Compact layout type solid rocket fuel gas super-combustion stamping engine based on axial symmetry

Abstract

The invention discloses a compact layout type solid rocket fuel gas super-combustion stamping engine based on axial symmetry. The engine comprises an air inlet and a combustion chamber which are coaxially connected and communicate with each other, wherein the air inlet and the combustion chamber form an engine shell, and the two ends of the engine shell are open; a fuel inlet is formed in the front section shell of the combustion chamber; fuel gas generators are arranged around the circumference of the outer side of the front section shell of the combustion chamber, the fuel gas generators comprise hollow first cylindrical bodies, converging sections, second cylindrical bodies and expanding sections which are connected and communicate in sequence from front to back, the first cylindrical bodies, the converging sections, the second cylindrical bodies and the expanding sections are all double-layer shell structures and form a closed cavity; the circumferences of inner shells at the rearends of the expanding sections protrude towards the central axis; and fuel injecting ports are formed in bulges of the expanding sections and used for injecting fuel into the combustion chamber. According to the stamping engine, the fuel gas generators are arranged on the outer wall of the front section of the combustion chamber, the minimum size limitation, caused by the placement of the fuel gasgenerators, of the air inlet dose not exist, and the length of the air inlet can be reduced.

Description

technical field [0001] The invention belongs to the field of aerospace science and technology, and in particular relates to an axisymmetric compact layout solid rocket gas scramjet. Background technique [0002] The solid rocket gas scramjet engine uses the fuel-rich gas produced by the gas generator to mix and burn with air to produce high-temperature gas, and the thrust is generated by the expansion of the nozzle. The schematic diagram is as follows figure 1 shown. Compared with the liquid scramjet, it has the advantages of simple structure, low cost, short combat response time, good maneuverability and safety, and long storage time. Compared with the solid fuel scramjet, it has the advantages of easy flow adjustment and no Ignition and flame stability problems, the working process of the combustion chamber is less affected by the incoming flow parameters, and the working time is long. Therefore, the solid rocket gas scramjet has a good application prospect [1-3]. [000...

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Problems solved by technology

[0003] At present, the research on solid rocket gas scramjet at home and abroad is still in its infancy. Domestic Lu Zhong designed two schemes of head and side air intake, and verified the solid rocket gas scramjet through numerical simulation and experimental research. The feasibility of [1]; Liu Zai, Chen Linquan and others carried out the impact analysis of the afterburner configuration of solid rocket gas scramjet. For the pure gas phase combustion products, the length of the afterburner and the expansion angle of the afterburner were analyzed. The influence of combustion chamber performance[3]; Li Xuan, Ma Lifeng et al. carried out the simulation research on the performance of solid rocket gas scramjet engine. For the combustion products of pure gas phase, the two mixed enhancement methods of concave cavity and spoiler were studied respectively. Influence of the mixed combustion performance of the afterburner[4]

In the gun-launched extended-range missile, it is necessary to use a solid rocket gas scramjet engine to further increase its range. However, the missile has strict requirements on the projectile diameter and projectile length. If the gas generator is placed in the inlet cone, it will Increase the length of the intake port. Under the small bullet diameter, it is more difficult for the incoming air to enter the combustion chamber at a high Mach number.

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