Spacecraft transient thermal analysis model inversion correction method

Abstract

The invention discloses a spacecraft transient thermal analysis model inversion correction method. The spacecraft transient thermal analysis model inversion correction method comprises the main steps of firstly establishing a spacecraft transient thermal analysis model and counting to-be-corrected heat transfer parameter sets of the model and an uncertainty range of the model; then carrying out random sampling and establishing as well as optimizing original samples; building a transient temperature analysis value and experiment value error objective function, and transforming the function into a fitness function, and correcting the parameter by adopting a loop inversion method which combines a genetic algorithm and a quasi-linear algorithm (BFGS); and finally selecting multiple groups of better results, and carrying out positive optimization by utilizing experimental data unused in the correction so as to obtain a final heat transfer parameter correction value. The invention provides the loop inversion method which combines a universal objective function construction method, the genetic algorithm and the quasi-linear algorithm (BFGS) of the correction method, and a positive optimization method for an approximate optimal result; and the correction precision and correction efficiency of the spacecraft transient thermal analysis model parameter are improved while an inversion false solution is avoided to the greatest extent.

Description

Technical field: [0001] The invention relates to an inversion correction method for a spacecraft transient thermal analysis model, which belongs to the technical field of spacecraft thermal model correction and multi-parameter inversion. Background technique: [0002] Thermal analysis is the core means of spacecraft thermal control optimization design, thermal control performance check, virtual thermal test and on-orbit thermal control strategy planning, and its accuracy is crucial to spacecraft engineering. However, due to the complex geometric structure and material composition of the spacecraft, and the different manufacturing and installation processes of the thermal control components, the heat transfer parameters will change greatly. When establishing a thermal analysis model, the theoretical values ​​of heat transfer parameters formed on the basis of simplification and assumptions often deviate from the actual engineering values, which seriously affects the accuracy o...

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Problems solved by technology

[0004] At present, the research on the correction method of the transient thermal analysis model has just started, and the existing methods still have problems of lack of systematicness and universality, and there is still room for improvement in improving the correction efficiency and correction accuracy, and the inversion results are There is no clear verification method for the false local optimal solution or the global optimal solution

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