Accession Number:

ADA151946

Title:

A Modern Control Design Methodology with Application to the CH-47 Helicopter.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s):

• Holdridge,R. D.

Report Date:

1985-01-01

Pagination or Media Count:

249.0

Abstract:

A control system design methodology is developed in this dissertation which produces robust, low-order optimal controllers for multiple-input multiple-output systems. The methodology attempts to focus the strengths of recent Modern Control design algorithms on the problems associated with real control system designs. The methodology is a set of procedures which aids the engineer in creating a realizable controller in either digital or analog form. To demonstrate the usefulness of the methodology, two control augmentation systems CAS were designed and flight tested on a CH-47 helicopter at NASA Ames Research Center. The first design was a longitudinal cruise CAS giving the pilot decoupled control of forward velocity and climb rate. This design task demonstrated the low-order controller and robustness features of the methodology. It also demonstrated the use of modern control techniques in designing integral-error controllers. Flight test results are presented. The second controller is a translational velocity commandprecision hover hold system. This two mode controller demonstrates the methodology as applied to a more complicated design task which includes control law switching and inner loopouter loop considerations. Flight test results are also presented. Originator-supplied keywords include Thesis.

Descriptors:

• *FLIGHT CONTROL SYSTEMS
• *COMPUTER AIDED DESIGN
• FLIGHT TESTING
• OPTIMIZATION
• PITCH(MOTION)
• DEMONSTRATIONS
• AUGMENTATION
• THESES
• HELICOPTERS
• DECOUPLING
• FLIGHT INSTRUMENTS
• INPUT OUTPUT DEVICES
• SWITCHING

Subject Categories:

• Flight Control and Instrumentation
• Computer Hardware
• Cybernetics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE