Integrated rocket ejector engine assembly and engine thereof

A technology for ejector rockets and engines, which is applied in the field of small-sized integrated ejector rocket engine components and their engines, can solve the problems of no module installation, poor mixing, and no consideration of the influence of air flow, so as to reduce the impact, The effect of improving the ejection ability and reducing the thickness

Pending Publication Date: 2019-12-20
HUNAN AIRTOPS INTELLIGENT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Among the above-mentioned different RBCC configuration schemes, the scheme in which the ejector rocket is arranged on the top wall of the exit of the isolation section has poor mixing between the primary flow and the secondary flow; the scheme in which the ejector rocket is arranged in the ce...

Method used

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  • Integrated rocket ejector engine assembly and engine thereof
  • Integrated rocket ejector engine assembly and engine thereof
  • Integrated rocket ejector engine assembly and engine thereof

Examples

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Embodiment 1

[0062] see Figure 1-12 , Embodiment 1 of the present invention provides an integrated ejector rocket engine assembly, comprising: a ram inlet 1, three support plates and an ejection rocket 7, and the three support plates are respectively an oxidant support plate 2 and a fuel support plate 3 1. Pressure measuring circuit board 4; the three boards hang the ejector rocket 7 in the ram inlet 1; the three boards in the embodiment of the present invention hang the ejector rocket 7 in the center of the ram inlet 1 place. One end of the oxidizer support plate 2, the fuel support plate 3, and the pressure measurement circuit board 4 is connected to the ejection rocket 7, and the other end of the oxidant support plate 2, the fuel support plate 3, and the pressure measurement circuit board 4 is connected to the ram air inlet 1;

[0063] The embodiment of the present invention adopts the mode of central layout, and the ejector rocket 7 is suspended on the ram air inlet 1 by three suppor...

Embodiment 2

[0109] Embodiment 2 of the present invention is a rocket-based combined cycle engine, comprising the engine assembly described in Embodiment 1, and the engine assembly is respectively connected to the flow channel of the previous stage and the flow channel of the latter stage by stamping the wall flange 14. connect.

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Abstract

The invention provides an integrated rocket ejector engine assembly. The integrated rocket ejector engine assembly comprises a stamping gas inlet path, three support plates and a rocket ejector, wherein the three support plates are separately an oxidant support plate, a fuel support plate and a voltage test circuit board; and the three support plates are used for hanging the rocket ejector in thestamping gas inlet path. The invention further provides a rocket based combined cycle engine. The integrated rocket ejector engine assembly can reduce the structural dimension, so that influences on air incoming flow are reduced.

Description

technical field [0001] The invention belongs to the field of rocket-based combined cycle (RBCC) engines, and relates to a small-sized integrated ejector rocket engine assembly and an engine thereof. The integrated ejection rocket engine of the present invention is mainly applicable to the ejection rocket engine using gas-oxygen / fuel in a rocket-based combined cycle (Rocket Based Combined Cycle, RBCC) engine. Background technique [0002] With the continuous exploration of the aerospace field in various countries, the rocket-based combined cycle (RBCC) engine has become one of the most likely to be used in the future space-to-ground propulsion system due to its advantages of reusability and low cost. The RBCC engine is mainly composed of a ram inlet, ejector rocket, ram afterburner, tail nozzle, etc.; the ejector rocket is an important part of the rocket-based combined cycle engine, and it is the main source of engine thrust in the ejection mode. . [0003] At present, coun...

Claims

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Application Information

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IPC IPC(8): F02K7/18F02K9/64F02K9/52F02K9/44
CPCF02K7/18F02K9/64F02K9/52F02K9/44
Inventor 黄超席文雄罗世彬
Owner HUNAN AIRTOPS INTELLIGENT TECH CO LTD
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