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Device for acquiring rocket-borne data of solid-liquid power sounding rocket

A technology for sounding rockets and data acquisition, applied in the field of rocket-borne data acquisition systems, to achieve the effects of high-efficiency thrust adjustment, good versatility, and simple solid-liquid powered sounding rocket rocket-borne data acquisition devices

Active Publication Date: 2012-10-17
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, there is currently no such collection device

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  • Device for acquiring rocket-borne data of solid-liquid power sounding rocket
  • Device for acquiring rocket-borne data of solid-liquid power sounding rocket
  • Device for acquiring rocket-borne data of solid-liquid power sounding rocket

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Embodiment Construction

[0031] The present invention will be further described below in conjunction with accompanying drawing. Based on the research purpose of the solid-liquid powered sounding rocket and the requirements of the on-board data collection, the present invention designs and implements the on-board data device for recording the three axial accelerations of the sounding rocket and part of the working conditions of the rocket engine. It aims to monitor and control the supply system, pressurization system, and blow-off system of the solid-liquid rocket engine in sequence, so as to record the working conditions of the rocket engine and some functions of the rocket-borne computer, and calculate the The actual thrust of the solid-liquid sounding rocket is compared with the rocket acceleration at that time. The final missile-borne data acquisition device can meet the performance requirements of solid-liquid power sounding rocket data acquisition, meet the environmental requirements of the elect...

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Abstract

The invention relates to a device for acquiring rocket-borne data of a solid-liquid power sounding rocket. The device is mainly used for acquiring, processing, monitoring and storing signals output by three uniaxial accelerometers, a pressure transmitter for measuring the pressure of an oxidizing agent storage tank, a pressure transmitter for measuring the pressure of a high-pressure gas cylinder capable of pressurizing the oxidizing agent storage tank, a pressurization working condition conversion electromagnetic valve, an auxiliary circuit blow-off self-locking electromagnetic valve and a main circuit blow-off self-locking electromagnetic valve. According to a rocket-borne data acquisition circuit, core functions of sequential control, data acquisition, signal conditioning, switching value conversion, data caching, data storage, data remote transmission and the like of the data acquisition device can be realized by a control chip; and other functions of voltage stabilization, protection, power supply, electricity conversion control, clock input and the like are required to be realized besides the core functions. By the device, thrust which is actually generated by a solid-liquid rocket engine and accelerations of the rocket in three axial directions can be totally monitored and compared at the working stage of the engine.

Description

technical field [0001] The invention belongs to the field of rocket-borne data acquisition systems, and in particular relates to an arrow-borne data acquisition device of a solid-liquid powered sounding rocket. Background technique [0002] The solid-liquid sounding rocket is a rocket for detection and scientific experiments in near-Earth space. Its main purpose is to conduct space exploration or conduct flight verification tests, and to accumulate experience for the development of solid-liquid powered aircraft. Compared with solid and liquid propellant rockets, the advantage of solid-liquid powered sounding rockets is that they are easy to shut down and restart, thanks to the independent on / off control valves in the solid-liquid rocket motor, which makes the entire mixed combustion process faster than liquid propellants. And solid motors are easy to control. At the same time, the solid-liquid rocket engine has a strong thrust adjustment capability, but the stable combustio...

Claims

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Application Information

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IPC IPC(8): G05B19/042
Inventor 宋佳蔡国飙辛洁孔德帅陈辰
Owner BEIHANG UNIV
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