Determination Method of Thrust Vector Eccentricity of Spacecraft Electric Thruster

Abstract

The present invention discloses a determination method of spacecraft electric thruster thrust vector eccentricity. The determination method is characterized by adopting a plume measurement device and an electric thruster, using the plume measurement device to measure the ion current distribution of the electric thruster, obtaining the spatial position of an ion current peak by the plane position of the ion current peak, and finally determining the thrust vector eccentricity of the electric thruster by the spatial position of the ion current peak. Compared with a conventional method of determining the thrust eccentricity of the electric thruster by a multi-probe array, the determination method of the present invention has simple requirements for test equipment, is high in measurement precision and is convenient to operate.

Description

technical field [0001] The invention relates to a determination method, in particular to a determination method for thrust vector eccentricity of an electric thruster for a spacecraft. Background technique [0002] Various spacecraft such as satellites and deep space probes have widely used electric thrusters. However, asymmetric factors such as assembly and processing size deviations cause the thrust direction of the electric thruster to deviate from its central axis, and the starting point of the thrust is not from the center of the thruster, forming a moment of thrust vector around the center of mass of the satellite, which reduces the thrust efficiency of the satellite. It is necessary to start the flywheel in time Or the attitude control chemical propulsion system generates counter torque to prevent the deviation of satellite attitude. [0003] At present, the thrust vector eccentricity of the electric thruster is directly measured by the multi-probe array installed on...

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Problems solved by technology

[0005] (1) A large number of probes (ranging from dozens to hundreds) need to be arranged in an orderly manner for measurement, and the requirements for power supply, data acquisition and electromechanical interface of the probes have been greatly increased, and the complexity of the system has increased significantly;

[0006] (2) The spatial resolution is not high, and only the data of discrete points in the plume surface can be measured, especially near the center of the plume, the characteristics of the ion current peak may be missed;

[0007] (3) The distance between the probes of the multi-probe array is relatively short, and the independent measurement of each probe will cause mutual interference, which will affect the accuracy of the measurement. However, if the interval is too large, it will cause the omission of key measurement parameters. Therefore, it is necessary to Trade off the pros and cons between measurement accuracy and spatial resolution to determine a reasonable probe spacing;

[0008] (4) The more the number of probes introduced, the greater the distortion interference to the plume, which is not conducive to the authenticity of the measurement;

[0009] (5) The area of ​​the probe array plate is relatively large, facing the plume area, it will cause serious backflow, which will distort the measurement;

[0010] (6) Affected by the physical size of the probe itself, the angle of view of the probe will interfere, and the measurement accuracy is limited

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