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Device and method for measuring rocket fuel liquid oxygen liquid level through laser ranging

A technology of rocket fuel and laser ranging, which is applied in the direction of measuring devices, lubrication indicating devices, buoy liquid level indicators, etc., can solve the problems of complex installation, low measurement accuracy, and low safety factor, and achieve simple and complex equipment installation. Low, laser energy safe and reliable effect

Inactive Publication Date: 2020-09-04
BEIJING INST OF AEROSPACE CONTROL DEVICES
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem of the present invention is to overcome the deficiencies of the prior art, and provide a device and method for measuring the liquid level of rocket fuel liquid oxygen storage tank by laser ranging, aiming at solving the problems of traditional resistive, capacitive, differential pressure ultrasonic, Radar and other rocket low-temperature fuel liquid oxygen storage tank liquid level monitoring solutions are affected by low temperature, capacitor dielectric constant, tank pressure, electromagnetic wave interference, etc., and have problems such as low measurement accuracy, small range, poor reliability, low safety factor, and complicated installation

Method used

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  • Device and method for measuring rocket fuel liquid oxygen liquid level through laser ranging
  • Device and method for measuring rocket fuel liquid oxygen liquid level through laser ranging
  • Device and method for measuring rocket fuel liquid oxygen liquid level through laser ranging

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Embodiment 1

[0055] The invention discloses a device for measuring the liquid oxygen level of rocket fuel by laser ranging. One of its core ideas is: based on the principle of phase-type semiconductor laser ranging, the phase shift generated by measuring the intensity-modulated sine wave going back and forth to the measured distance To measure the distance, combined with the known height information of the fuel storage tank to obtain the liquid level information of the low-temperature fuel in the fuel storage tank. It has the characteristics of large measurement range span (short-range measurement to long-distance measurement can be realized), no measurement blind zone, high precision, short response time, high reliability, etc., and is very suitable for liquid level measurement that requires high measurement accuracy; and It is resistant to low temperature, and the measurement accuracy is not easily affected by temperature. It adopts the laser principle and is not susceptible to electromag...

Embodiment 2

[0070] On the basis of the above-mentioned embodiments, the working process of the device for measuring the liquid oxygen level of rocket fuel based on the above-mentioned laser ranging is described below.

[0071] Such as Figure 4 , in this embodiment, the method for measuring the liquid oxygen level of rocket fuel by laser ranging may specifically include:

[0072] Step 1, parameter selection and installation of laser sensor probe 1, leak pipe 2, reflective floating plate 3 and rocket fuel tank 8, etc.

[0073] Preferably, a phase-type laser ranging sensor probe with a measurement frequency of 250 Hz, a measurement range of 0.05-100 m, a measurement accuracy of ±1 mm, and a laser emission power of <1 mW can be selected as the laser sensor probe 1 . The laser sensing probe 1 is vertically installed directly above the rocket fuel tank body 8 and fixed by a flange. Wherein, the shell top of rocket fuel tank body 8 is provided with an 80mm*50mm optical glass window, and the s...

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Abstract

The invention discloses a device and method for measuring the rocket fuel liquid oxygen liquid level through laser ranging. The device comprises a control module which is used for transmitting a lasertriggering signal through a data communication module, and updating the liquid level information in real time according to the liquid level height; a laser sensing probe which is used for emitting measurement laser, and transmitting the reflected laser to a data acquisition and processing module; a reflection floating plate which is used for reflecting the measurement laser and outputting the reflected laser; a data acquisition and processing module which is used for recording initial data information and analyzing the reflected laser to obtain measurement data information; and a data communication module which is used for calculating the liquid level height according to the initial data information and the measurement data information. The problems that a traditional rocket low-temperature fuel liquid oxygen liquid level monitoring scheme is affected by low temperature, capacitance dielectric constant, in-tank pressure intensity, electromagnetic wave interference and the like, so that measurement precision is low, the range is small, reliability is poor, the safety coefficient is low, and installation is complex are solved.

Description

technical field [0001] The invention belongs to the technical field of liquid oxygen liquid level monitoring of rocket low-temperature fuel, and in particular relates to a device and method for measuring the liquid oxygen liquid level of rocket fuel by laser ranging. Background technique [0002] High-thrust launch vehicles are the strategic cornerstone of my country's aerospace power and national security. Liquid hydrogen / liquid oxygen, liquid oxygen / kerosene and other liquid fuels have become the propellants of mainstream launch vehicles. At present, domestic launch vehicles mostly use liquid hydrogen / liquid oxygen fuel. The filling amount and utilization of cryogenic propellants directly affect the thrust and reliable flight of launch vehicles. Therefore, accurate liquid level measurement must be implemented. In addition, cryogenic propellants also need liquid level monitoring during production and storage. [0003] Due to the application characteristics of flammable and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01F23/292G01F23/64
CPCG01F23/292G01F23/64
Inventor 李瑞艳梅影朱晓非潘亮李娜杨潇君戴智航
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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