Design optimization method for spacecraft passive thermal control parameters

Abstract

The invention discloses a design optimization method for spacecraft passive thermal control parameters. The design optimization method comprises the following steps that firstly, statistics is carried out on a thermal control parameter set to be designed and the design scope of the thermal control parameter set, and objective temperatures and the optimum value and the limit range of the objective temperatures are determined; secondly, an objective function is established, the sensitivity of the objective function on the thermal control parameters is analyzed, and the parameters are classified according to sensitivity; then, a sampled optimal sample serves as an initial value, and step-by-step optimization is carried out on the thermal control parameters through a quasi-linear algorithm according to the sensitivity classification; finally, whether an optimized value meets the temperature limitation or not under various thermal working conditions is detected, and if not, a suboptimum sample is selected again to serve as an initial value for optimization until the optimized value meeting the temperature limitation is acquired. The establishing method for the objective function with a weight mean square error, a sensitivity analysis classifying method for multiple working condition mean square errors on the thermal control parameters, the thermal control parameter step-by-step optimizing method and the like are put forward, and the effective optimization design method is provided for improving the cost-effectiveness and reliability of a spacecraft thermal control system to meet the harsh requirements of a current spacecraft.

Description

Technical field: [0001] The invention relates to a method for designing and optimizing passive thermal control parameters of a spacecraft, which belongs to the technical field of spacecraft thermal control. Background technique: [0002] The main task of the thermal control system is to ensure the normal working temperature environment of the spacecraft in orbit, known as the "lifeline of the spacecraft". Therefore, the performance and reliability of the thermal control system directly determine the success or failure of the spacecraft and its working life. For a single-piece developed spacecraft, the thermal control system design technology plays a vital role in every spacecraft development, and it has always been regarded as the core technology of spacecraft thermal control and has been widely concerned and widely Research. [0003] The design idea of ​​"passive thermal control as main and active thermal control as supplementary" is usually adopted in the design of therm...

AI Technical Summary

Problems solved by technology

Although this design optimization method can obtain a thermal control design scheme that meets the temperature requirements, it does not fully exploit the performance potential of passive thermal control due to the strong coupling effect of the designable parameters on the target point temperature.

Images