Helicopter flight attitude tracking control method and system based on explicit model prediction

Through the method based on explicit model prediction, the track change characteristics of the helicopter's flight attitude are extracted, the attitude regulation index is calculated, the yaw node is identified, the attitude tracking status is checked, and the flight attitude is adjusted. The stability problem of the helicopter's flight attitude under the influence of multi-dimensional factors is solved, and the efficient attitude regulation and stability improvement is achieved.

CN119759068AActive Publication Date: 2025-04-04CHINA NATIONAL AIRCRAFT GENERAL AVIATION CO LTD
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Patent Information

Application Number
CN202510273842.2
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-03-10
Publication Date
2025-04-04
Estimated Expiration
2045-03-10

AI Technical Summary

Technical Problem

Under the influence of multi-dimensional factors, the stability of the helicopter's flight attitude decreases, resulting in a time-space deviation of the flight attitude, making it difficult to achieve effective attitude regulation.

Method used

The helicopter flight attitude tracking control method based on explicit model prediction is adopted. By obtaining the flight attitude record of the target helicopter, the track change characteristics are extracted, the time and space correlation components of the attitude node are calculated, the attitude regulation is performed based on the track change characteristics, the attitude regulation index is obtained, the yaw node is identified, the attitude tracking status is checked, and the flight attitude is adjusted to reduce errors.

Benefits of technology

Under the influence of multi-dimensional factors, the helicopter flight attitude is effectively regulated, the posture stability is improved, the time and space deviation is reduced, and the robustness under various operating conditions is enhanced.

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Abstract

The present application provides a helicopter flight attitude tracking control method and system based on explicit model prediction, which extracts the track change characteristics of the target helicopter during flight; extracts the time-related components and space-related components of each attitude node from the flight attitude record of the target helicopter, controls the attitude of the attitude node according to the time-related components and space-related components corresponding to the attitude node in combination with the track change characteristics to obtain the attitude control index of the target helicopter at each attitude node; determines the attitude bias information of the target helicopter based on all the attitude control indexes; and adjusts the flight attitude of the target helicopter based on the attitude error cost determined by the attitude bias information. The above scheme tracks and adjusts based on the attitude error cost, and can achieve control of the flight attitude of the target helicopter under the influence of multi-dimensional factors, thereby improving the stability of the flight attitude of the target helicopter.
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