Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Three-directional force measurement device and measurement method for large thrust rocket engine

A technology of rocket engine and measuring device, which is applied in the direction of measuring device, engine test, force/torque/work measuring instrument, etc., can solve the problems of reduced measurement accuracy, inability to effectively ensure measurement accuracy, etc., to ensure measurement accuracy , The effect of solving accurate measurement interference and simple structure

Active Publication Date: 2018-12-25
XIAN AEROSPACE PROPULSION TESTING TECHN INST
View PDF4 Cites 7 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problem that the existing three-way force measurement method of a large-thrust rocket engine cannot effectively ensure the measurement accuracy, so that the measurement accuracy is reduced, and provides a three-way force measurement device and method for a high-thrust rocket engine. This method can realize the accurate measurement of three-way thrust of 1200kN high-thrust liquid oxygen kerosene engine

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Three-directional force measurement device and measurement method for large thrust rocket engine
  • Three-directional force measurement device and measurement method for large thrust rocket engine
  • Three-directional force measurement device and measurement method for large thrust rocket engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0051] The technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings.

[0052] In the present invention, a three-way force measuring device is additionally installed on the test frame of the 1200kN rocket engine to measure the lateral thrust of the 1200kN high-thrust rocket engine. Utilize the measuring device provided by the present invention, apply the lateral thrust of different directions and different sizes by means of the calibration force source, obtain the measured value of the sensor in each three-direction force measuring device, and establish the relationship between the measured value of each force sensor and the three-direction force of the engine The calculation model (correction formula) between them is used, and the method of in-situ calibration of engine thrust is used to fit and obtain the size of each correction coefficient in the calculation model. In the actual lateral thrust me...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention relates to a three-directional force measurement device and measurement method for large thrust rocket engines, and solves the problem that the existing three-directional force measurement method of the large thrust rocket engines can not effectively ensure the measurement accuracy, and reduces the measurement accuracy. The measurement device comprises a test vehicle moving frame, atest vehicle fixing frame, an upper layer lateral thrust measurement unit, a lower layer lateral thrust measurement unit, and an axial thrust measurement unit. The test vehicle fixing frame comprisesan outer layer support frame, a fixing frame upper ring beam, a fixing frame lower ring beam, a fixing frame auxiliary beam, and a fixing frame connecting beam. The test vehicle moving frame comprisesa moving frame upper ring beam, a moving frame lower ring beam, and an inner layer support frame. The axial thrust measurement unit is installed between the moving frame upper ring beam and the fixing frame upper ring beam. The lower layer lateral thrust measurement unit is arranged between the fixing frame auxiliary beam and the moving frame lower ring beam. The upper layer lateral thrust measuring units are eight sets, and are arranged between the fixing frame connecting beam and the moving frame upper ring beam. Meanwhile, the invention further provides a three-directional force measurement method based on the device.

Description

technical field [0001] The invention relates to the field of high-thrust rocket engine testing, in particular to a three-way force measuring device and method for a high-thrust rocket engine. Background technique [0002] Existing tests of high-thrust rocket engines only consider the magnitude of the main thrust of the engine, and there are few studies on the lateral thrust of the engine. At present, when measuring the lateral thrust of the rocket engine, the thrust measurement method based on the multi-component force meter and the thrust measurement method based on the unidirectional force sensor (the measurement method based on the six-degree-of-freedom platform and the thrust measurement method based on the orthogonal coordinate system) are mainly used. ). [0003] Due to the large size and high thrust of the high-thrust rocket engine, if the thrust measurement method of the multi-component force meter is used, the lateral pretension device cannot be installed on the si...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): G01M15/00G01L5/13
CPCG01L5/133G01M15/00
Inventor 李大海刘洋唐斌运郭立沈继彬李亮杨战伟
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com