Abstract

A discrete variable structure control (DVSC) with sliding vector is presented to track the velocity and acceleration command for a hypersonic cruise missile. In the design an integrator is augmented to ensure the tracking with zero steady-state errors. Furthermore the sliding surface of acceleration is designed using the error of acceleration and acceleration rate to avoid the singularity of control matrix. A proper power rate reaching law is utilized in this proposal; therefore the state trajectory from any initial point can be driven into the sliding surface. Besides, in order to validate the robustness of controller, the unmolded dynamic and parameter disturbance of the missile are considered. Through simulation the proposed controller demonstrates good performance in tracking velocity and acceleration command.

Highlights

  • Hypersonic vehicle has attracted attention because of its potential military and civil application [1,2,3,4,5,6,7]

  • This paper presents a design method of hypersonic cruise missile autopilot using discrete variable structure control

  • The cowl of scramjet is arranged in the mandible of hypersonic cruise missile

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Summary

Introduction

Hypersonic vehicle has attracted attention because of its potential military and civil application [1,2,3,4,5,6,7]. The sliding variable structure control shows its advantage in robustness to the disturbance [11,12,13,14] Using this method, Xu et al [4] presented an adaptive sliding mode control for hypersonic aircraft with nonlinear and model uncertainty. In case there is uncertainty, neural network based hypersonic flight control research could be found in literatures [14,15,16,17] These literatures have satisfactory effect for a continuous plant, the computer on board always works discontinuously, and controller on the basis of continuous system cannot offer the same performance by a digital computer with a certain sampling interval. This paper presents a design method of hypersonic cruise missile autopilot using discrete variable structure control.

Model of Hypersonic Cruise Missile
Design of Variable Structure Controller
Simulations
Conclusion
Full Text
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