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弹箭与制导学报 >

2022 , Vol. 42 >Issue 5: 117 - 122

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2022.05.022

多变量调节固冲发动机性能分析

  • 王远远 1 ,
  • 孙振华 1, 2 ,
  • 沈欣 3 ,
  • 贺永杰 1, 2
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  • 1 中国空空导弹研究院,河南 洛阳 471009
  • 2 航空制导武器航空科技重点实验室,河南 洛阳 471009
  • 3 空装驻洛阳地区第一军事代表室,河南 洛阳 471009

王远远(1996—),男,河南洛阳人,硕士研究生,研究方向:冲压发动机总体设计。

收稿日期: 2021-07-13

  网络出版日期: 2025-01-16

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Performance Analysis of Multivariable-adjustable Ducted Rocket

  • WANG Yuanyuan 1 ,
  • SUN Zhenhua 1, 2 ,
  • SHEN Xin 3 ,
  • HE Yongjie 1, 2
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  • 1 China Airborne Missile Academy, Luoyang 471009, Henan, China
  • 2 Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons, Luoyang 471009, Henan, China
  • 3 The First Military Representative Office of Air Force Equipment Department in Luoyang, Luoyang 471009, Henan, China

Received date: 2021-07-13

  Online published: 2025-01-16

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摘要

针对多变量调节、喷管调节、进气道调节及定几何固冲发动机开展全飞行包线工作性能数值仿真,对比分析了不同类型固冲发动机不同工况下工作性能的分布情况和具体差异。结果表明,可调喷管可提高小喉径不可调喷管低空低速和大喉径不可调喷管高空高速时的推力性能;低速和高速状态下可调进气道和可调喷管分别对推力提升作用更大;在使用可调喷管的基础上使用可调进气道不仅能最大限度提高发动机推力和比冲,还可扩大发动机的正常工作包线;与中等喷管喉径定几何固冲发动机相比,多变量调节固冲发动机在高度为5 km,速度为Ma 2.5时推力提高24%,在高度为20 km,速度为Ma 4时比冲提高26%。

关键词： 多变量调节; 固冲发动机; 性能分析; 进气道; 喷管; 全包线; 数值仿真

本文引用格式

王远远 , 孙振华 , 沈欣 , 贺永杰 . 多变量调节固冲发动机性能分析[J]. 弹箭与制导学报, 2022 , 42(5) : 117 -122 . DOI: 10.15892/j.cnki.djzdxb.2022.05.022

Abstract

Directed against ducted rockets of multivariable-adjustable, adjustable-nozzle, adjustable-inlet and fixed-geometry, this paper carries out numerical simulation of working performance in full flight envelope curve. Then, compared and analyzed the conversion and specific difference of working performance of different types ducted rockets under different operating conditions. Results show that, adjustable-nozzle can improve the thrust performance of small throat diameter nonadjustable-nozzle at low altitude and low speed, as well as large throat diameter nonadjustable-nozzle at high altitude and high speed. Adjustable-inlet improves thrust great at low speed and adjustable-nozzle at high speed. On the basis of using adjustable-nozzle, using adjustable-inlet can not maximize the thrust and specific impulse,but also expand the normal working envelope. Compared with the nozzle of medium throat diameter fixed-geometry ducted rocket, the thrust of multivariable-adjustable at 5 km/Ma 2.5 is increased by 24%, and the specific impulse at 20 km/Ma 4 is increased by 26%.

Key words： multivariable-adjustable; ducted rocket; performance analyzed; inlet; nozzle; full flight envelope curve; numerical simulation

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