Accession Number:

ADA155107

Title:

Flight Control System for a Computer Controlled Aircraft with Limited Sensors.

Descriptive Note:

Technical note,

Corporate Author:

AIR FORCE ACADEMY CO

Personal Author(s):

Report Date:

1985-04-30

Pagination or Media Count:

63.0

Abstract:

The Department of Electrical Engineering at the United States Air Force Academy is attempting, through one of its senior design courses, to design, build, and fly a computer controlled aircraft. The Department of Aeronautics was asked to help design the flight control system to be implemented by the on-board digital computer. The project involved building and testing a wind tunnel model of the aircraft to determine its aerodynamic characteristics, performing mass tests on the actual aircraft to determine inertia characteristics, developing a 12 degree-of-freedom nonlinear aircraft simulation computer program, and designing the actual flight control system. This report describes only the last task. A complete flight control system for a small computer controlled aircraft was designed using only yaw rate, heading, lateral load factor, airspeed, altitude, and rate of climb feedback. This multi-input multi-output control problem was done using the classical root locus technique on a linearized system model. The simulation results revealed surprisingly good performance, considering the limitation on sensors. Additional keywords charts Fortran equations of motion kinematic equations.

Subject Categories:

  • Flight Control and Instrumentation
  • Computer Programming and Software
  • Computer Hardware

Distribution Statement:

APPROVED FOR PUBLIC RELEASE