Accession Number:

ADA136834

Title:

An Open Loop Missile Evasion Algorithm for Fighters

Descriptive Note:

Master's thesis

Corporate Author:

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

Personal Author(s):

Report Date:

1983-11-01

Pagination or Media Count:

128.0

Abstract:

Proportional navigation PN is a guidance law used on many missiles today. Closed loop missile evasion maneuvers for fighters flying against proportional navigation missiles have been investigated, but they all require that the fighter have relative state information that is currently unavailable. An open loop missile evasion algorithm is needed today to allow pilots to best maneuver their aircraft against PN guided missiles to improve the chances of survival. A preliminary investigation of fighter maneuvers revealed the strengths and weakness of particular maneuvers. Maximum g turns and barrel rolls were expected to show little increase in miss distance over a non-maneuvering target. A switchingjinking maneuver proved a good maneuver. A switchingjinking maneuver coupled with a last second bank reversal was thought to be the best evasive maneuver. The computer simulation TACTICS IV was used to simulate fightermissile engagements. From those simulations the miss distance was calculated and used to determine the best fighter maneuver. As expected maximum g turns in any direction and barrel rolls proved to be the worst maneuvers.

Subject Categories:

  • Attack and Fighter Aircraft
  • Statistics and Probability
  • Guided Missile Trajectories, Accuracy and Ballistics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE