Attitude-control engine vector thrust measurement and calibration integrated device and measurement method

A vector thrust and engine technology, applied in the calibration/testing of force/torque/power measuring instruments, measuring devices, force/torque/power measuring instruments, etc., can solve the problems of large mutual interference and large uncertainties

Active Publication Date: 2016-04-13
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology

[0010] In order to realize the vector thrust measurement requirements of the attitude control engine and solve the problems of large mutual interference between phases, many uncertainties introduced by the

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  • Attitude-control engine vector thrust measurement and calibration integrated device and measurement method
  • Attitude-control engine vector thrust measurement and calibration integrated device and measurement method
  • Attitude-control engine vector thrust measurement and calibration integrated device and measurement method

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Embodiment Construction

[0100] The present invention will be further described below in conjunction with accompanying drawing:

[0101] The attitude control engine vector thrust measurement and calibration integrated device is used as the main means for attitude control engine vector thrust acquisition. It is characterized in that: the device consists of two parts: vector thrust measurement device and vector thrust in-situ calibration device; During the working process of the attitude control engine, the vector thrust is measured; the measurement range of the main thrust Fx is 0-2000N, the lateral force Fy and Fz are 0-60N, the X-axis moment Mx is 0-20N·m, and the Y-axis moment My is 0 ~10N·m, Z-axis moment Mz is 0~50N·m; its axial thrust static measurement expanded uncertainty is 0.5% (k=2), lateral thrust static measurement expanded uncertainty is 2% (k= 2) Expanded uncertainty of torque static measurement: 2% (k=2); vector thrust in-situ calibration device can perform in-situ calibration on the ve...

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Abstract

The invention relates to an attitude-control engine vector thrust measurement and calibration integrated device and a measurement method, so as to satisfy the requirement on attitude-control engine vector thrust measurement. The attitude-control engine vector thrust measurement and calibration integrated device comprises an engine, a standard vector force source, a loading mechanism, a vector force measurement unit, a data processing module and an in-situ thrust calculating module. The standard vector force source is used to generate and control nine standard forces on the loading mechanism according to the execution requirement. The loading mechanism is used to fix a vector force sensor to be calibrated. The vector force measurement unit is used to collect voltage signals that are outputted by the vector force sensor to be measured. The data processing module is used to receive a loading result from the standard vector force source and a measurement result from the vector force measurement unit and obtain a calibration coefficient of the vector force sensor to be calibrated by means of calculation. The in-situ thrust calculating module is used to calculate the force that is applied on a flange face of the engine. When the engine is working, the main thrust, the horizontal lateral force, the vertical lateral force, etc. of the engine can be obtained to examine the working performance of the engine.

Description

technical field [0001] The invention relates to an aerospace engine test, in particular to a test method for accurately obtaining vector thrust during the working process of an attitude control engine. Background technique [0002] Ideally, the thrust of the engine coincides with the central axis of the engine, but the actual situation is often: due to the limitation of machining accuracy and the influence of asymmetric factors, the geometric asymmetry of the engine is formed, or the gap between the engine throat and the nozzle is formed under high temperature and high pressure. The deformation and the asymmetric flow of gas in the nozzle cause the thrust action line of the engine to deviate from the central axis of the engine, resulting in thrust eccentricity, lateral thrust and the moment of the main thrust vector around the center of mass of the propeller. The existence of thrust eccentricity not only affects the missile's Flight performance, but also directly affects the...

Claims

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Application Information

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IPC IPC(8): G01L5/00G01L25/00
CPCG01L5/00G01L25/00
Inventor 李广会冷海峰于军王宏亮赵飞王朋军周献齐刘阳
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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