Accession Number:

ADA164516

Title:

Multivariable Output Control Law Design for the STOL (Short Takeoff and Landing) F-15 in Landing Configuration.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1985-12-01

Pagination or Media Count:

294.0

Abstract:

Using the MULTI computer aided design and simulation program, multivariable, output feedback digital control laws are designed for the F-15 STOL aircraft in the landing configuration. The STOL F-15 landing configuration includes canards and reversible thrust in addition to conventional F-15 control surfaces. The additional controls allow decoupling of the output variables in the longitudinal plane. Longitudinal aircraft dynamics, derived from data provided by the prime contractor, McDonnell-Douglas, are presented in linearized state space form for the design procedure. Control laws are developed to stabilize the aircraft to perform longitudinal landing maneuvers flight path control and flare at six flight conditions. The design encompasses actuator dynamics, computational delay, sensor dynamics, sensor noise, and plant nonlinearities. Proportional plus integral controller designs for each flight condition demonstrate good time response characteristics. Designs of two of the flight conditions are sufficiently insensitive to plant variations to be used at all but one of the remaining flight conditions. The technique of multivariable output feedback, with the MULTI program provides good robust designs for the STOL F-15. Keywords Proportional integral control Aircraft landings Jet fighters. Theses

Subject Categories:

  • Military Aircraft Operations
  • Flight Control and Instrumentation

Distribution Statement:

APPROVED FOR PUBLIC RELEASE