Synthesis of Nonlinear Guidance Laws for Missiles with Uncertain Dynamics

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Authors
  1. Rabbath, C.A.
  2. Lechevin, N.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN)
Abstract
This technical memorandum describes a nonlinear guidance law for a single-missile single-target engagement. The guidance relies on the concepts of Lyapunov stability and backstepping, which are constructive methods in nonlinear control theory. The design of the guidance law allows taking into account the nonlinear relative kinematics between the missile and the target, and ensuring ultimate boundedness of the missile-target system trajectories provided the estimation error of the target acceleration is bounded in magnitude. In other words, despite the nonlinear kinematics between the missile and the target, the guidance scheme is guaranteed to result in a relatively small miss distance between the missile and the target. There are two steps in designing the nonlinear guidance law. In the first step, using the fully nonlinear missile-target engagement kinematics, an appropriate Lyapunov function candidate is selected and a state-feedback law is obtained. Closed-loop pole placement using linear matrix inequalities provides an ultimate bound to the maximum allowable miss distance, assuming idealized flight control dynamics; that is, infinitely fast reaction times for the missile. In the second step of the guidance law, the control law is robustified by means of a high-gain backstepping approach, taking into account the uncertain flight control dynamics of the pursuer missile as an uncertain although bounded time constant. Numerical simulations of the nonlinear guidance in closed

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Report Number
DRDC-VALCARTIER-TM-2006-606 — Technical Memorandum
Date of publication
01 Nov 2007
Number of Pages
48
DSTKIM No
CA030358
CANDIS No
528842
Format(s):
CD ROM

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