Accession Number:

AD0760125

Title:

Landing Approach Automatic Flight Control System Design via Reduced Order Optimal Control Law

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

• Pfleeger, Jerry D.

Report Date:

1973-06-01

Pagination or Media Count:

89.0

Abstract:

A set of optimal feedback gains is used as a basis for designing a practical longitudinal automatic flight control system for the landing approach task. A procedure is developed to give a good first-cut design. The procedure is systematic and straightforward. The procedure is used to design two control systems for a DC-8 aircraft. In one case it is assumed that pitch, rate, normal acceleration, and longitudinal airspeed are continuously measured on board the aircraft. The second system is similar to the first with the exception that longitudinal airspeed is deleted as one of the measured variables. These systems are compared with a high-performance automatic flight control system that was designed using classical control techniques. The procedure is also used to design two control systems for a hypothetical aircraft with direct lift control capability.

Descriptors:

• *FLIGHT CONTROL SYSTEMS
• *JET TRANSPORT AIRCRAFT
• ADAPTIVE CONTROL SYSTEMS
• EQUATIONS OF MOTION
• FEEDBACK
• LANDING AIDS
• MATHEMATICAL MODELS
• OPTIMIZATION
• THESES

Subject Categories:

• Transport Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE