Accession Number : ADA020094
Title : Results of Some Investigations of Differential Gain Theory Applied to Air-to-Air Systems. Volume IV. Intercepting an Accelerating Target Using Quasi-Optimal Control for Air-to-Air Systems.
Descriptive Note : Final rept. Mar 74-Apr 75,
Corporate Author : CALIFORNIA UNIV LOS ANGELES SCHOOL OF ENGINEERING AND APPLIED SCIENCE
Personal Author(s) : Eide,Henry F.
Report Date : AUG 1975
Pagination or Media Count : 50
Abstract : The technique of quasi-optimum control, developed by B. Friedland is applied to the problem of intercepting an accelerating target with an air launched missile. The problem is first stated as an optimal control problem with non-linear system equations and a quadratic cost functional. Several techniques of finding feedback type optimal controls which have been developed by solving various approximations to the original problem are then described. None of these techniques makes explicit use of a measurement of lateral target acceleration. Three control techniques are then developed which use measurements of target acceleration to develop closed form controls. The first control is found by solving a linearized version of the original problem. The other two controls are quasi-optimum controls which use the solution of the linearized problem to obtain a new feedback type solution that is more nearly optimal for the original problem. Based on performance in simulations of typical attack geometries and target maneuvers, these three control techniques are found to be superior to previous techniques.
Descriptors : *Air to air missiles, *Interception probabilities, Control theory, Guided missile trajectories, Aerodynamic control surfaces, Vector analysis, Optimization, Miss distance, Feedback, Nonlinear differential equations
Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
Air- and Space-launched Guided Missiles
Air Navigation and Guidance
Distribution Statement : APPROVED FOR PUBLIC RELEASE