Method for realizing satellite solar wing sensor layout on the basis of EI (Effective Independence) method

Abstract

The invention discloses a method for realizing a satellite solar wing sensor layout on the basis of an EI (Effective Independence) method. The method comprises the following steps of: through the structural layout characteristics of a satellite solar wing, selecting a plurality of initial measurement points to construct a modal matrix [Phi]; taking the minimum covariance of an estimation error as optimal estimation to construct an independent modal matrix A; carrying out feature value decomposition on the A to extract an order with a high contribution degree as an optimized measurement point; and combining the requirements of the weight and the reliability of a sensor on the solar wing to determine an optimal layout method for a satellite solar wing modal measurement point. By use of the method, the optimal sensor arrangement of solar wing modal in-orbit measurement can be realized, and the implementation of in-orbit modal measurement is guaranteed.

Description

technical field [0001] The invention relates to the field of sensor layout, in particular to a sensor layout method for on-orbit modal measurement of satellite solar wings. Background technique [0002] In order to meet the requirements of high-power and high-resolution tasks, current satellite platforms generally use large-scale and flexible solar cell arrays or extended antennas. These flexible accessories complicate the dynamic characteristics of satellite structures, especially low-frequency characteristics. Therefore, real-time tracking of the solar array structure in space and real-time identification of its dynamic performance are very important, and the sensor layout for the modal identification of the solar wing in my country is at the initial stage. [0003] The current modal measurement sensor layout of satellite solar wings has the following problems: [0004] 1) Due to the limitation of ground test conditions, it is impossible to accurately and reliably display...

AI Technical Summary

Problems solved by technology

[0004] 1) Due to the limitation of ground test conditions, it is impossible to accurately and reliably display the in-orbit status of the solar wing, resulting in high or low reliability in the whole star design process, making the parameters in the sensor layout process inconsistent with the actual situation in orbit, and there is a reliability problem question;

[0005] 2) Lack of sensor layout methods for on-orbit low-frequency measurements of solar wings

Images