Design optimization method for spacecraft passive thermal control parameters
An optimization method and parameter design technology, which is applied in the field of spacecraft thermal control, can solve the problems of not fully utilizing the potential of passive thermal control performance, and achieve the effects of improving cost-effectiveness and reliability, improving optimization efficiency, and improving optimization accuracy
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[0035] The present invention proposes a design and optimization method for passive thermal control parameters of a spacecraft, which is based on a stochastic approximation inversion method, with the goal of minimizing the error between the temperature design value and the optimal value, through combined sampling and inversion of multiple thermal control parameters Take into account the coupling changes of multiple parameters, and give full play to the potential of passive thermal control. Specific as figure 1 As shown, a spacecraft passive thermal control parameter design optimization method includes the following steps:
[0036] Step 1. Count the set of thermal control parameters to be designed and their designable range;
[0037] Step 2, determine the target point and its optimum temperature value and limit range;
[0038] Step 3. Construct the target point temperature design value and the optimal value error objective function under multiple working conditions, uniformly ...
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