Unlock instant, AI-driven research and patent intelligence for your innovation.

Multichannel solid rocket engine ignition sequence control method

A technology of solid rockets and ignition timing, applied to rocket engine devices, machines/engines, mechanical equipment, etc.

Inactive Publication Date: 2013-05-29
NORTHWESTERN POLYTECHNICAL UNIV
View PDF5 Cites 24 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the original ignition timing control device, two ignition channels, the accuracy of the ignition signal time interval is 1s, it is far from enough to complete the propellant ignition and the ignition trigger control of the two pulsers at different given times in such a short time of

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Multichannel solid rocket engine ignition sequence control method
  • Multichannel solid rocket engine ignition sequence control method
  • Multichannel solid rocket engine ignition sequence control method

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment

[0029] Under the preset working conditions of the T-shaped burner with a working pressure of 7.0MPa and a working time of 2.0s, the pulse trigger excitation is carried out at the middle time of work of 1.0s and the moment of 2.0s just after the propellant has been burned to investigate the effect of ignition timing control . Among them, the time interval of high-speed timer 1 in the ignition sequence is set to 1000ms, and the time interval of high-speed timer 2 is set to 1000ms, that is, the first pulse trigger time is 1.0s after engine ignition, and the second pulse trigger is after engine ignition 2.0s, and close after two triggers for 2s. Trigger control timing such as Figure 5 shown.

[0030] Figure 6 It is the actual situation of pulse-triggered excitation timing under experimental working conditions. The working time of the engine is 2.0s. It can be seen from the figure that the 1st and 2nd ignition channels are triggered at the same time. The excitation time of t...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention relates to a multichannel solid rocket engine ignition sequence control method. Propellant ignition time and two-way pulser ignition triggering excitation time which is specially required are accurately controlled through accurate sequence triggering control according to a known pressure intensity-time curve, and therefore experimental measurement work of composite propellant pressure intensity coupling response functions of a random pulse excitation method can be carried out under the condition that the pulse triggering excitation time is accurately controlled. The greatest characteristic of the multichannel solid rocket engine ignition sequence control method is that T-shaped burner ignition time and the two times of pulse excitation time are accurately controlled, accurate pulse triggering excitation can be carried out on T-shaped burner experiment under different working conditions through adjustment of a time interval of a high-speed timer according to an engine internal trajectory pressure intensity curve, and the precision of the triggering time interval is 10 ms.

Description

technical field [0001] The invention relates to an ignition sequence control method of a multi-channel solid rocket motor, which accurately controls the ignition of the engine and the ignition trigger of a pulser at a specific working time, and lays a foundation for accurately implementing external excitation at different working hours and studying the combustion stability of the solid rocket motor. Background technique [0002] As one of the important factors affecting combustion instability in solid rocket motors, the pressure coupling characteristics of composite propellants have been paid attention by researchers at home and abroad. For solid propellants, the pressure coupling characteristics are usually characterized by the pressure coupling response function, and the pressure coupling response function needs to be obtained by means of experimental measurement. At present, most experimental tests use the T-shaped burner method. The main feature of the T-shaped burner i...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/95
Inventor 金秉宁刘佩进吕翔
Owner NORTHWESTERN POLYTECHNICAL UNIV