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Device for measuring class of discontinuous parameters of solid rocket engine

A technology of parameter measurement and solid rockets, which is applied in the direction of measuring devices, engine testing, machine/structural component testing, etc. It can solve problems such as complex troubleshooting, poor flexibility of use, and many transfer links, and achieve intuitive observation and troubleshooting The effect of simplicity and few transfer links

Inactive Publication Date: 2013-12-18
中国航天科技集团公司第四研究院四0一所
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Although the current measurement device can meet the requirements of the solid rocket motor test, it has many disadvantages such as too many switching links, poor reliability, complicated troubleshooting, poor flexibility of use, and unintuitive observations that must rely on acquisition or recording equipment.

Method used

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  • Device for measuring class of discontinuous parameters of solid rocket engine
  • Device for measuring class of discontinuous parameters of solid rocket engine
  • Device for measuring class of discontinuous parameters of solid rocket engine

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Embodiment Construction

[0018] Describe the present invention below in conjunction with specific embodiment:

[0019] Refer to attached Figure 4 , the solid rocket motor class discontinuous parameter measuring device in the present embodiment comprises a chassis, an input panel with an input interface socket, a power switch and a status indication, an output panel with an output interface socket, a power supply socket and a power supply switch, Power supply adapter cable and circuit board. The input panel and the output panel are fixed on the chassis by screws, and the circuit board is installed in the chassis through the installation slot.

[0020] The input interface socket, the output interface socket and the power supply socket are all BNC interface sockets. input panel such as figure 2 As shown, 10 channels are designed, and BNC interface sockets and status indicators are all distributed on the panel. Output panel such as image 3 As shown, the number of channels corresponds to the input,...

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Abstract

The invention provides a device for measuring a class of discontinuous parameters of a solid rocket engine. The device for measuring the class of discontinuous parameters of the solid rocket engine comprises a case, an input panel with an input interface socket, a power supply switch and state indication, an output panel with an output interface socket, a power supply socket and a power supply diverter switch, a power supply patch core and a circuit board. A current limitation circuit of the circuit board is formed by connecting n channel measuring circuits in parallel and then connecting the n channel measuring circuits with a total current limitation resistor R0 in series. A power supply indication circuit of the circuit board is formed by connecting an ordinary luminous diode L and a power supply indication circuit resistor R1 in series. A single channel measuring circuit is formed by connecting a highlight luminous diode Li, a single blade switch K and a one-way shunting resistor R in series. According to the device for measuring the class of discontinuous parameters of the solid rocket engine, the luminous diode is used for observing each line of signals, current limiting measures are adopted to ensure that the current of each line of the signals is in the milliampere level, a BNC contact is used for unitizing and simplifying the switch over links, two power supply modes which are a battery mode and a power supply mode are provided, and therefore measurement of the class of discontinuous parameters in a solid rocket engine test can be achieved.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motor test measurement and control, in particular to a discontinuous parameter measurement device for solid rocket motors. Background technique [0002] In the ground tests of various types of solid rocket motors, it is necessary to measure the opening moment of the nozzle cap, and analyze it correspondingly with the thrust and pressure data to obtain the opening characteristics of the nozzle cap; in the test where the reverse nozzle is used to achieve thrust termination In the process, it is also necessary to measure the moment when the blocking cap on each reverse nozzle is blown off after the shutdown command is issued, and the flame starts to spray out from the reverse nozzle, or arrange multiple measuring points on the throwing track of the blocking cap, and use To study the performance of the termination mechanism; in the test of evaluating the ablation of the gas rudder, it is necessar...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00
Inventor 贺晓芳陈宁芳李会婷佟力波张荣郭李艳王智勇丁佐琳李蔚刘洁冯旭
Owner 中国航天科技集团公司第四研究院四0一所
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