马赫数0至8范围RBCC发动机特性

刘昊

doi:10.7638/kqdlxxb-2021.0132

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马赫数0至8范围RBCC发动机特性

专栏——吸气式组合动力 | 更新时间：2026-05-28

- 马赫数0至8范围RBCC发动机特性
- Characteristic analysis of RBCC engine at Mach number 0 to 8
- 空气动力学学报 2022年40卷第1期页码：165-180
- 作者机构：
  
  西安航天动力研究所,西安,710100
- 作者简介：
  
  刘昊*（1984-），男，陕西蓝田人，研究员，研究方向：组合推进技术. E-mail：ganeland@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0132
  中图分类号： V430
- 纸质出版：2022
- 稿件说明：
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刘昊. 马赫数0至8范围RBCC发动机特性[J]. 空气动力学学报, 2022, 40(1): 165−180.

LIU Hao. Characteristic analysis of RBCC engine at Mach number 0 to 8[J]. 2022, 40(1): 165-180.
刘昊. 马赫数0至8范围RBCC发动机特性[J]. 空气动力学学报, 2022, 40(1): 165−180. DOI： 10.7638/kqdlxxb-2021.0132

LIU Hao. Characteristic analysis of RBCC engine at Mach number 0 to 8[J]. 2022, 40(1): 165-180. DOI： 10.7638/kqdlxxb-2021.0132.

摘要

为获得飞行马赫数

= 0～8 RBCC发动机特性及结构调节规律，基于试验数据，建立了采用控制体法，考虑热完全气体效应、化学平衡流动效应、黏性损失及热损失等影响的发动机特性分析模型，并通过发动机自由射流试验获得的推力、比冲数据对所建立的发动机特性分析模型进行确认。完成二元中心火箭布局变结构模型RBCC发动机火箭引射模态、火箭冲压模态及冲压模态特性仿真，定量获得了飞行动压、马赫数、攻角、当量比、火箭流量等因素变化对发动机性能影响；并针对给定模拟飞行弹道，完成

= 0～8 RBCC发动机特性计算，给出了进气道收缩比、燃烧室扩张比、尾喷管扩张比、发动机总面积比随飞行马赫数及工作模态变化规律。研究表明：1）火箭引射模态，马赫数每增加1，推力、比冲增加约18.2%，火箭推力增益增加约15%；2）火箭冲压模态，火箭流量越大，火箭推力增益越小，且获得正的火箭推力增益范围越窄；3）

= 2模态转换点，发动机性能及结构参数均存在间断，确保推力及结构参数的连续调节、匹配应是模态转换规律制定的关注点；4）模拟弹道下，进气道收缩比、燃烧室扩张比、尾喷管扩张比、发动机总面积比在

= 0～8范围内分别变化6.17、4.26、30.38、8.94倍。

Abstract

In order to obtain the characteristics and structural regulation law of the RBCC (Rocket-Based Combined-Cycle) engine in a flight Mach number range of

= 0～8

an engine characteristic analysis model is established based on experimental data

which adopts the control volume method and takes into account the effects of heat complete gas

chemical equilibrium flow

viscosity loss

heat loss

etc. The model is then ver

ified using the thrust and specific impulse data obtained in a free-jet experiment. Characteristics of the RBCC engine of two-dimensional variable structures are analyzed for three operation modes

i.e. the injector operation mode

the ramjet operation mode and the rocket ramjet mode. Effects of the flight dynamic pressure

Mach number

angle of attack

equivalent ratio and rocket flow rate on the performance of the model engine are quantitatively obtained. A characteristic analysis is carried out for the

= 0～8 RBCC engine along a simulated trajectory

and variations with the flight Mach number at different engine operation modes are given for the air inlet contraction ratio

combustor expansion ratio

nozzle expansion ratio

total area ratio. The results show that: 1) Under the ejector operation mode

for every increasement of one in the flight Mach number

the engine thrust and specific impulse are increased by about 18.2%

and the rocket thrust gain is increased by about 15%. 2) Under the ramjet operation mode

with the increase of the rocket flow rate

the rocket thrust gain decreases

and the larger the rocket flow rate is

the narrower the positive rocket thrust gain range is. 3) During the operation mode transformation at

= 2

the performance and structural parameters of the engine are both discontinoues

thus special attention needs to be put for the continuous adjustment of the thrust and structural parameters of the engine. 4) Under the given simulated trajectory

the inlet contraction ratio

the combustor expansion ratio

the nozzle expansion ratio and the engine total area ratio vary 6.17

4.26

30.38

8.94 times in the range of

= 0～8

respectively.

关键词

Keywords

references

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