Comparison of Inverse Optimal and Tuning Functions Designs for Adaptive Missile Control

Sonneveldt, L.; Oort, E. R. van; Chu, Q.P.; Mulder, J.A.

doi:10.2514/1.31316

Cited by 20 publications

(13 citation statements)

References 9 publications

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“…[5][6][7] These design methods need, however, function approximators for constructing the unknown dynamic model, 6,7 and optimization processes for adapting these control systems. 8,9 Sliding mode control is a method that forces the state trajectories of a dynamic system to slide along a predefined subspace of the state space, within which a sliding mode can be realized and the equilibrium can be reached. 10 Alternatively, model-free adaptive control approaches are worth well to be investigated for fault-tolerant flight control.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Adaptive Flight Control Using Incremental Approximate Dynamic Programming and Output Feedback

Zhou

Kampen

Chu

2017

Journal of Guidance, Control, and Dynamics

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A self-learning adaptive flight control for nonlinear systems allows a reliable, faulttolerant and effective operation of complex flight vehicles in a dynamic environment. Approximate dynamic programming provides a model-free control design for nonlinear systems with complex design processes and non-guaranteed closed-loop convergence properties. Linear approximate dynamic programming systematically applies a quadratic cost-togo function and greatly simplifies the design process of approximate dynamic programming. This paper presents a newly developed self-learning adaptive control method called incremental approximate dynamic programming for nonlinear unknown systems. It combines the advantages of linear approximate dynamic programming methods and incremental control techniques to generate a near-optimal control without a priori knowledge of the system model. In this paper, two incremental approximate dynamic programming algorithms with the direct availability of full states and with only the availability of system outputs have been developed. Both algorithms have been applied to a nonlinear aerospace related simulation model. The simulation results demonstrate that both model-free adaptive control algorithms improve the closed-loop performance of the nonlinear system, while keeping the design process simple and systematic as compared to conventional approximate dynamic programming algorithms.

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Section: Introductionmentioning

confidence: 99%

Nonlinear Adaptive Flight Control Using Incremental Approximate Dynamic Programming and Output Feedback

Zhou

Kampen

Chu

2017

Journal of Guidance, Control, and Dynamics

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“…An inverse optimal adaptive attitude tracking controller was proposed in [4] for rigid spacecraft with external disturbances and a constant uncertain inertia matrix. In [8], an inverse optimal adaptive backstepping technique is applied to the design of a pitch control law for a surface-to-air nonlinear missile model with a constant inertia matrix [2]. In [1], and [2], the authors initially developed an inverse optimal adaptive controller for an Euler-Lagrange system with full state feedback, then extended their result to output feedback type using a nonlinear filter based approach.…”

Section: Introductionmentioning

confidence: 99%

Inverse optimal adaptive output feedback control of Euler-Lagrange systems: A variable structure observer based approach

Aksoy

Zergeroğlu

Tatlıcıoğlu

2015

2015 54th IEEE Conference on Decision and Control (CDC)

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Abstract-This work focuses on inverse optimal, observer based output feedback control of Euler-Lagrange systems. Specifically a variable structure observer based output feedback controller is proposed which aside from ensuring asymptotic position tracking also ensures that a positive cost function, penalizing control input performance, is minimized. Simulation studies performed on a two link planar robot manipulator are included to illustrate the overall performance and feasibility of the proposed controller.

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“…An inverse optimal adaptive attitude tracking controller is developed in [10] for rigid spacecraft with external disturbances and a constant uncertain inertia matrix. In [11], an inverse optimal adaptive backstepping technique is applied to the design of a pitch control law for a surface-to-air nonlinear missile model with a constant inertia matrix. However, these previous IOACs are developed for classes of systems where the dynamics can be expressed in a specific form to facilitate the development of a CLF.…”

Section: Introductionmentioning

confidence: 99%

“…In general, the input gain matrix j({) must be known. Systems with a constant inertia matrix, such as the applications in [10] and [11], can easily be transformed into (1), unlike systems with an uncertain state-dependent inertia matrix or uncertainty in the input matrix.…”

Section: Introductionmentioning

confidence: 99%

Inverse optimal adaptive control of a nonlinear Euler-Lagrange system, part I: Full state feedback

Dupree

Patre

Johnson

et al. 2009

Proceedings of the 48h IEEE Conference on Decision and Control (CDC) Held Jointly With 2009 28th Chinese Control Conference

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A sufficient condition to solve an optimal control problem is to solve the Hamilton-Jacobi-Bellman (HJB) equation. However, finding a value function that satisfies the HJB equation for a nonlinear system is challenging. Inverse optimal control is an alternative method to solve the nonlinear optimal control problem by circumventing the need to solve the HJB equation. Inverse optimal adaptive control techniques have been developed that can handle structured (i.e., linear in the parameters (LP)) uncertainty for a particular class of nonlinear systems that do not include Euler-Lagrange systems with an uncertain time-varying inertia matrix. In this paper, an inverse optimal adaptive controller is developed to asymptotically minimize a meaningful performance index while the generalized coordinates of a nonlinear Euler-Lagrange system asymptotically track a desired time-varying trajectory despite LP uncertainty. A Lyapunov analysis is provided to examine the stability of the developed optimal controller, and preliminary simulation results illustrate the performance of the controller.

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Comparison of Inverse Optimal and Tuning Functions Designs for Adaptive Missile Control

Cited by 20 publications

References 9 publications

Nonlinear Adaptive Flight Control Using Incremental Approximate Dynamic Programming and Output Feedback

Nonlinear Adaptive Flight Control Using Incremental Approximate Dynamic Programming and Output Feedback

Inverse optimal adaptive output feedback control of Euler-Lagrange systems: A variable structure observer based approach

Inverse optimal adaptive control of a nonlinear Euler-Lagrange system, part I: Full state feedback

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