In-orbit engine plume data acquisition method based on gyroscope data

Abstract

The invention discloses an in-orbit engine plume data acquisition method based on gyroscope data. The method comprises the steps of building normal three-axis stabilization attitudes of a spacecraft, adopting a momentum wheel to be an actuator for controlling three axes and a magnetic torquer for unloading, adopting attitude sensors such as a gyroscope and an infrared or star sensor for determining attitude, identifying a starting control point and air injection time of an engine involved in a test, preparing before work of the engine, such as starting a heater and starting a latching valve, recording data output by the gyroscope, analyzing test results, and analyzing disturbing force and moment generated during air injection of the engine according to the gyroscope data and quality characteristics of the spacecraft. According to the in-orbit engine plume data acquisition method based on the gyroscope data, plume data acquisition of the in-orbit engine under high vacuum and real environment is achieved.

Description

Technical field [0001] The invention belongs to the technical field of spacecraft attitude and orbit control, and relates to an on-orbit engine plume data acquisition technology, in particular a plume acquisition technology based on gyro data. Background technique [0002] Spacecraft are generally equipped with a variety of engines to achieve attitude control and orbital control, such as attitude adjustment, orbital maneuvering, etc. The plume injected during engine operation may hit the surface of the spacecraft to produce disturbing power and torque, which will affect the attitude control of the spacecraft. Accuracy or orbital control accuracy, and even more serious effects, such as loss of control. Studies have shown that to correctly evaluate the effect of plume on spacecraft, it is first necessary to accurately describe the engine vacuum plume field. There are two main methods to study the vacuum plume field: numerical simulation method and experimental research method. Th...

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Problems solved by technology

[0007] The shortcomings of the above-mentioned relevant literature are: the numerical simulation results only focus on the optimization of the simulation algorithm. Although the simulation results provided by foreign literature are compared, there is a lack of engineering test data support; the ground test method only simulates the space environment within 100km , using measuring equipment such as pressure sensors, and spacecraft generally operate in a high-vacuum environment of 300km or more, the space environment is different from that within 100km, and the ground test conditions do not meet the high-vacuum environment of spacecraft in-orbit operation

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