Ground-based all-physical principle verification test method for separate microsatellites

Abstract

The invention provides a ground all-physical principle verification test method for a separated micro-satellite. The method comprises the following steps: preparation is made for a ground all-physicalprinciple verification test of the separated micro-satellite before the test; after preparation before the test is completed, a two-cabin unlocking test is completed on a double-three-degree-of-freedom air floating platform, and whether the two cabins can be effectively unlocked or not is judged; under the condition that the two cabins can be effectively unlocked, an inter-cabin cable disturbancetest is completed on the double-three-degree-of-freedom air floating platform, and the cable disturbance between the two cabins and the control effect of the two cabins in a cable existence state arejudged; and according to the cable disturbance size and the control effect between the two cabins obtained by the inter-cabin cable disturbance test, a magnetic levitation control full-physical three-loop control test is completed on the double-three-degree-of-freedom air floatation platform, and a final separation type micro-satellite ground full-physical principle verification test is completed. According to the active air floatation design, three-degree-of-freedom omnibearing attitude control verification of the load cabin and the platform cabin is realized through the air feet.

Description

technical field [0001] The present invention relates to the field of spacecraft design, in particular to a method for verifying the ground full physics principle of a separated micro-satellite, and more specifically to a process design for a separate micro-satellite ground full-physics principle verification test. Background technique [0002] Space solar observation, high-resolution earth remote sensing and other tasks put forward high requirements on the stability of satellite platforms. However, ordinary satellites are interfered by flexible parts such as solar panels and movable parts such as flywheels, so they cannot meet the stability requirements of space scientific observations. The high-performance separate microsatellite installs the sun observation load on the suspension board, which is physically isolated from the platform interference source. [0003] In the above background, this patent proposes a design of a separate micro-satellite ground full physical princ...

AI Technical Summary

Problems solved by technology

However, ordinary satellites are interfered by flexible parts such as solar panels and movable parts such as flywheels, so they cannot meet the stability requirements of space scientific observations.

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