Measuring device and method of thrust vector of detection space plasma thruster

Abstract

The invention relates to a measuring device and a method of the thrust vector of a detection space plasma thruster. The measuring device of the thrust vector mainly comprises an electrostatic probe, an electrostatic probe regulating mechanism, a locating piece and a data acquisition and processing system. The method comprises the following steps: first fixing the electrostatic probe on a movable platform, simultaneously regulating the position of the electrostatic probe, installing the locating piece on the position which the probe can contact when the axis of the probe coincides with that of the plasma thruster, collecting the electrons jetted on the local position by the thruster in real time by the electrostatic probe on which positive bias voltage is applied when the movable platform moves at a constant speed along the direction vertical to the axis of the thruster, thus collecting the voltage signals at both ends of sample resistance in real time by the data acquisition and processing system when current flows through a probe circuit, and educing deflection of the actual thrust vector from the design objective by comparing the differences between the time corresponding to the vertex of the voltage signals at both ends of the sample resistance and the sudden change time of the voltage signals at both ends of the locating piece according to the moving speed of a translation stage and the distance from the electrostatic probe to the exit of the thruster.

Description

technical field [0001] The invention relates to a measuring device and method for detecting the thrust vector of a space plasma thruster. Background technique [0002] With the development of the times, space control capabilities play an increasingly important role in a country's security. The weight of chemical fuel carried by chemical rockets accounts for more than 90% of the total weight of the vehicle, and the payload only accounts for about 1%. However, due to the limitation of the chemical energy of the propellant, it is difficult to increase its specific impulse. Therefore, chemical propellants are suitable for short-term, high-thrust propulsion tasks. Relatively speaking, electric rocket propulsion technology can obtain higher carrying efficiency, and is suitable for propulsion tasks with long-term, small and medium thrust, and high specific impulse. At present, for satellites of various purposes, in order to reduce weight and size, improve positioning accuracy, an...

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Problems solved by technology

However, the above methods all measure the magnitude of the thrust, or measure the thrust component along the axial direction of the thruster, but whether the thrust direction generated by the thruster is absolute

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