A missile adaptive control law design method suitable for navigation precision degradation

By eliminating uncertainties and external disturbances caused by the decrease in navigation accuracy through adaptive control laws, an adaptive control law for missiles was designed to ensure system stability and robustness, and to achieve accurate navigation of missiles in complex environments.

CN116224787BActive Publication Date: 2026-09-11NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Application Number
CN202310055400.1
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-01-20
Publication Date
2026-09-11
Estimated Expiration
2043-01-20

AI Technical Summary

Technical Problem

Existing technologies are insufficient to effectively address the uncertainties and external disturbances in aircraft systems caused by decreased navigation accuracy, leading to system instability and potential accident risks.

Method used

An adaptive control law was designed. By establishing a six-degree-of-freedom model of the missile, an adaptive compensation term was introduced to eliminate the uncertainties of the system's external disturbances and its own inherent uncertainties. The adaptive control law and Lyapunov function design method were used to ensure the system's stability.

Benefits of technology

It achieves system stability and robustness even with decreased navigation accuracy, effectively tracks the desired trajectory, and reduces the impact of system uncertainty.

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Abstract

The application relates to a missile adaptive control law design method suitable for navigation precision reduction, and belongs to the controller field. The application firstly establishes a six-degree-of-freedom model of a missile; secondly introduces disturbance and uncertainty of a system into the system model; and finally designs a control law and an adaptive law, and eliminates the influence of uncertain external disturbance and inherent uncertainty of the system by introducing an adaptive compensation term. The application has simple design, better robustness for controller parameters, and can well eliminate uncertain external errors caused by navigation precision reduction of the missile and inherent uncertainty.
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