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
Descriptors:
Subject Categories:
- Attack and Fighter Aircraft