Adaptive matched augmented proportional navigation

a proportional navigation and adaptive matching technology, applied in the field of missile guidance, can solve the problem of inability to obtain a consistent accurate estimate of t.sub.go

Inactive Publication Date: 2001-08-07
AIR FORCE UNITED STATES
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Problems solved by technology

This is due to the fact that a consistently accurate estimate of t.s...

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Embodiment Construction

The invention is disclosed in a WL / MN Interim Report dated Dec 1993, to the advanced medium range air-to-air missile (AMRAAM) System Program Office, entitled "Bank-To-Turn In-House Control Study", with limited distribution authorized for Dec. 17, 1993, and in a paper entitled "Adaptive Matched Augmented Proportional Navigation" which is in the restricted Proceedings of the AIAA Missile Sciences Conference, Monterey, Calif., Nov 1994. Copies of the report and paper are included herewith as part of the application as filed, and are hereby incorporated by reference.

Perhaps the most challenging of all guidance and control problems is that of a modern tactical air-to-air missile in pursuit of a highly maneuverable aircraft. The problem consists of the estimation of target motion, the generation of guidance commands to optimally steer the missile toward target intercept, and the control of the coupled, nonlinear, multivariable, uncertain dynamics of the air-to-air missile. Each portion of...

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Abstract

Two new adaptive homing guidance laws are developed which are variants of Augmented Proportional Navigation (PRONAV). The first guidance law commands flight path angle rate and is referred to as adaptive matched augmented PRONAV (AMAAP). The second guidance law commands linear acceleration and is referred to as adaptive matched augmented linear PRONAV (AMALP). The major attributes of these guidance laws are (1) they are the solutions of a linear quadratic control problem, (2) they do not require an estimate of time-to-go (t.sub.go), (3) they are matched to a nonlinear model of the target's motion, (4) they adapt in real time to provide optimal guidance over each small segment of the intercept trajectory, and (5) they optimally account for missile deceleration.

Description

BACKGROUND OF THE INVENTIONThe present invention relates generally to missile guidance.The traditional approach to missile guidance is to use Proportional Navigation (PRONAV). PRONAV was developed by C. Yuan at RCA Laboratories during World War II using physical intuition [1]. The resulting simplistic guidance law states that the commanded linear acceleration a.sub.c is proportional to the line-of-sight (LOS) rate .sigma..sub.T. The proportionality constant can be broken down into the product of the effective navigation ratio N times the relative missile-target closing velocity Vc,Two decades later, the quasi-optimality of PRONAV was derived [2]. The prefix quasi is used here because of all the assumptions that must be made in deriving PRONAV as a solution of a linear-quadratic optimal control problem [3]. These assumptions are as follows:1. The target has zero acceleration.2. The missile has perfect response and complete control of its acceleration vector.3. The missile is launched...

Claims

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Application Information

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IPC IPC(8): F41G7/20F41G7/22G05D1/12
CPCF41G7/2246G05D1/12
Inventor CLOUTIER, JAMES R.
Owner AIR FORCE UNITED STATES
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