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...

Examples

Embodiment Construction

[0027] Below in conjunction with accompanying drawing, the present invention will be further described

[0028] Such as figure 1 As shown, the present invention includes a combustion chamber housing 1, a corundum insulating layer 2, a silicon rubber insulating layer 3, a heat protection layer 4, an electrode fixing sleeve 5, a combustion surface electrode 6, a nozzle 7, an asbestos gasket 8, an electric control solid Propellant grain 9, electrode fixing device 10, sliding electrode 11, spring 12, voltage controller 13, fixed sealing end 14, electrode pin 15, resistance monitor 16 and lead terminal insulating plate 17. The electronically controlled solid propellant grain 9 is installed in the combustion chamber housing 1, the front end of the electrically controlled solid propellant grain 9 is in contact with the combustion surface electrode 6, and the rear end is in contact with the sliding electrode 11, and the spring 12 pushes the sliding electrode 11 and The electrically c...

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...

Examples

Embodiment Construction

[0027] Below in conjunction with accompanying drawing, the present invention will be further described

[0028] Such as figure 1 As shown, the present invention includes a combustion chamber housing 1, a corundum insulating layer 2, a silicon rubber insulating layer 3, a heat protection layer 4, an electrode fixing sleeve 5, a combustion surface electrode 6, a nozzle 7, an asbestos gasket 8, an electric control solid Propellant grain 9, electrode fixing device 10, sliding electrode 11, spring 12, voltage controller 13, fixed sealing end 14, electrode pin 15, resistance monitor 16 and lead terminal insulating plate 17. The electronically controlled solid propellant grain 9 is installed in the combustion chamber housing 1, the front end of the electrically controlled solid propellant grain 9 is in contact with the combustion surface electrode 6, and the rear end is in contact with the sliding electrode 11, and the spring 12 pushes the sliding electrode 11 and The electrically c...

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