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Vector thrust loading device for attitude control engine

A vector thrust and loading device technology, applied in rocket engine devices, jet propulsion devices, machines/engines, etc., can solve problems such as affecting calibration accuracy, and achieve the effect of high machining accuracy and light weight

Active Publication Date: 2016-06-08
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] For the in-situ calibration of the vector force sensor, the standard force involved is composed of force loads Fx, Fy, Fz in three directions and moment loads Mx, My, Mz in three directions, and the application of the standard force system is its key technology , if the deviation imposed by the standard force system is large, it will seriously affect the calibration accuracy

Method used

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  • Vector thrust loading device for attitude control engine
  • Vector thrust loading device for attitude control engine

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Embodiment Construction

[0023] Such as figure 1 , figure 2 As shown, the vector thrust loading device of attitude control engine is composed of loading head 1, connecting rod 4, rear flange 5, sensor mounting flange 3, positioning pin, pull ring, pressing seat and other parts.

[0024] Before the vector force sensor 2 is calibrated, it is fixed to the sensor mounting flange 3 by 4 M12 bolts, and the sensor mounting flange 3 is connected to the fixed foundation; after the loading head 1 and the vector force sensor 2 are positioned by two positioning pins , It is fixed by 4 bolts, and the loading head 1 is provided with positioning holes for positioning with the engine mounting flange. Before in-situ calibration, it is connected and fixed with the engine through 12 M8 bolts;

[0025] The pull ring is used to realize the application of standard pulling force, with 3 degrees of freedom, and has a compensation effect on the applied standard pulling force; the pressure seat is used to realize the application o...

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Abstract

The invention relates to a vector thrust loading device for an attitude control engine. The vector thrust loading device comprises a loading head, a connecting rod, a sensor mounting flange and a rear flange, wherein one end of the loading head is connected to the engine; the other end of the loading head is connected to the rear flange through the connecting rod; the sensor mounting flange is arranged between the rear flange and the loading head and is fixed on a stationary foundation; one end of a vector force sensor is fixed on the sensor mounting flange, and the other end of the vector force sensor is fixed on the loading head; the central position of the loading head is set as an original point; six pull rings and two pressing seats are arranged on the loading head; a seventh pull ring is arranged on the rear flange; and the first to sixth pull rings and the two pressing seats realize the application of Fy, Fz, Mx, My and Mz standard forces in a combination manner. According to the invention, the problem of application of standard vector forces under the vector force sensor coordinate system in the in-situ calibration process of the vector force sensor on a testing site is solved.

Description

Technical field [0001] The invention relates to an aerospace engine test, in particular to a method for realizing standard vector thrust loading in the process of in-situ calibration of the vector thrust of an attitude control engine. Background technique [0002] During the operation of the rocket engine, due to the asymmetric flow in the internal flow field of the combustion chamber, the vectoring nozzle, etc., it will inevitably produce a slight lateral force relative to the main thrust vector. Due to the higher and higher requirements for the control accuracy of the aircraft, the influence of this tiny lateral force on the control of the aircraft needs to be paid enough attention. [0003] In order to evaluate the working effect of the engine, the prior art provides a set of vector thrust measurement system developed on a high-altitude simulation test bench to obtain the vector thrust of the engine. However, because the liquid rocket engine needs to continuously supply propell...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/80
CPCF02K9/80F02K9/96
Inventor 李广会于军王朋军赵飞李广阔张丽娜李林永寇鑫
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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