A trajectory planning method and system for high-efficiency active observation of a non-cooperative target with strong security

By using state gain reachability set and fast model predictive control, the active observation trajectory of non-cooperative targets is planned, which solves the problems of navigation error ellipsoidal diffusion and long observation period in traditional methods, improves safety and concealment, and achieves efficient observation of non-cooperative targets.

CN120029286BActive Publication Date: 2026-05-15HARBIN INST OF TECH
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Patent Information

Application Number
CN202510145109.2
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2025-02-10
Publication Date
2026-05-15
Estimated Expiration
2045-02-10

AI Technical Summary

Technical Problem

Traditional on-orbit servicing methods rely on the orbital trajectory generated by the periodic solution of the HCW equation, which leads to the spread of navigation error ellipsoids, increases the risk of spacecraft collisions, and results in long observation mission cycles and poor information concealment, making it difficult to meet the requirements of high concealment.

Method used

By determining the safe observation ellipsoid using state gain reachability set theory and combining it with fast model predictive control, the active observation trajectory of non-cooperative targets is planned to avoid entering the safe observation ellipsoid. Target information is acquired during single-loop circling, and the trajectory planning model is optimized to reduce collision risk and improve stealth.

Benefits of technology

It significantly shortens the observation mission cycle, improves the safety and stealth of the observation mission, reduces the risk of spacecraft collisions, and enables efficient and safe observation of non-cooperative targets.

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Abstract

The application is directed to the non-cooperative target observation task with large navigation information error and low update frequency, thereby a strong security efficient non-cooperative target active observation trajectory planning method is provided, and the application relates to the field of spacecraft orbit optimization technology. The state gain reachable set is calculated from the navigation initial error by the matrix differential equation, and the spacecraft structure size compensation is carried out, the boundary of the safety strategy is taken as the path inequality constraint, the optimization model with the path fuel consumption and the path length as the composite performance index, the optimization variable is the observation path state and the corresponding control, and the trajectory planning model is established comprehensively, and then the model prediction control is used to solve the optimization problem, so as to obtain the corresponding path state. The application is suitable for the trajectory planning of the non-cooperative target active observation in the space orbit optimization.
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