Device for measuring class of discontinuous parameters of solid rocket engine

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...

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.

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