Carrier rocket pre-launch additional parameter monitoring method

An additional parameter, launch vehicle technology, applied in the field of aerospace measurement, can solve the problem of inability to complete long-term power-on, and achieve the effect of high reliability, good economy, and optimization of personnel positions

Active Publication Date: 2020-12-11
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the case of the existing measurement mode, if the transmission mode of radio frequency measurement is adopted, the long-term (generally not more than 4 hours) power-on requirement cannot be fulfilled

Method used

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  • Carrier rocket pre-launch additional parameter monitoring method
  • Carrier rocket pre-launch additional parameter monitoring method
  • Carrier rocket pre-launch additional parameter monitoring method

Examples

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Embodiment Construction

[0043] The present invention will be further elaborated below in conjunction with embodiment.

[0044] A pre-launch additional parameter monitoring system for a launch vehicle, comprising an arrow liquid level sensor, an arrow liquid level converter, an arrow temperature sensor, an arrow temperature and humidity sensor, a ground liquid level signal processing module, a ground temperature signal processing module, a ground Temperature and humidity signal processing module, ground power supply module and ground communication module;

[0045] The ground power supply module controls the power supply of the liquid level sensor on the arrow, the liquid level converter on the arrow, the temperature sensor on the arrow, and the temperature and humidity sensor on the arrow;

[0046] The liquid level sensor on the arrow and the liquid level transducer on the arrow work together to output the voltage value V representing the information of the liquid level of the propellant i , and the ...

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Abstract

The invention relates to a carrier rocket pre-launch additional parameter monitoring system. A ground power supply module enables an on-rocket liquid level sensor, an on-rocket liquid level converter,an on-rocket temperature sensor and an on-rocket temperature and humidity sensor to supply power; and the on-rocket liquid level sensor and the on-rocket liquid level converter act together to outputa voltage value Vi representing propellant liquid level height information and transmit the voltage value Vi to the ground liquid level signal processing module, and the ground liquid level signal processing module determines the on-rocket propellant liquid level height according to the voltage value Vi and transmits the on-rocket propellant liquid level height to a ground communication module. The requirement for continuous monitoring of temperature and humidity measuring points in a fairing can be met, the requirement for accurate measurement of the liquid level of a cryogenic propellant isalso met, meanwhile, other temperature parameters on the rocket transmitted for a long distance can be effectively measured, the system has high reliability, ground equipment and a ground cable network can be repeatedly used, the cost is low and the economy is better.

Description

technical field [0001] The invention relates to a method for monitoring additional parameters of a launch vehicle before launch, and belongs to the technical field of aerospace measurement. Background technique [0002] The parameters of the launch vehicle before launch and in flight are mostly measured by the on-board measurement system. There are many parameters and complex types. Generally, each cabin has an independent acquisition and compilation system to collect and edit the parameters nearby. The acquisition and compilation system consists of converter adapters, data The acquisition and editing device is composed of a power supply and distribution timing system to complete the unified power supply to the single unit of the measurement system. [0003] After the launch vehicle, especially the new generation of low-temperature launch vehicle, needs to continuously monitor the temperature and humidity parameters in the fairing and the parameters related to filling, after...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01F23/26G01K7/18G01D21/02
CPCG01F23/263G01F23/265G01K7/18G01D21/02
Inventor 程程谢立李雷金健金豹任安宇
Owner SHANGHAI AEROSPACE SYST ENG INST
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