Accession Number:

ADA055417

Title:

Pitch Rate Flight Control for the F-16 Aircraft to Improve Air-To-Air Combat.

Descriptive Note:

Master's thesis,

Corporate Author:

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

Personal Author(s):

Report Date:

1977-12-01

Pagination or Media Count:

79.0

Abstract:

Digital simulations were developed to implement a pitch rate control system for the F-16 aircraft engaged in aerial gunnery. First, the EASY Modelling and Analysis Program by Boeing Computer Services was adapted to implement a longitudinal axis F-16 aircraft, flight control system, and pilot model. Comparison of closed loop system responses indicated a proposed pitch rate flight control configuration would improve target tracking performance. The Terminal Aerial Weapon Delivery Simulation TAWNDS program by McDonnell Douglas Corporation was adapted for the F-16 aircraft. An non-linear six-degree-of-freedom aircraft model, multi-axis flight control system, and multi-axis pilot model were developed to demonstrate target tracking capabilities. Eight different air-to-air scenarios were developed to simulate evasive encounters with a F-4 target aircraft. Time history target tracking errors indicated the improved tracking performance of the proposed pitch rate flight control configuration over the present normal acceleration configuration of the F-16 aircraft. Author

Subject Categories:

  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE