Abstract

Hypersonic technology plays an important role in prompt global strike. Because the flight dynamics of a hypersonic vehicle is nonlinear, uncertain, and highly coupled, the controller design is challenging, especially to design its guidance and control law during the attack of a maneuvering target. In this paper, the sliding mode control (SMC) method is used to develop the guidance law from which the desired flight path angle is derived. With the desired information as control command, the adaptive neural control in discrete time is investigated ingeniously for the longitudinal dynamics of the hypersonic missile. The proposed guidance and control laws are validated by simulation of a hypersonic missile against a maneuvering target. It is demonstrated that the scheme has good robustness and high accuracy to attack a maneuvering target in the presence of external disturbance and missile model uncertainty.

Highlights

  • The hypersonic missile can propel the development of the prompt global strike

  • The geometry of an idealized interception in which the missile and the target are closing on each other at constant speed is shown in Figure 1, where M is hypersonic missile, T is target, VM and γM are the speed and path angle of the hypersonic missile, VT and γT are the speed and path angle of the target, r is the distance between the hypersonic missile and the target, and λ is the line of sight (LOS)

  • The neural network (NN) has learned the dynamic characteristics of the hypersonic missile

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Summary

Introduction

The hypersonic missile can propel the development of the prompt global strike. Controller design is crucial in making it feasible. The guidance and control law of a hypersonic missile attacking a maneuvering target instead of a ground stationary target are discussed. It is a more challenging task owing to the uncertainties of target maneuvers. In [16], an adaptive sliding mode guidance law designed for intercepting a maneuvering target is proposed. It is robust in the presence of disturbances and parameter perturbations and is able to eliminate chattering.

Hypersonic Vehicle Modeling
Guidance Law Design
System Transformation
Strict-Feedback Formulation
Discrete-Time Controller Design
Simulation
Conclusion and Future Work
Full Text
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