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

A technology of plasma and thrust vectoring, applied in the direction of measuring devices, force/torque/work measuring instruments, and electric devices, etc., can solve the problems of unavailable public reports, etc., achieve simple measuring equipment, improve detection accuracy, and high positioning The effect of precision

Inactive Publication Date: 2011-02-16
INST OF MECHANICS CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

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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 absolutely parallel to the axis of the engine, that is, whether the thrust vector is deflected, is also a requirement. An important parameter for accurate measurement, and no relevant public reports have been found so far

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

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Embodiment Construction

[0023] refer to figure 1 , making a plasma thruster thrust vector measurement device, the device includes: 1. Electrostatic probe, 2. Insulation sleeve, 3. Probe support seat, 4. Sampling resistor, 5. Bias power supply, 6. Data acquisition device , 7. Reference electrode, 8. Positioning piece, 9. Shock absorbing piece, 10. Movable platform, 11. Rotary table.

[0024] In this embodiment, the electrostatic probe 1 is made of a tungsten wire with a diameter of 0.3mm, and extends out of the insulating sleeve 2mm. The outer diameter of the insulating sleeve 2 is 1mm, and the length is 35mm, so as to reduce the disturbance to the jet flow as much as possible. The thin tungsten wire diameter makes the measurement results have a higher spatial resolution; the probe support seat 3 is made of high-temperature resistant ceramic material; the bias power supply 5 is set to 10V, the resistance of the sampling resistor 4 is 1 ohm, and the data acquisition The device 6 is a digital oscillosc...

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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 ofthe 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 thevertex 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 translationstage 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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01L5/12G01B7/30
Inventor 潘文霞孟显吴承康
Owner INST OF MECHANICS CHINESE ACAD OF SCI
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