Solar array modal thruster-excitation model simulation method

Abstract

The invention discloses a solar array modal thruster-excitation model simulation method. The method comprises the following steps: step 1, starting; step 2, analyzing air injection characteristics of a thruster; step 3, establishing a satellite module; step 4, applying an air injection force to a model to perform kinetic analysis; step 5, determining whether to excite a needed modal; step 6, applying a new air injection combination; and step 7, outputting the result. According to the solar array modal thruster-excitation model simulation method, in-orbit solar array modal excitation can be achieved by utilizing the thruster, and implementation of the in-orbit solar array modal excitation is ensured.

Description

technical field [0001] The invention relates to a solar array mode, in particular to a model simulation method for thruster excitation of the solar array mode. Background technique [0002] The mode identification of satellite solar arrays in orbit adopts the thruster excitation for attitude and orbit control. The identification experiment in the early stage of orbit operation is a kind of safety must be considered, that is, the impact on spaceborne missions must be controlled to a minimum and fully considered. Therefore, it is hoped to adopt an incentive method that can not only control the risk to a minimum, but also effectively achieve experimental identification in a steady state as much as possible. [0003] At present, the model simulation method of solar array modal thruster excitation has the following problems: 1. In the solar array on-orbit modal parameter excitation method, the characteristics of the excitation source are unknown in the time domain or frequency; ...

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Problems solved by technology

[0003] At present, the model simulation method of solar array modal thruster excitation has the following problems: 1. The solar array on-orbit modal parameter excitation method, the characteristics of the excitation source are unknown in the time domain or frequency; State identification requires real-time performance, and at the same time, the complexity and randomness of the excitation source must be considered; limited by ground test conditions, the in-orbit state of the solar wing cannot be accurately and reliably displayed, resulting in high or low reliability during the design process, making the process parameters Inconsistent with the actual situation in orbit, there are reliability problems; 2. Lack of model simulation methods for solar array modal thruster excitation

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