Axis-symmetric structure RBCC (rocket based combined cycle) whole flow passage with multistage rocket

Abstract

The invention discloses an axis-symmetric structure RBCC (rocket based combined cycle) whole flow passage with a multistage rocket. The whole flow passage comprises a shell, a center cone is axially arranged in the shell in a sleeving manner, one section of the front end of the center cone goes through the shell, an outer compression section of an air inlet section is formed between the portion going through the shell and an inlet of the shell, an annular passage is formed between the shell and the center cone, an inner compression section of the air inlet section, an isolation section and a combustion chamber section are sequentially formed in the annular passage from front to back, the rear end of the shell is slidably connected with a tail pipe, and the tail pipe is communicated with the annular passage. The shell is slidably connected with the center cone and can slide front and back relative to the center cone in different rocket modes. According to the axis-symmetric structure RBCC whole flow passage with the multistage rocket, structural weight and pneumatic resistance are effectively decreased, corresponding rocket ejectors are selected in different modes, and the performance of the rocket is improved.

Description

technical field [0001] The invention belongs to the technical field of rocket engines, and in particular relates to an axisymmetric structure RBCC full flow passage adopting a multi-stage rocket. Background technique [0002] Rocket ramjet combination (RBCC) engines usually use a variable-structure inlet with adjustable throat area and a variable-structure exhaust nozzle with adjustable expansion area in order to work in a wide Mach number range. For the variable structure intake port of the binary structure, the adjustment of the throat area will cause the inlet part of the combustion chamber to adjust with the throat of the intake port or form a stepped structure, which is unfavorable for the performance of the engine and the realization of sealing; for the variable structure tail nozzle , because the matching aircraft rear body cannot be adjusted or the adjustment cost is relatively high, so the adjustment of the expansion area of ​​the tail nozzle can only be partially a...

AI Technical Summary

Problems solved by technology

[0003] RBCC engines usually only use single-stage rockets. When the engine works in the ejection mode, the contact area between the single-stage rocket plume and the air is small, and the ability to do work on the air is weak, resulting in insufficient air suction capacity of the engine ejection, and due to the The total pressure of incoming air in the injection mode is low, and the energy exchange between the rocket plume and the air is insufficient, which limits the total pressure of the air flowing into the engine combustion chamber, resulting in the failure of the engine to obtain better performance in the injection mode.

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