In-orbit measuring system and method for deformation of satellite large-array-plane antenna based on fiber grating

Abstract

The invention provides an in-orbit measuring system for deformation of a satellite large-array-plane antenna based on a fiber grating. The system comprises a light wave generator 1, multiple grating measuring points 3, a light wave demodulator 4 and an information processor 5 which are connected successively via a conduction fiber 2; the light wave generator 1 comprises a main light source and a splitter, and provides light wave needed by the multipath conduction fiber; the multiple grating measuring points 3 are arranged on the surface of the satellite large-array-plane antenna, and used for forming a sensing network; the light wave demodulator is used to demodulate the collected light wave, and further obtains the strain and temperature of each grating sensing point; and the information processor 5 is used to calculate the strain and temperature of each grating sensing point, and obtains the deformation parameter of the surface of the antenna array plane. The invention also provides an in-orbit measuring method for deformation of the satellite large-array-plane antenna based on the fiber grating. Thus, convenience is provided for antenna structure control or signal compensation, and improves the anti-interference performance of satellite imaging.

Description

technical field [0001] The invention relates to the technical field of aerospace satellites, in particular to an on-orbit measurement system and method for satellite large-array antenna deformation based on fiber gratings. Background technique [0002] For high-resolution remote-sensing satellites, due to the influence of alternating sunshine and seasons, the temperature environment of the satellite structure fluctuates greatly, and its large-array antennas are deformed, resulting in flatness that cannot meet the requirements for use, affecting satellites in orbit. imaging performance. Therefore, it is necessary to measure the deformation of the satellite array antenna, so as to realize further antenna structure control or signal compensation according to the deformation, so that the anti-jamming performance of satellite imaging can be improved. Contents of the invention [0003] Aiming at the defects in the prior art, the object of the present invention is to provide an ...

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Problems solved by technology

[0002] For high-resolution remote-sensing satellites, due to the influence of alternating sunshine and seasons, the temperature environment of the satellite structure fluctu

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