Conference Paper

A new nonlinear guidance law formulation for proportional navigation guidance

DOI: 10.1109/VSS.2012.6163500 Conference: 12th International Workshop on Variable Structure Systems (VSS), 2012, At Mumbai


In this paper, a variable structure control technique using simple adaptation law for upper bounds on norm of uncertainties for a non linear proportional navigation guidance law is proposed. The basic system of non linear equations for proportional navigation guidance are presented as a control problem. The target acceleration is considered as an unknown quantity. A variable structure adaptive control law with mismatched uncertainties is designed. The stability of the proposed controller is then established using Lyapunov function. Simulations are carried out to prove the effectiveness of the new control law under various target maneuvering conditions.

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    • "Yoo and Chung [17] proposed a simple adaptation law for obtaining the upper bound on the uncertainties and showed that the method guarantees asymptotic stability of the uncertain systems for which the sliding mode controller is designed. Deb and Viswanath (Jan, 2012) [18] have used a variable structure adaptive control where simple adaptation laws in [17] are used for estimating the upper bound of uncertainties and unknowns including target acceleration while in [19] (Feb, 2012) the authors have used the disturbance observer proposed by Chen [20]. Talole and Phadke (Oct, 2012) [21] proposed a sliding mode and inertial delay based missile guidance where the target acceleration is estimated using the inertial delay control (IDC) proposed by Zhong and Rees [22]. "
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    ABSTRACT: Abstract—The dynamics involving proportional navigation engagement geometry are presented as a system of non linear differential equations. This system of equations forms a control problem where the LOS angle,rate, derivative of LOS rate, miss distance and missile acceleration are considered as states. The controller based on sliding mode control strives to make LOS rate and other states zero. Target acceleration is estimated using disturbance observer. Comparison with existing laws and simulations are carried out to demonstrate efficacy.