航天推进技术研究院主办
[1]杜炜强,吴宝元.高超声速进气道优化设计初探[J].火箭推进,2007,33(06):17-21.
Du Weiqiang,Wu Baoyuan.Investigation on optimization design of scramjet inlet[J].Journal of Rocket Propulsion,2007,33(06):17-21.
点击复制
Du Weiqiang,Wu Baoyuan.Investigation on optimization design of scramjet inlet[J].Journal of Rocket Propulsion,2007,33(06):17-21.
高超声速进气道优化设计初探
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
33
期数:
2007年06期
页码:
17-21
栏目:
研究与设计
出版日期:
2007-12-28
- Title:
- Investigation on optimization design of scramjet inlet
- 分类号:
- V430
- 文献标志码:
- A
- 摘要:
- 以总压恢复系数为目标,利用无粘流斜激波关系式和约束最优化计算方法,在考虑混合气体比热随温度变化的条件下,对二维混压式高超声速进气道设计方法作了初步探索,利用数值模拟软件对附面层作了修正,研究了进气道的基本性能。数值模拟结果表明:该进气道在飞行马赫数Ma=4～6.5范围内能够可靠工作。
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]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.
ZHAO Hong-liang,ZHANG Meng-zheng.Investigation of thrust/drag property of scramjet[J].Journal of Rocket Propulsion,2014,40(06):41.
[6]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.
[7]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.
[8]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.
[9]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.
[10]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.
更新日期/Last Update:
1900-01-01