某高超声速弹用发动机安装特性分析

商旭升; 蔡元虎; 李京伟

doi:10.15892/j.cnki.djzdxb.2013.06.009

弹箭与制导学报 >

2013 , Vol. 33 >Issue 6: 99 - 102,109

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2013.06.009

导弹与制导技术

某高超声速弹用发动机安装特性分析

商旭升 ,
蔡元虎 ,
李京伟

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1 海军装备研究院，北京 100161
2 西北大业大学动力与能源学院，西安 710072
3 海军司令部，北京 100841

商旭升(1966 －) ，男，河北任丘人，研究员，博士，研究方向: 航空发动机总体性能设计。

收稿日期: 2013-02-08

网络出版日期: 2025-05-26

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A Hypersonic Missile Engine’s Installing Characteristic Analysis

SHANG Xusheng ,
CAI Yuanhu ,
LI jingwei

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1 Navel Academy of Armament, Beijing 100161, China
2 School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China
3 Naval Commander Department, Beijing 100841, China

Received date: 2013-02-08

Online published: 2025-05-26

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摘要

摘要:为了评估飞行中发动机的推力与耗油率，在导弹总体设计时必须考虑发动机安装特性。文中基于对发动机总体性能与部件特性的分析，通过建立进气道附加阻力、喷管/后体阻力及进气道与发动机流量匹配计算模型，选择保持动压50kPa的飞行轨迹，对导弹用发动机的安装阻力系数、发动机安装推力、安装耗油率进行了计算。结果表明:进、排气系统的外部阻力使推力降低，耗油率增加。

关键词： 预冷却吸气式发动机; 安装性能; 进气道阻力; 喷管-后体阻力

本文引用格式

商旭升 , 蔡元虎 , 李京伟 . 某高超声速弹用发动机安装特性分析[J]. 弹箭与制导学报, 2013 , 33(6) : 99 -102,109 . DOI: 10.15892/j.cnki.djzdxb.2013.06.009

Abstract

In order to evaluate the thrust and fuel consumption rate of the engine in flight，the overall design of missile engine installation characteristics must be taken into account．In this paper，based on the analysis of the engine overall performance and components charac teristics，through the establishment of inlet additional resistance，nozzle /afterbody drag and engine / inlet flow matching，keep dynamic pressure 50kPa flight trajectory，mounting resistance coefficient，the engine installed thrust，installed fuel consumption rate were calculat ed．The results show that: the external resistance of the inlet and nozzle，reducing the thrust，fuel consumption increase．

Key words： pre-cooling air breathing engine; installation performance; inlet drag; nozzle-afterbody drag

参考文献

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