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Apparatus and method for measuring small rocket engine thrust force vector in vacuum

A thrust vectoring and measuring device technology, which is applied to measuring devices, engine testing, force/torque/work measuring instruments, etc., can solve the problems of unfinished public reports, thrust vector deflection, etc., and achieves simple and high-precision measuring equipment. The effect of uniform movement and high reset accuracy

Inactive Publication Date: 2009-05-20
INST OF MECHANICS - CHINESE ACAD OF SCI
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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 axis of the engine, but whether the thrust direction generated by the small rocket engine is absolutely parallel to the axis of the engine, that is, the deflection of the thrust vector, is also a requirement. An important parameter for accurate measurement, and no relevant public reports have been found so far

Method used

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  • Apparatus and method for measuring small rocket engine thrust force vector in vacuum
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  • Apparatus and method for measuring small rocket engine thrust force vector in vacuum

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Embodiment Construction

[0025] refer to figure 1 , figure 2 , making a small rocket engine thrust vector measuring device, the device includes: 1 sampling hole, 2. pressure probe, 21 water-air isolation sleeve, 22 conical outer tube, 23 cooling water spacer, 24 cooling water outlet, 25 cooling water Inlet, 3 gas passage, 4 sensor sensing surface, 5 sensor, 6 data transmission line, 7 data acquisition and processing system, 8 pressure probe support shock absorber, 9 movable platform, 10 rotary table.

[0026] In this embodiment, the diameter of the sampling hole 1 is 0.3mm, so that the measurement results can reach a higher spatial resolution; the cone angle of the pressure probe conical head is 24°, and the straight section of the pressure probe connected to the conical head The diameter of the sensor is 12mm to minimize disturbance to the jet flow field; the sensor 5 uses a differential pressure sensor with an accuracy of 2.5‰ and a response frequency of 1kHz to ensure good accuracy of the measure...

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Abstract

The invention relates to a measuring device and a method for detecting thrust vector of a tiny rocket motor used in vacuum. The device for detecting the thrust vector mainly comprises a pressure probe, a movable platform, a rotating table and a data acquisition system. The method comprises the following steps: fixing the pressure probe to the movable platform first, and then adjusting the position of the pressure probe simultaneously, so as to make an axis of the pressure probe parallel to an axis of the tiny rocket motor. When the movable platform moves at constant speed along the direction perpendicular to the axis of the tiny rocket motor, a sensor positioned in the pressure probe senses local dynamic pressure signals in jet current generated by the tiny rocket motor in real time, and the acquisition system acquires and transmits the signals to a data processing and displaying system. Through analyzing symmetry of the dynamic pressure relative to the axis of the tiny rocket motor, the method studies deflection conditions of actual thrust vector and design objective.

Description

technical field [0001] The present invention relates to an apparatus and method for measuring the thrust vector of a small rocket motor used in a vacuum. 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 position...

Claims

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Application Information

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IPC IPC(8): G01L5/00G01L5/12G01M15/00
Inventor 潘文霞孟显吴承康
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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