On-orbit micro-thrust measurement simulation system of electrostatic suspension accelerometer

By designing an in-orbit microthrust measurement simulation system of electrostatic suspension accelerometer, the real-life simulation problem of satellite microthrust measurement in complex environments is solved, and accurate measurement of satellite microthrust and reduction of orbit errors are achieved.

CN119827797AActive Publication Date: 2025-04-15LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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Patent Information

Application Number
CN202411694428.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-11-25
Publication Date
2025-04-15
Estimated Expiration
2044-11-25

AI Technical Summary

Technical Problem

In complex background environments, the real-life simulation problem of electrostatic suspension accelerometers that are difficult to accurately measure the tiny thrust of satellites.

Method used

Design a microthrust measurement simulation system for an electrostatic suspension accelerometer, including an in-rail parameter simulation device and an electrostatic suspension accelerometer output measurement device. The system generates an on-orbit simulation environment through simulation, including acceleration simulation, noise simulation and satellite attitude simulation, and processes the electrostatic suspension accelerometer output, fuses different sensor data, and performs real-life simulation.

Benefits of technology

Real-life simulation of the single axial measurement of satellite microthrust in orbit was achieved, and key accelerometer design parameters that meet the actual control requirements were obtained, reducing the orbital error to less than 1m, ensuring the accurate measurement of satellite microthrust by the accelerometer.

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Abstract

The invention relates to an on-orbit micro-thrust measurement simulation system of an electrostatic suspension accelerometer, and belongs to the technical field of high-precision acceleration measurement simulation. The system comprises an on-orbit parameter simulation device and an electrostatic suspension accelerometer output measurement device. Wherein the on-orbit parameter simulation device is used for simulating and generating an on-orbit simulation environment of the electrostatic suspension accelerometer, and the on-orbit simulation environment comprises acceleration simulation, noise simulation and satellite attitude simulation; the electrostatic suspension accelerometer output measuring device is used for processing the output of an electrostatic suspension accelerometer, the processing result is divided into two paths, one path serves as primary non-conservative force acceleration data measured by the accelerometer and is fed back to the electrostatic suspension accelerometer, and the other path serves as secondary non-conservative force acceleration data. And the other path is used as the electrostatic force acceleration after the mass block is subjected to the electrostatic force effect and is used for measuring the electrostatic suspension accelerometer.
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