PDF下载 分享
[1]赵宏亮,张蒙正.超燃冲压发动机推阻力特性研究综述[J].火箭推进,2014,40(06):41-45.
　ZHAO Hong-liang,ZHANG Meng-zheng.Investigation of thrust/drag property of scramjet[J].Journal of Rocket Propulsion,2014,40(06):41-45.
点击复制

超燃冲压发动机推阻力特性研究综述

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 40 期数: 2014年06期 页码: 41-45 栏目: 研究与设计 出版日期: 2014-12-29
Title:
Investigation of thrust/drag property of scramjet
作者:
赵宏亮; 张蒙正
西安航天动力研究所，陕西 西安 710100
Author(s):
ZHAO Hong-liang;  ZHANG Meng-zheng
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
关键词:
超燃冲压发动机; 推阻力特性; 研究方法; 测量技术
Keywords:
scramjet;  thrust characteristic;  research method;  measurement technology
分类号:
V434-34
文献标志码:
A
摘要:
超燃冲压发动机由进气道、燃烧室和尾喷管等部件构成，推阻力是其最重要的特性参数。回顾了超燃冲压发动机部件级推阻力特性和整体推阻力特性研究现状，介绍了超燃冲压发动机推阻力特性研究方法和测量技术。建议今后研究过程中关注以下几个问题：研究精确的自由射流试验测量技术，研究流场均匀性对发动机性能的影响，开发高精度仿真平台。
Abstract:
Thrust and drag are the most important characteristic parameters of scramjet, which consists of inlet, combustor and nozzle. The research status of the component-level and the overall thrust/drag characteristics are reviewed in this paper. The research methods and measurement technology for the thrust/drag characteristics of scramjet are introduced. Some suggestions are proposed for the future study: investigating the accurate free-jet test measurement technology, investigating the impact of the flow field uniformity on scramjet performance, and developing the high-precision simulation platform.

参考文献/References:

[1]IGARASHI Y, MITANI T, KODEAR M, et al. Comparative studies on scramjet engine drag by experiments and numerical analysis, AIAA98-1512[R]. USA: AIAA, 1998.
[2]ODAM J, PAULL A. Comparison of experimental thrust measurements with theoretical values for a scramjet engine[C]// AIAA International Space Planes and Hypersonic Systems and Technologies. [S.l.]: AIAA, 2003: 1-10.
[3]DENNER BW. CFD prediction of inlet spill drag increments, AIAA 98-3566[R]. USA: AIAA, 1998.
[4]CONNERS T R, HOWE D C. Supersonic inlet shaping for dramatic reductions in drag and sonic boom strength, AIAA 2006-30[R]. USA: AIAA, 2006.
[5]金志光, 张堃元. 典型二元高超声速进气道与侧压式进气道的性能比较[J]. 航空动力学报, 2008, 23(9):1553- 1560.
[6]卫永斌, 张元, 骆晓臣. 二元高超声速进气道内部阻力特性分析与研究[J]. 空气动力学报, 2010, 28(1): 104-108.
[7]卫永斌, 张元. 三维侧压式高超声速进气道阻力特性分析[J]. 航空动力学报, 2009, 24(7): 1594-1600.
[8] 常军涛, 鲍文, 崔涛, 等. 抽吸对高超声速进气道抗反压能力的影响[J]. 航空动力学报, 2008, 23(3): 505-509.
[9]LUO Shi-bin, HUANG Wei. Drag force chara- cteristic of a typical dual-mode scramjet com- bustor[C]// 2010 2nd International Conference on Computer Engineering and Technology. [S.l.]: [s.n.], 2010(5): 255-259.
[10]王兰, 邢建文, 郑忠华, 等. 超燃冲压发动机内流性能的一维评估[J]. 推进技术, 2008, 29(6): 641-645.
[11]吴先宇, 李小山, 丁猛, 等. 超燃冲压发动机燃烧室构型对燃烧室性能影响[J]. 2008, 29(3): 300- 305.
[12]苏义,刘卫东. 支板阻力特性实验[J]. 航空动力学报,2009, 24(12): 2643-2648.
[13]潘余, 丁猛. 超燃冲压发动机凹腔火焰稳定器阻力分析[J]. 推进技术, 2009, 30(5): 518-522.
[14]GENIN F, MENON S. LES of supersonic combustion of hydrocarbon spray in a scramjet, AIAA 2004-4132[R]. USA: AIAA, 2004.
[15]黄伟, 柳军, 罗世彬, 等. 凹腔布局对高超声速飞行器气动-推进性能影响[J]. 固体火箭技术, 2010, 33(2): 138- 141.
[16]潘余, 丁猛, 梁剑寒, 等. 超燃冲压发动机多凹腔串联燃烧室阻力研究[J]. 航空学报, 2010, 31(1): 70-75.
[17]HSU K Y. Experimental study of cavity-strut combustion in supersonic flow, AIAA 2007- 5394[R]. USA: AIAA, 2007.
[18]CHANG Xin-yu, GU Hong-bin, CHEN Li-hong. Thrust and drag of a scramjet model with different combustor geometries, AIAA 2005-3315[R]. USA: AIAA, 2005.
[19]陈立红, 顾洪斌, 张新宇. 支板凹腔一体化超燃冲压发动机实验研究[J].工程热物理学报, 2007, 28(4): 717- 719.
[20]MARATHE A G, THIAGARAJAN V. Effect of geometric parameters on the performance of single expansion ramp nozzle, AIAA 2005-4429[R]. USA: AIAA, 2005.
[21]MEISS J H, MEINKE M. Numerical investigation to enhance the thrust vector of a scramjet nozzle, AIAA 2011-2346[R]. USA: AIAA, 2011.
[22]COCHRAN R B. Hypersonic nozzle/afterbody performance at low mach numbers, AD-A216 223[R]. USA: Air Force Inst. of Tech., 1989.
[23]LU Xin, YUE Lian-jie. Design of scramjet nozzle employing streamline tracing technique, AIAA 2009-7248 [R]. USA: AIAA, 2009.
[24]全志斌, 徐惊雷, 莫建伟. 单边膨胀喷管膨胀型面的非线性缩短设计[J]. 推进技术, 2012, 33(6): 951-955.
[25]莫建伟, 徐惊雷, 全志斌. 截短单边膨胀喷管的试验和数值模拟[J]. 推进技术, 2012, 33(6): 940 -945.
[26]FERGUSON F, DHANASAR M. A model for the design and analysis of thrust optimized scramjets, AIAA 2009- 7337[R]. USA: AIAA, 2009.
[27]KLICHE D, MUNDT C. Combustor modelling for multidisciplinary analysis and evaluation of supersonic combustion ramjets, AIAA 2009-7282[R]. USA: AIAA, 2009.
[28]王兰, 邢建文, 郑忠华, 等. 超燃冲压发动机内流性能的一维评估[J]. 推进技术, 2008, 29(6): 641-645.
[29]任鑫, 罗春钦, 董建明, 等. 超燃冲压发动机性能的准二维计算方法[J].推进技术, 2013, 34(4):457-462.
[30]贺伟, 于时恩, 李宏斌. 高超声速一体化飞行器推阻特性测量研究[J]. 试验流体力学, 2010, 4(2): 65-68.
[31]LOCKWOOD M K, PETLEY D H, HUNT J L, et al. Airbreathing hypersonic vehicle design and analysis methods, AIAA 96-0381[R]. USA: AIAA, 1996.
[32]郑日恒. 法国冲压发动机研究进展[J]. 航天制造技术,2006, 4(2): 6-10.
[33]马洪强, 高贺, 毕志献. 高超声速飞行器相关的摩擦阻力直接测量技术[J]. 试验流体力学, 2011, (25)4: 83-88.

相似文献/References:

[1]朱舒扬.全尺寸超燃冲压发动机推力测量台架研制[J].火箭推进,2015,41(05):106.
　ZHU Shuyang.Development of thrust measurement platform for full-scale scramjet[J].Journal of Rocket Propulsion,2015,41(06):106.
[2]姚照辉,李光熙,张蒙正,等.燃油分配对超燃冲压发动机的性能影响仿真分析[J].火箭推进,2013,39(04):30.
　YAO Zhao-hui,LI Guang-xi,ZHANG Meng-zheng,et al.Simulation and analysis for influence of fuel distribution on scramjet performance[J].Journal of Rocket Propulsion,2013,39(06):30.
[3]刘 昊,李光熙,杜 泉,等.超燃冲压发动机全流道反应流场仿真分析[J].火箭推进,2013,39(06):1.
　LIU Hao,LI Guang-xi,DU Quan,et al.Numerical simulation of reaction flow field in full flowpath of scramjet[J].Journal of Rocket Propulsion,2013,39(06):1.
[4]张 倩,王 兵,张耘隆,等.RBCC的可实现性方案—DRBCC分析[J].火箭推进,2014,40(05):1.
　ZHANG Qian,WANG Bing,ZHANG Yun-long,et al.An analysis of RBCC realizability scheme: DRBCC[J].Journal of Rocket Propulsion,2014,40(06):1.
[5]张蒙正,邹 宇.美国典型高超飞行器项目研发及启示[J].火箭推进,2012,38(02):1.
　ZHANG Meng-zheng,ZOU Yu.Development of American typical hypersonic flight vehicles and its enlightenment[J].Journal of Rocket Propulsion,2012,38(06):1.
[6]李龙飞,王延涛,杨伟东,等.超声速燃烧地面试验的蓄热式加热器及其关键技术[J].火箭推进,2012,38(02):16.
　LI Long-fei,WANG Yan-tao,YANG Wei-dong,et al.Thermal energy storage heater and its key technologies for supersonic combustion ground test facilities[J].Journal of Rocket Propulsion,2012,38(06):16.
[7]文 科,李旭昌,马岑睿,等.不同入口马赫数对超燃冲压发动机尾喷管的性能影响研究[J].火箭推进,2011,37(03):18.
　WEN Ke,LI Xu-chang,MA Cen-rui,et al.Influence of nozzle inlet Mach number on performance of scramjet nozzle[J].Journal of Rocket Propulsion,2011,37(06):18.
[8]冯锦虎,高峰,何至林.超燃冲压发动机隔离段内附面层/激波串相互干扰研究[J].火箭推进,2010,36(02):5.
　Feng Jinhu,Gao Feng,He Zhilin.Investigation of boundary layer/shock wave train interference in a scramjet isolator[J].Journal of Rocket Propulsion,2010,36(06):5.
[9]王玉峰,吴宝元,王东东.变比热对超燃冲压发动机尾喷管设计的影响分析[J].火箭推进,2010,36(02):43.
　Wang Yufeng,Wu BaoYuan,Wang Dongdong.Scramjet engine nozzle design with variable specific heat[J].Journal of Rocket Propulsion,2010,36(06):43.
[10]杨事民,唐豪,黄胡.凹腔超声速燃烧室氢气燃烧流场数值模拟[J].火箭推进,2008,34(01):12.
　Yang Shimin,Tang Hao,Huang Yue.Numerical simulation of hydrogen combustion on flow field in supersonic combustor with cavity[J].Journal of Rocket Propulsion,2008,34(06):12.

备注/Memo

收稿日期：2014-08-13；修回日期：2014-08-29 作者简介：赵宏亮（1989—），男，硕士研究生，研究领域为发动机燃烧过程

更新日期/Last Update: 1900-01-01