Delay igniter for composite enhanced distance bullet rocket engine

Abstract

In the invention, a delay mechanism in the delayed igniter of the rocket engine is set as a totally-enclosed mechanism. In the delay mechanism there is a detonating cap and a fixed air chamber in order to ensure the steady burning of the starting mix. There are front and back starting mix cases, one is set at the back of the propellant grain of the rocket engine, the other is set at the front of the propellant grain. In the center of the propellant grain between the two starting mix cases there is a flame energy delivering passage with the 15~180 mm diameter.

Description

technical field [0001] The invention relates to a delayed ignition tool for a rocket engine of a bottom-row rocket composite extended-range shell. Background technique [0002] The ignition device of an ordinary rocket engine is located at the front end of the propellant of the rocket engine. The igniter and the medicine box in the ignition device are designed as one, which is easy to realize the reliable ignition function. The compound range-extended bomb with the bottom row and rocket serial structure is adopted. In order to increase the charging space of the rocket engine propellant chamber, the rocket delayed ignition device can only be placed at the rear end of the rocket engine nozzle, which brings problems. Yes, the rear end of the nozzle of the rocket engine has high chamber pressure, high overload, and high rotation speed, and the ignition device ignites from the rear end of the propellant. Since the propellant grain is long, the ignition device transmits the flame ...

AI Technical Summary

Problems solved by technology

The compound range-extended bomb with the bottom row and rocket serial structure is adopted. In order to increase the charging space of the rocket engine propellant chamber, the rocket delayed ignition device can only be placed at the rear end of the rocket engine nozzle, which brings problems. Yes, the rear end of the nozzle of the rocket engine has high chamber pressure, high overload, and high rotation speed, and the ignition device ignites from the rear end of the propellant. Since the propellant grain is long, the ignition device transmits the flame energy of the powder box to the propulsion through a certain channel. The front end of the powder column has lost a lot, and the reliability of the ignition and the stability of the delay time cannot be guaranteed.

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