Multi-stage rotary detonation rocket ramjet combined engine

A rocket engine and ramjet technology, which is applied in the direction of combined engines, rocket engine devices, ramjet engines, etc., can solve the problems of insufficient air suction, low ejection efficiency, and small thrust gain, etc. Improve injection boosting efficiency, improve working stability, and realize the effect of thrust performance

Active Publication Date: 2021-07-23
HUAZHONG UNIV OF SCI & TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] Among them, the traditional RBCC engine has the following problems: in the injection mode (below Ma2), the thrust gain is small, the specific impulse is low, and the a

Method used

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  • Multi-stage rotary detonation rocket ramjet combined engine
  • Multi-stage rotary detonation rocket ramjet combined engine
  • Multi-stage rotary detonation rocket ramjet combined engine

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Embodiment Construction

[0032] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.

[0033] The invention provides a multi-stage rotary detonation rocket ramjet combination engine, comprising: a ramjet and a multi-stage rotary detonation rocket engine embedded between the ramjet inlet and the combustion chamber; wherein, the multi-stage rotary detonation rocket The engine includes a plurality of single-stage rotary detonation rocket engines distributed in steps, and adopts a com...

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Abstract

The invention discloses a multi-stage rotary detonation rocket ramjet combined engine, and belongs to the field of combined engines. The combined engine comprises a ramjet engine, and a multi-stage rotary detonation rocket engine embedded between an air inlet channel and a combustion chamber of the ramjet engine, wherein the multi-stage rotary detonation rocket engine comprises a plurality of single-stage rotary detonation rocket engines distributed in a stepped mode, and thrust is provided in a rotary detonation combustion mode; and according to the whole engine system, the ramjet engine and the multi-stage rotary detonation rocket engine jointly generate thrust. Compared with a single-stage rotary detonation structure, the multi-stage rotary detonation structure can enable multi-stage rotary detonation to jointly generate an ejection and suction combination in a rocket ejection mode with a low Mach number, and the low-speed ejection pressurization efficiency is improved; in a subsonic combustion and scramjet mode, the positions of induced flames and a flame stable area can be adjusted, the working stability of the engine is improved, meanwhile, a larger thrust range can be provided, thrust adjustment is more flexible, and the thrust performance is improved.

Description

technical field [0001] The invention belongs to the technical field of combined engines, and more specifically relates to a multi-stage rotary detonation rocket ramjet combination engine. Background technique [0002] With the development of aerospace technology, human exploration in the field of outer space continues to increase, and the concept of various new aerospace vehicles has sprung up, which is more and more important for improving the propulsion power of the aircraft and improving the structure of the engine to adapt to the flight of a wider speed range. higher demand. [0003] There are many deficiencies or limitations in a single engine for working in a wide speed range, and combined cycle engines such as TBCC, RBCC, T-RBCC, and SABER have evolved. The combined engine is an engine combined with two or more engines with different working principles (different types), and it is suitable for aircraft with a wide flight speed range and large altitude changes. figur...

Claims

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Application Information

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IPC IPC(8): F02K9/76F02K7/18F02C7/057F02K1/15
CPCF02K9/76F02K7/18F02C7/057F02K1/15
Inventor 陈文娟朱澳星罗飞腾龙垚松
Owner HUAZHONG UNIV OF SCI & TECH
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