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Integrated device and method for attitude control engine thrust measurement and in-situ calibration

An in-situ calibration, engine technology, applied in the direction of force/torque/work measurement instrument calibration/test, force/torque/work measurement instrument, measurement device, etc., can solve the problem of large initial torque, large influence of thrust measurement accuracy, elasticity The components are prone to fatigue cracks and other problems, so as to enhance the bending moment resistance, high stability and reliability, and improve the thrust measurement accuracy.

Active Publication Date: 2022-04-12
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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Problems solved by technology

[0006] In order to realize the high-precision measurement of the thrust of the 0-1000N thrust, especially the thrust of the attitude control engine in the state of the large nozzle, it solves the problem that the measuring force sensor bears a large initial torque and the elastic element of the sensor is prone to fatigue in the steady state thrust measurement of the existing attitude control engine Cracks, and external factors such as heat radiation and vibration have a great influence on the thrust measurement accuracy. The present invention provides a thrust measurement device, method and calibration force loading device for an attitude control engine

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  • Integrated device and method for attitude control engine thrust measurement and in-situ calibration

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Embodiment Construction

[0059] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention and the accompanying drawings. Apparently, the described embodiments do not limit the present invention.

[0060] Such as figure 1 As shown, this embodiment provides a thrust measurement device for an attitude control engine, including an integrated device for thrust measurement and in-situ calibration of an attitude control engine, including a thrust measurement device, a calibration force loading device, a data acquisition system 16 and Data processing system 17, the thrust measuring device and the calibration force loading device are both arranged on the base plate;

[0061] The thrust measuring device includes a central shaft 1, an elastic sheet 2, a connecting frame 3, a fixed frame 4, a measuring force sensor 5 and an adapter frame 6;

[0062] The central shaft 1 is installed on the fixed frame 4, the elastic...

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Abstract

The invention relates to an aerospace liquid engine test device, in particular to an integrated device and method for thrust measurement and in-situ calibration of an attitude control engine to solve the problem that the measuring force sensor of the existing attitude control engine bears a large initial moment and is prone to fatigue cracks. And external factors such as heat radiation and vibration have a great influence on the thrust measurement accuracy. The technical solution adopted in the present invention is: an integrated device for attitude control engine thrust measurement and in-situ calibration, including a thrust measurement device, a calibration force loading device, a data acquisition system and a data processing system. The thrust measurement device includes a center Shaft, elastic sheet, connecting frame, fixed frame, measuring force sensor and adapter frame; the calibration force loading device is arranged on one side of the central axis, and the calibration force loading device includes a calibration frame, a lead screw loading mechanism, a standard force sensor and steel wire. The invention also provides a method for thrust measurement and in-situ calibration of the attitude control engine.

Description

technical field [0001] The invention relates to an aerospace liquid engine test device, in particular to an integrated device and method for attitude control engine thrust measurement and in-situ calibration. Background technique [0002] Steady-state thrust measurement mostly uses a thrust wall-type measuring device. The measuring force sensor is fixed on the thrust wall. The engine is connected to the measuring force sensor through an adapter frame. The thrust force can be measured through the deformation of the strain gauge. [0003] For the 0-1000N thrust attitude control engine, the engine is directly connected to the measuring force sensor through the adapter frame, that is, the engine is connected to one end of the adapter frame through the bolt hole on the flange of the head, and the center of the measuring force sensor is an internal thread through hole. The other end of the adapter is bolted to the measuring force sensor through the center hole. The torque generat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01L5/00G01L25/00
CPCG01L5/0038G01L25/00
Inventor 赵明李广会寇鑫肖晶晶赵飞李民民黄鹏辉
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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