Electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing

Abstract

The invention discloses an electric control power device with real-time controllable thrust and capable of repeatedly igniting and extinguishing. The electric control power device comprises a combustion chamber shell, a spray pipe, an electrode fixing sleeve, an electrode, an electric control solid propellant grain, a spring, a lead end insulating plate, an electrode fixing device, a thermal protection layer, an insulating layer, a resistance monitor, a voltage controller, a fixed sealing end and an electrode contact pin. According to the electric control power device, the voltage required byfirst ignition is reduced by changing the electrode structures of the initial combustion surface and the combustion surface of the propellant grain, and meanwhile, the stable combustion of the same end surface can be guaranteed through the electrode contact and end surface combustion modes; the resistance monitor is matched with the voltage controller, and the applied voltage is adjusted, so thatthe magnitude of the generated thrust is ensured to be certain; and the electrode contact pin is matched with the fixed sealing end for use, so that the sealing effect on a combustion chamber can be achieved, the electric control power device can be easily assembled with an external missile or an aircraft, and the purposes of rapid installation and disassembly are achieved.

Description

technical field [0001] The invention relates to the field of special solid motors, in particular to an electronically controlled power device with real-time controllable thrust and repeatable ignition and flameout. Background technique [0002] In order to meet the needs of high mobility, fast response, and high interception capability of missiles in future wars, missile weapons and equipment are developing in the direction of high mobility and rapid defense penetration, requiring missile engines to be capable of repeated multiple starts and real-time controllable thrust. Although the liquid rocket engine can achieve multiple ignitions, its complex structure, toxic propellant and long filling time do not meet the needs of rapid response operations. The solid rocket motor has a simple structure and short launch preparation time, and is more suitable as a missile weapon power device. However, there are two major defects in the popularization and application of solid propellan...

AI Technical Summary

Problems solved by technology

However, there are two major defects in the popularization and application of solid propellant engines: on the one hand, after the solid propellant is extinguished, it is difficult to ignite again, and multiple starts cannot be achieved; on the other hand, the combustion process of solid propellant is uncontrolled, making it difficult to achieve Thrust adjustment

The above-mentioned improvement methods all belong to the passive adaptation to the combustion characteristics of solid propellants, the effect is limited, and it is still impossible to achieve multiple starts and flexible thrust adjustment

[0004] Although the currently available electronically controlled solid propellants meet the above requirements, during the combustion process of the grain, due to changes in temperature and the length of the grain itself, the resistance of the grain itself changes, so that the burning rate at the same voltage is accelerated, and it cannot produce all the propellants. Need constant thrust

As an exception, due to the limited external energy supply that can be carried on missile weapons, reducing energy consumption in the process of realizing the above requirements is also a severe problem faced by missile weapon power plants at present

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