0
RESEARCH PAPERS

Quasi-Optimum Control of a Flexible Booster

[+] Author and Article Information
V. Cohen

Grumman Aircraft Engineering Co., Bethpage, N. Y.

B. Friedland

Aerospace Research Center, General Precision, Inc., Little Falls, N. J.

J. Basic Eng 89(2), 273-282 (Jun 01, 1967) (10 pages) doi:10.1115/1.3609595 History: Received August 03, 1966; Online November 03, 2011

Abstract

The problem of minimizing both the in-flight bending moments as well as the terminal drift of a flexible vehicle is considered. The performance criterion

V(T) = 12y2(T)+k2tT M2(ξ)dξ,
where y(T) is the drift, and M is the in-flight bending moment, is selected to achieve a compromise between excessive drift and excessive structural loading. The two-point boundary value problem for the design of the rigid-body control system is solved analytically for the linear, time-varying optimum control law. The flexibility of the vehicle is then accounted for, in a model consisting of two rigid sections hinged together with a torsional spring, by augmenting the rigid-body optimum control law with feedback terms proportional to the vehicle flexure and its rate. The results of a digital computer simulation indicate that the quasi-optimum control law obtained by this technique results in satisfactory performance, while the rigid-body control law is inadequate for a vehicle of moderate flexibility.

Copyright © 1967 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In