Design of Linear Flight Control Systems Using Optimal Control Theory

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Report Number: ASD TDR 63-376
Author(s): Rynaski, E. G., Reynolds, P. A., Shed, W. H.
Corporate Author(s): Cornell Aeronautical Laboratory, Inc.
Laboratory: Air Force Flight Dynamics Laboratory
Corporate Report Number: IH-1648-F-1
Date of Publication: 1964-04
Pages: 138
Contract: AF 33(657)-7498
DoD Project: 8225
DoD Task: 822501
Identifier: AD0600694

Abstract:

This report describes a study of the application of optimal control techniques based on a generalized performance index to the primary control system design of an X-15-type aircraft and a large flexible booster.

The following aspects of the application of optimal theory were studied:

1. The use of mathematical models to obtain desirable transient characteristics.

2. Realizability of feedback configurations.

3. A comparison between optimal and conventional design techniques.

4. Relationships between the weighting factors of the perfomance index and the dynamics of the optimal system.

5. The use of an IBM 7090 program to obtain optimal solutions of the control problems



Provenance: Bombardier/Aero

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