A high-speed aircraft entry phase guidance method and system

CN119126578BActive Publication Date: 2025-02-18NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Application Number
CN202411628141.8
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2024-11-14
Publication Date
2025-02-18
Estimated Expiration
2044-11-14

AI Technical Summary

Technical Problem

When high-speed aircraft enter the atmosphere, they are affected by various interference factors, which leads to the challenge of the accuracy and stability of the guidance algorithm, making it difficult to achieve high-precision trajectory tracking and landing.

Method used

Adaptive ultra-twist sliding mode control method is adopted, combining the standard motion equation of the entry section of the high-speed aircraft and the error tracking equation of the reference trajectory, the aircraft trajectory tracking guidance law is designed to achieve continuous control input and eliminate vibration.

Benefits of technology

It realizes high-precision trajectory tracking of the target trajectory in the case of interference, the algorithm converges quickly, and has the advantages of simplicity, robustness and strong adaptability.

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Abstract

The invention discloses a high-speed aircraft entry guidance method and system, belonging to the field of aircraft navigation guidance and control technology, including: in a planetary fixed coordinate system, without considering the planetary rotation motion and flattening, establishing a standard motion equation for the high-speed aircraft entry; establishing an error tracking equation for the high-speed aircraft entry relative to a reference trajectory; using an adaptive hypertorsion sliding mode control method and the error tracking equation for the aircraft entry relative to a reference trajectory, designing a high-speed aircraft trajectory tracking guidance law. The invention has the advantages of simple algorithm, strong robustness and adaptability.
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Citation Information

Patent Citations

  • RLV landing section guidance law acquiring method based on sliding-mode control theory

    CN107102547A

  • Aircraft intelligent trajectory reconstruction reentry guidance method

    CN111351488A