Impact Time Guidance Law against Maneuvering Targets Using Sliding Mode Control

Document Type : Research Article

Authors

1 Department of Electrical and Computer Engineering, khaje nasir University.

2 Department of Mechanical Engineering, emam hosein university.

3 faculty of electrical engineering, tarbiat modares university

4 Department of Aerospace Engineering, Imam Hossein University.

Abstract

Controlling the impact time of missiles to the target has great importance in applications such as the cooperative attack of multiple missiles since multiple missiles can be reached a specified point simultaneously. This paper presents a sliding mode based guidance law, to control the impact time against maneuvering targets. At first, by selecting an appropriate switching surface and using nonlinear engagement dynamics, a new sliding mode control has been designed which, the sufficient conditions of its stability are derived using the Lyapunov stability theorem. The sliding surface has been selected such that the line of sight rate and the error of the time to go converge to zero at the same time. By considering the nonlinear dynamic equations of maneuvering targets, this will guarantee to impact the target at the desired time. Unlike the other similar methods, our proposed method does not need the assumptions of small flight path angle and stationary target. Using an engagement simulation model, the effectiveness of the proposed method is shown for different scenarios (static and maneuvering targets) and different impact times. In the end, the comparison results with two similar methods are also presented.
 

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References

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Amirkabir Journal of Mechanical Engineering
Volume 53, Issue 2
May 2021
Pages 913-922

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