Structural design of inlet isolation segment of rocket-based-combined-cycle engine

Abstract

The invention discloses structural design of an inlet isolation segment of a rocket-based-combined-cycle engine. Under the restraint that the minimal section of the inlet isolation segment is located in a throat segment, the sectional area of an effective circulation area of the isolation segment is improved, so that the sectional area of the inlet throat segment is increased to be equal to the sectional area of an intake of a combustion chamber, effective circulation area equal-sectional-area circulation is achieved on an inlet rocket supporting plate segment, and an equal straight segment behind the inlet rocket supporting plate segment is improved into a contraction segment so as to be matched with the section of the intake of the combustion chamber. It is ensured that the minimal section area of the inlet isolation segment is located in the throat segment. By means of the inlet isolation segment, the start mach number of an inlet is lowered, and the flow coefficients of the inlet in an injection mode and a ramjet mode and other performance parameters are increased. The design of the inlet isolation segment of the rocket-based-combined-cycle engine is high in development performance, the inlet isolation segment is designed according to different sectional sizes of the intake of the combustion chamber, the work range of the inlet can be effectively expanded, and the overall performance of the engine can be improved.

Description

technical field [0001] The invention relates to the technical field of rocket ramjet engines, in particular to a structural design of an inlet isolation section of a rocket-based combined cycle engine. Background technique [0002] The Rocket-Based-Combined-Cycle (RBCC) engine has potential advantages such as reusability, low cost, and high reliability, and is considered to be one of the propulsion systems most likely to be used in future space-to-ground transportation systems. one. The aircraft with the rocket-based combined cycle engine as the propulsion system can take off from the ground at zero speed and accelerate continuously until it reaches the cruising state during the flight. The working Mach domain includes the subsonic stage, transonic stage, supersonic stage, and hypersonic stage; In space, the rocket-based combined cycle engine has the ability to continuously work from sea level to outside the atmosphere. According to the working altitude and Mach number of ...

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Problems solved by technology

[0003] The variable-structure intake scheme that adjusts the intake lip or compression surface to achieve a wide range of work, although it can broaden the working range of the intake and improve the work of the intake in the ejection mode and sub-combustion mode Performance, but it needs to be supported by a complex mechanical structure, which will bring a series of problems in sealing, ease of realization, and additional structural quality, and the feasibility of the scheme is poor

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