Aluminum film baffle device and pulse solid engine applying same

Abstract

The invention discloses an aluminum film baffle device and a pulse solid engine applying the same. The aluminum film baffle device takes a flexible aluminum film baffle as a fracture element and is matched with a hollow-carved baffle support in a cross-shaped supporting structure. The aluminum film baffle can bear high pressure and cannot be fractured in the direction where the aluminum film baffle is supported by the baffle support while the flexible aluminum film baffle can be fractured easily in the direction where the aluminum film baffle is not supported by the baffle support. One side of the aluminum baffle, which cannot be fractured, is dead against a first pulse grain so as to prevent the aluminum baffle from being fractured during the burning process of the first pulse grain of the engine. Therefore, a second pulse grain of the engine can be protected. When the second pulse grain is ignited, the aluminum film baffle rapidly is fractured so that gas passes through the aluminum film baffle device. The device provided by the invention has stable and reliable performance and the material of the baffle is easy to get and process. The fragments of the fractured aluminum film baffle can not affect the operation of the engine and the device has no special requirements on a loading device and an igniter.

Description

technical field [0001] The invention relates to an aluminum film partition device and a pulse solid motor using the aluminum film partition device, and belongs to the technical field of multiple ignition and starting of solid rocket motors. Background technique [0002] Due to the advantages of simple structure and good reliability, solid rocket motors have been widely used in the fields of weapons and aerospace. However, compared with other forms of engines, the lack of flexibility in energy management of solid rocket motors is a great weakness. In tactical missiles, the general solid propulsion system adopts a boost-cruise propulsion mode, that is, a two-stage engine or a single-chamber dual-propulsion engine. In this propulsion mode, from the moment of launch, the missile will continue to accelerate until the engine is shut down and reaches the maximum flight speed, and then enters the state of inertial flight. Since the flight resistance of the missile is proportional ...

AI Technical Summary

Problems solved by technology

However, these solutions all have certain insurmountable limitations. For example, the first two partition devices mentioned above have the disadvantages of large randomness in work performance and large engine thrust loss, while the flexible flame-retardant layer partition device needs to adopt a specific The form of charge and igniter has relatively large restrictions on the overall design of solid rocket motors

In addition, the fragments produced after the rupture of the above separators are not easy to be ablated, which will have a certain impact on the operation of the engine.

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