An electronically controlled power device with real-time controllable thrust and repeatable ignition and flameout

Abstract

The invention discloses an electronically controlled power device with real-time controllable thrust and repeatable ignition and extinguishment, which includes a combustion chamber shell, a nozzle, an electrode fixing sleeve, an electrode, an electrically controlled solid propellant grain, a spring, and insulation for lead terminals. Plates, electrode fixtures, thermal shields, insulation, resistance monitors, voltage controllers, stationary seals, and electrode pins. The device of the present invention reduces the voltage required for the first ignition by changing the initial burning surface of the propellant grain and the electrode structure of the burning surface, and at the same time, the layer electrode contact and the end surface combustion mode ensure that the same end surface can burn stably; through the resistance monitor and voltage control Cooperate with the device, adjust the applied voltage, and ensure a certain amount of thrust; use the electrode pins to cooperate with the fixed sealing end, which can not only seal the combustion chamber, but also be easy to assemble with external missiles or aircraft to achieve rapid installation and disassembly. Purpose.

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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