Rocket engine micro-force measuring device

A technology of rocket engine and measuring device, which is applied in the direction of measuring device, force/torque/work measuring instrument, force/torque/work measuring instrument calibration/test, etc. and other problems to achieve the effect of improving accuracy, reducing friction and elastic resistance

Pending Publication Date: 2019-04-16
SHAANXI SPACEFLIGHT XINO MEILING ELECTRIC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] At present, engine tests generally use a center frame supported by rollers, a flexible frame supported by leaf springs, and a sliding frame supported by slide rails, etc., all of which are contact structures. Elastic resistance cannot be completely eliminated. It has little influence on testing large force values, but it has a greater impact on testing small force values, and every increase in processing accuracy will lead to a geometric doubling of processing costs.

Method used

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  • Rocket engine micro-force measuring device
  • Rocket engine micro-force measuring device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] A rocket engine micro-force measuring device, at least comprising a fixed frame 1 fixedly connected to a test site, characterized in that: a load-bearing pier 2 and an air-floating small displacement device are fixed above the fixed frame 1, and a load-bearing pier 2 is slidably connected with a For the booster device, a force transmission frame 9 is fixed on the side close to the booster device above the small displacement device of the air flotation, and an engine fixing unit is arranged on the side away from the booster device above the small displacement device of the air flotation, and the force transmission frame 9 is close to the booster The outer wall and the inner wall on one side of the device are respectively detachably connected with a force sensor one 8 and a force sensor two 10. When the non-working state is in a non-working state, a force gap is left between the force sensor one 8 and the force-applying device. The force transmission calibration frame 19 o...

Embodiment 2

[0028] Such as figure 1 , figure 2 As shown, it is improved on the basis of Embodiment 1, and the force applying device includes a speed reducer 4, a force booster 5, a force-bearing mount 6 and a force measuring shaft 7, wherein the output shaft of the speed reducer 4 is connected to the force force The input shaft of the booster 5 is connected by transmission, the booster 5 is slidingly connected with the fixed frame 1 along the length direction of the fixed frame 1, the load-bearing mounting seat 6 is fixed on the end of the load-bearing pier 2 away from the force booster 5, and the load-bearing mounting base 6 A force measuring shaft 7 is also fixed on the side close to the force sensor one 8, and a force gap is left between the force sensor one 8 and the force measuring shaft 7 in the non-working state.

[0029]The centerlines of the reducer 4, the force booster 5, the force-bearing mount 6, the force measuring shaft 7, the force sensor one 8, the force transmission fra...

Embodiment 3

[0037] Such as figure 1 , figure 2 As shown, it is improved on the basis of Embodiment 1 and Embodiment 2, and the force sensor-8 is connected with the electrical signal of the external data acquisition equipment, and is used for the real-time force value during feedback test or static calibration; The second sensor 10 is connected with the external display by electric signal, and serves as an instrument for feeding back the current calibration force value during static calibration.

[0038] The external data acquisition equipment is connected with the force sensor-8 by electrical signal, and the data acquisition equipment selects the PC-based measurement and control system of American NI Company, and the NI hardware products are connected to PC or notebook computer through USB or Ethernet. Connect the CompactDAQ chassis to the PC and insert the I / O module with integrated signal conditioning into the chassis. Described external data collection equipment is existing mature t...

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PUM

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Abstract

The invention discloses a rocket engine micro-force measuring device comprising a fixed frame. A bearing pier and a small floatation displacement device are fixed on the fixed frame. A force adding device is connected to the bearing pier in a sliding manner. A force transmitting frame and an engine fixing unit are arranged at the small floatation displacement device. A force sensor 1 and a force sensor 2 are connected to the outer wall and the inner wall of one side of the force transmitting frame. A force transmission calibration frame is fixed on the force transmitting frame; one end of theforce transmission calibration frame is arranged in the force transmitting frame and the other end of the force transmission calibration frame is in transmission connection with the force adding device. The central lines of the force adding device, the force sensor 1, the force transmitting frame, the force transmission calibration frame and the force sensor 2 are arranged at the same straight line. According to the invention, the device is integrated with the test tooling, data acquisition and processing. When a vehicle is tested, the engine is fixed on the measuring device according to the required test state and thus real-time data are collected and analyzed; and under comparison with the design task book, the performance, precision, and reliability of the engine are evaluated and problems are found, so that the direction and approach are pointed out for improving the design.

Description

technical field [0001] The invention belongs to the technical field of rocket engine testing, in particular to a rocket engine micro force measuring device. Background technique [0002] Rocket propulsion technology is widely used in space science experiments and national defense construction. The precise control of engine thrust is of great significance to control the attitude of the aircraft and improve the accuracy of target hitting. The attitude and orbit control engine (KKV) is different from the general propulsion engine. The attitude and orbit control engine is in an intermittent working state, and the ignition time of each engine may only last for a few milliseconds to tens of milliseconds. It is very necessary to run the orbit, so an accurate understanding of the thrust status of the rocket engine is a necessary prerequisite for improving the control accuracy. [0003] In the past ten years, solid KKV technology has developed from tactical missile air defense and a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01L5/13G01L25/00
CPCG01L5/133G01L25/00
Inventor 胡广琳雷海胡鑫王茂森庞海洋
Owner SHAANXI SPACEFLIGHT XINO MEILING ELECTRIC
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