Combustion chamber casing of a double pulse engine and its forming method

Abstract

The invention discloses a double-pulse engine combustion chamber casing and a molding method. Through the design of the double-pulse engine combustion chamber casing and the isolation device, material optimization, process and structure optimization, composite materials are selected as the isolation device and the combustion chamber casing When molding, the composite material isolation device is formed first, and then the combustion chamber casing is integrally poured into one body. The prepared dual-pulse engine combustion chamber shell is light in weight, and there is no opening in the center of the isolation device, and no other sealing structure is needed, and the seal is tight. In addition, the isolation device is also an integral composite material structure, which is light in weight and resistant to high internal pressure / The working environment with low pressure and strong pressure is stable and reliable. Guarantee the sealing performance of the isolating device to the shells of the double pulse and two combustion chambers, eliminate gaps, make the seal tight, and have simple molding methods, light weight, high reliability, and low cost. Installed efficiency.

Description

Technical field [0001] The present invention belongs to the field of aerospace technology, and in particular, the present invention relates to a two-pulsed engine combustion chamber housing and a molding method. Background technique [0002] Double pulse engine uses an isolation device to divide the combustion chamber of the solid engine into two parts, performs two ignitions, reasonably dispensing thrust, and two pulse interval, and realizes the optimal control of the missile flight ballistic and the optimal management of engine energy, and improves various types. The performance of the tactical missile system. At present, the double pulse engine combustion chamber housing is divided into two types of integral steel structures and integral fiber winding structures, and the two pulse engines are separated from the isolation device. [0003] Now the double pulse engine combustion chamber structure is formed separately from the housing and the isolation device, the housing and the ...

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Problems solved by technology

[0008] The present invention aims at the disadvantages of the prior art, such as the heavy weight of the combustor casing of the double-pulse engine, the difficulty in sealing the isolation device, and the inability to withstand a large high internal pressure / low pressure collapse pressure ratio, etc., and provides a combustor casing of the double-pulse engine and Molding method, according to the bearing requirements of the dual-pulse engine combustion chamber casing and isolation device, composite materials are selected as the material of the isolation device and combustion chamber casing, EPDM or nitrile rubber is used as the insulation structure, carbon fiber / epoxy The composite material is used as the load-bearing structure, and the isolation device divides the combustion chamber shell into two parts, and the isolation device meets the application environment of the first-order pulse high internal pressure and the second-order pulse low pressure collapse pressure, so as to reduce the inertia weight of the engine and increase the missile's effective range

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