Accession Number:

ADA301281

Title:

The Optimal Central Guidance of Medium Range Air-to-Air Missile,

Descriptive Note:

Corporate Author:

NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1995-09-25

Pagination or Media Count:

26.0

Abstract:

In recent years, the development of high speed microcomputers makes it possible to apply optimal control theory to the missile guidance system. Although, numerous research papers have been published on this subject, hardly any of them deal with the concept of central guidance control. Here, an optimal central guidance principle that satisfies the needs of missiles with various speeds and guiding time is proposed. The major purpose of central guidance control is to guide the missile and enable it to maintain an optimal geometric position in relation to its target as soon as the target is locked on to by the missile head guidance. In order to reach the necessary maximum gravity force, the missile must have a certain minimum velocity which is contingent upon targets maximum gravity force, height and distance between them. For distant and low altitude targets the major factor is missile speed. Its better to use a central guidance that can maximize the residual speed of the missile. For closer targets, the timing is very important, since the missile has to destroy the target before it launches a counter attack. Therefore, central guidance control that can minimize the intercepting time has to be applied. By solving the boundary value of nonlinear equations, these guidance rules can be obtained. Here, we will introduce the mathematical model of medium range air to air missiles, and discuss guidance principles of self searching. At the end, we will introduce the central guidance principle.

Subject Categories:

  • Computer Hardware
  • Air- and Space-Launched Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE