Static unbalance characteristic on-orbit estimation method and equipment of large-inertia rotating component

Abstract

The invention discloses a static unbalance characteristic on-orbit estimation method and equipment of a large-inertia rotating component. A first torque acquisition module acquires a satellite rigid torque, a second torque acquisition module acquires a solar battery flexible torque, a third torque acquisition module acquires an interference torque of a satellite according to the acquired satelliterigid torque and the acquired solar battery flexible torque, and a static unbalance acquisition module acquires a static unbalance amplitude and a static unbalance phase of the large-inertia rotatingcomponent according to the interference torque of the satellite. Through the method disclosed by the invention, the static unbalance state can be efficiently and reliably acquired, the efficiency, the reliability and the stability of a satellite system are greatly improved.

Description

technical field [0001] The invention relates to an on-orbit estimation method and equipment for the static unbalance characteristic of a rotating component with large inertia. Background technique [0002] Usually, satellites are loaded with rotating parts with large inertia, and they are always in a state of constant rotation around a certain axis of the satellite body during in-orbit application. Satellite attitude stability index. [0003] During the ground test, the static unbalance characteristics of the rotating parts are generally identified at the stand-alone level, and then fed back to the control system for angular momentum compensation design and test verification. However, there may be differences between the ground test results and the actual in-orbit situation, the main reasons are as follows: [0004] 1. The test conducted at the stand-alone level only considers the characteristics of the rotating parts themselves, but in fact the satellite is also equipped ...

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Problems solved by technology

[0004] 1. The test conducted at the stand-alone level only considers the characteristics of the rotating parts themselves, but in fact the satellite is also equipped with a single-wing or double-wing solar cell array, which has obvious flexibility and the low-frequency mode shape may be the same as the rotating part's rotation direction. Attitude stability may have additive effects;

[0005] 2. After the satellite is in orbit, the rotating parts may need to be unfolded, and the unfolding has certain uncertainties, which leads to a certain deviation between the ground test data and the in-orbit state;

[0006] 3. In the orbital vacuum environment, the rotating part is exposed to direct sunlight for a long time, and the thermal effect of the material may cause its center of mass to shift, thereby affecting its rotational characteristics;

[0007] 4. Some unidentified reasons on the ground affect the rotation characteristics of the rotating parts

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