Pasty propellant fuel gas generator ignition device based on solid rocket engine

Abstract

The invention discloses a pasty propellant fuel gas generator ignition device based on a solid rocket engine. The pasty propellant fuel gas generator ignition device comprises a hole plate base, a fuel gas generator combustion chamber and an ignition engine. The two ends of an ignition engine combustion chamber of the ignition engine are fixedly connected with an ignition engine rear base and an ignition engine front cone respectively. An ignition powder column is arranged in the ignition engine combustion chamber. A powder baffle is arranged at the end, close to the ignition engine rear base, of the ignition powder column, and a powder fixing plate is arranged at the other end of the ignition powder column. A powder fixing plate locating base and an ignition powder box are arranged between the powder fixing plate and the ignition engine front cone. Inclined fuel gas nozzles are evenly distributed on the cavity wall between the powder baffle and the ignition engine rear base. The ignition engine and the end face of the hole plate base are coaxially and fixedly connected. The hole plate base is fixed to the propellant inlet end of the fuel gas generator combustion chamber. The ignition engine is located in the fuel gas generator combustion chamber. The pasty propellant fuel gas generator ignition device is simple in structure, simple and reliable in ignition mode and good in ignition effect, and pasty propellant can be fully ignited.

Description

technical field [0001] The invention belongs to the technical field of rocket motors, in particular to an ignition device for a paste propellant gas generator based on a solid rocket motor. Background technique [0002] Paste propellant is a new type of non-solid and non-liquid propellant developed on the basis of solid propellant. It is prepared by suspending solid particles such as oxidant and combustion agent in liquid binder and adding a small amount of gel agent. It does not need to be vulcanized when it is filled in the engine or storage tank. Paste propellant has the advantages of high specific impulse, good manufacturability, easy storage, thrust adjustment and multiple starts, etc., and has attracted more and more attention from all over the world. It is like a solid propellant when it is stored, and it becomes fluid like a liquid propellant after pressurization, but it does not leak, does not explode, and is safer and more reliable. Paste rocket motors can be swi...

AI Technical Summary

Problems solved by technology

[0003] The ignition methods of the current paste propellant rocket engines mainly include: 1) multiple igniters to ignite. This type of paste propellant rocket engines mostly adopts the integrated design of the propellant storage tank and the combustion chamber, and multiple ignition chambers are arranged in the combustion chamber. igniter to achieve multiple starts; the disadvantage is that the ignition reliability of the igniter is required to be high

2) Ignition with constant fire, ignite the solid tubular charge through the ignition cartridge, the pressure is transmitted back, and the paste propellant is extruded, and the paste propellant starts to burn after it comes out of the tube hole, and its thrust can be controlled by adjusting the flow rate of the pipeline The disadvantage is that the ignition process is not easy to control, and the ignition reliability is poor

3) Shen Haiqin introduced an ignition technology using a "thermal grid" in the document "Progress in Research on Bulk Propellant Rocket Engines". It is provided 0.5-0.8s before reaching the combustion chamber. The heat grid is made of thermally conductive and heat-resistant materials, such as molybdenum alloy. When the engine is working, the heat grid is heated to the temperature of the combustion products, and is used as a means of igniting the propellant during multiple starts The disadvantage is that the structure is more complicated, and the ignition effect is greatly affected by the properties of the thermal grid material.

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