An ultra-low orbit spacecraft aerodynamic configuration optimization method, device, equipment and medium

By using multi-objective optimization based on the NRLMSISE-00 model and the NSGA-III algorithm, the problems of single optimization objective, insufficient adaptability, and poor coordination between configuration and propulsion system in the aerodynamic configuration design of ultra-low orbit spacecraft are solved, and efficient and reliable aerodynamic configuration optimization and long-life design are achieved.

CN121435730BActive Publication Date: 2026-06-09SHANHAI XINGYAO (CHENGDU) TECHNOLOGY CO LTD
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
SHANHAI XINGYAO (CHENGDU) TECHNOLOGY CO LTD
Filing Date
2025-10-31
Publication Date
2026-06-09

AI Technical Summary

Technical Problem

The aerodynamic configuration design of ultra-low orbit spacecraft suffers from problems such as singular optimization objectives, insufficient adaptability of optimization algorithms, low coupling between atmospheric environment and optimization process, lack of collaborative design between configuration and propulsion system, and contradiction between lightweight structure and erosion resistance design, leading to performance imbalance and short on-orbit life.

Method used

A multi-objective optimization function based on the NRLMSISE-00 model is adopted, combined with the NSGA-III algorithm, considering drag coefficient, working propellant capture efficiency, structural weight and antigen oxygen erosion performance. By introducing thruster adaptability screening conditions, the core geometric parameters of the ultra-low orbit spacecraft are optimized, and the optimal aerodynamic configuration is screened through constraint conditions.

Benefits of technology

It enables rapid optimization of aerodynamic configuration, improves on-orbit reliability and lifespan, ensures the performance stability of aerodynamic configuration under different orbital environments and the coordinated operation of propulsion system, and solves the problems of performance imbalance and short lifespan in traditional design.

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Abstract

The application discloses a kind of super low orbit spacecraft aerodynamic configuration optimization method, device, equipment and medium, it is related to spacecraft design field.The method comprises: obtaining target parameter;According to target parameter and NRLMSISE-00 model, calculate real-time atmospheric environment parameter;Based on real-time atmospheric environment parameter, construct multi-objective optimization function;With NSGA-III algorithm, with the minimum drag coefficient, the maximum working medium capture efficiency, the minimum structure weight and the optimal atomic oxygen erosion resistance performance as target, the multi-objective optimization function is solved, and the core geometric parameter of super low orbit spacecraft is obtained;Using constraint condition, core geometric parameter, derivative constraint parameter and material and coating parameter are filtered, and the optimal aerodynamic configuration of super low orbit spacecraft is obtained.The application can realize the rapid optimization of super low orbit spacecraft aerodynamic configuration, and has high reliability and long on-orbit life.
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Citation Information

Patent Citations

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  • Spacecraft, coating and method

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