wheel momentum when any wheel has reached a prescribed maximum speed. Significant points investigated are: 1. The problem of reaction wheel motor damping and its effect on the system steady state and transient behavior 2. The effectiveness of first and second order decoupling in reducing gyroscopic coupling between axes 3.

Published in:

Aerospace and Navigational Electronics, IEEE Transactions on  (Volume:Technical_Paper ,  Issue: 0 )