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Rocket nozzle applied to RBCC engine and RBCC engine

A technology of engines and rockets, which is applied in the field of aerospace engines, can solve problems such as poor performance, and achieve the effects of increasing the thrust-to-weight ratio, shortening the length, and reducing the length

Active Publication Date: 2021-04-09
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, in the current design of rocket nozzles, none of them can meet the requirements of rapid mixing of rocket jet and air in a very short range while ensuring low energy loss, and the performance is poor.

Method used

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  • Rocket nozzle applied to RBCC engine and RBCC engine
  • Rocket nozzle applied to RBCC engine and RBCC engine
  • Rocket nozzle applied to RBCC engine and RBCC engine

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Embodiment Construction

[0025] In order to make the above objects, features and advantages of the present invention more comprehensible, specific implementations of the present invention will be described in detail below in conjunction with the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, the present invention can be implemented in many other ways different from those described here, and those skilled in the art can make similar improvements without departing from the connotation of the present invention, so the present invention is not limited by the specific embodiments disclosed below.

[0026] The terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of indicated technical features. Thus, the features defined as "first" and "second" may explicitly or ...

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PUM

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Abstract

The invention relates to a rocket nozzle applied to an RBCC engine and the RBCC engine. According to the rocket nozzle applied to the RBCC engine, the RBCC engine is provided with an inner flow channel, the rocket nozzle is arranged in the inner flow channel, the rocket nozzle comprises a throat part and an outlet, the throat part is round, and the area of the throat part is A1; the outlet communicates with the throat part and is positioned on the isolation section of the inner flow channel, the outlet is not round, and the area of the outlet is A2; the numerical value of A2 is estimated through the following mathematical model, so that when the RBCC engine is in the design working condition, jet flow of the rocket nozzle and injected air meet the pressure matching condition, K is the specific heat ratio of fuel in the rocket nozzle, Mat is the Mach number of the outlet, Pts is the total pressure of the injected air, and Ptp is the total pressure of the rocket.

Description

technical field [0001] The invention relates to the technical field of aerospace engines, in particular to a rocket nozzle applied to an RBCC engine and an RBCC engine. Background technique [0002] The speed range of the engine is an important design index of the engine. A wide speed range means a wider application range of the engine. The larger the flight envelope range, the more practical the engine and the wider the application prospect. RBCC (Rocket-Based Combined Cycle, rocket-based combined cycle propulsion system) engine breaks through the limitations of conventional air-breathing ramjet engines, can work at a wider flight Mach number, and has a wide range of applications. [0003] However, for a conventional geometrically non-adjustable RBCC engine, the engine is in the ejection mode at a lower Mach number. At this time, the engine needs to use the internal rocket to pressurize the inhaled air. In order to further increase the thrust, the rocket jet and the air nee...

Claims

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Application Information

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IPC IPC(8): F02K9/97F02K7/18
CPCF02K7/18F02K9/97
Inventor 顾瑞孙明波蔡尊李佩波姚轶智王泰宇
Owner NAT UNIV OF DEFENSE TECH
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