Method of measuring micro thrust eccentricity of solid rocket engine without constraint condition

A solid rocket and engine technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as large test errors, increased test workload and cost, and large impact on measurement accuracy

Pending Publication Date: 2020-06-30
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The methods used today are all based on ground-mounted devices. When the engine is constrained in the six-component force test platform, there will be mutual interference between the six force-measuring components, and the deformation of the measurement frame due to heat and force , have greatly reduced the measurement accuracy of the thrust measurement system
In addition, the supporting design of the ground fixing system also has a great impact on the measurement accuracy, which will bring a large test error
In addition, since the installation state of each test is different in this method, the measurement system must be calibrated before each test, which increases the test workload and test cost.

Method used

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  • Method of measuring micro thrust eccentricity of solid rocket engine without constraint condition
  • Method of measuring micro thrust eccentricity of solid rocket engine without constraint condition
  • Method of measuring micro thrust eccentricity of solid rocket engine without constraint condition

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Embodiment

[0060] refer to Figure 1 to Figure 7 , this embodiment is based on the calculation of thrust eccentricity through flight test data under free-state flight. The following is an analysis of the recorded data of a certain rocket engine under unconstrained conditions. The specific steps are as follows:

[0061] Step 1: Calculate the upper limit of flight speed according to the magnitude of aerodynamic resistance. In the example, the engine weighs 1.2Kg, the thrust is about 320N, the working time is 0.8s, and the aerodynamic resistance is less than 0.1% of the engine thrust. The upper limit of flight speed calculated by the formula in step 1 is about 60m / s. Calculate the additional load mass according to the upper limit of the flight speed to control the flight speed and height of the aircraft, improve the measurement accuracy, and facilitate the recovery of equipment. Calculated from the upper limit of the speed of the entire working section, the attached mass is about 2.8Kg. ...

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Abstract

The invention relates to a method of measuring micro thrust eccentricity of a solid rocket engine without constraint condition. The method comprises the following steps of configuring a certain load to the engine, wherein the flight of the engine is limited at a certain height and speed range; measuring and recording data through a gyroscope sensor in a free flying state; and calculating the processed data to obtain micro thrust eccentricity of the engine. Test data of an aircraft and thrust of the engine are established in a rectangular coordinate system of the aircraft. In the coordinate system, the thrust eccentricity is calculated finally by solving components of the thrust of the engine in three coordinate axis directions.

Description

technical field [0001] The invention belongs to the technical field of aerospace propulsion, in particular to a method for measuring the micro-thrust eccentricity of a solid rocket motor under unconstrained conditions. Background technique [0002] With the improvement of the level of my country's contemporary aerospace industry, the thrust vector measurement of rocket engines has gradually become the focus of engine development. Accurate measurement of thrust vector is very critical for evaluating engine performance indicators. Ideally, the thrust action line of a solid rocket motor should coincide with the central axis of the engine, but in fact, due to the limitation of machining accuracy, the geometric asymmetry of the engine, or the asymmetric flow of high-temperature and high-pressure gas through the nozzle and the throat of the nozzle The deformation caused by ablation causes the thrust line of the engine to deviate from the central axis of the engine, resulting in th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/08
CPCF02K9/96F02K9/08
Inventor 罗阳阳刘旸蔡祥林赵瑜惠卫华鲍福廷孙林魏然
Owner NORTHWESTERN POLYTECHNICAL UNIV
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