scramjet

scramjet

1. And over the next several decades, the scramjet work could eventually provide China with a tactical hypersonic global-strike capability beyond the country's strategic ballistic missile force.

“中国是具备在军事上和美国竞争的最有潜力的国家，假以时日，中国的区域破坏性军事技术能够抵消美国的传统军事优势。”

2. "The facility is to provide high enthalpy [thermal dynamic] model scramjet testing," he says.

“该实验室将提供高焓值[热动力学]模型超燃冲压发动机测试，”他说。

3. An efficient method for increasing mass flow capture ratio of a three-dimensional sidewall compression scramjet inlet

一种提高后掠侧压式进气道流量系数的有效措施

4. 2-D scramjet inlet

二元进气道

5. The results indicate that, the flow field distortion of 2-D scramjet inlet was much weaker than that of the sidewall compression scramjet inlet.

二元进气道流量系数对飞行马赫数的敏感程度远高于侧压式进气道；

6. Preliminary investigation for scramjet engine performed by Beijing Power Machineries Institute is described in this paper.

介绍了北京动力机械研究所进行的超燃冲压发动机初步研究。

7. Form the control view, Sequence Model Approximation (SMA for short) which is a stable optimal control based on none mode and used on scramjet as a control algorithm is also presented.

从控制的角度，给出了基于序列模型逼近法（一种基于未知模型的稳态优化算法）的燃烧模态控制地面试验控制算法。

8. Researchers have done much research for different combustor configurations.The configuration with backwind step is widely adopted in the design of scramjet combustor.

以往国内外的研究工作者对不同结构的燃烧室进行了大量研究,其中突扩型结构是主流的设计思想之一。

9. As part of this effort, an integrated scramjet model is about to begin testing at up to Mach 5.6 in a new wind tunnel in Beijing.

作为该项工作的一部分，一个可达5.6马赫的综合冲压模型即将在北京的一个新的风洞内开始测试。

10. sidewall compression scramjet inlet

侧压式进气道

11. Advanced ramjet technologies are also important for scramjet development, and the Chinese have been active in this area for decades.

先进亚燃冲压技术对于超燃冲压技术至关重要，而中国数十年来在这一领域一直很活跃。

12. Integrated flow field calculation of a modularized scramjet

单模块超燃冲压发动机一体化流场数值计算

13. dual-mode scramjet

双模态冲压发动机

14. Keywords dual-mode scramjet engine;cavity flame holders;mode-transition;subsonic combustion;supersonic combustion;experiment test;numerical analysis;kerosene fuel;

双模态冲压发动机;凹槽火焰稳定器;模态转换;亚声速燃烧;超声速燃烧;实验测试;数值分析;煤油燃料;

15. Keywords dual-mode scramjet;combustor,chemical non-equilibrium flow;massively parallel computation;turbulence model;

双模态冲压发动机;燃烧室;化学非平衡流;大规模并行计算;湍流模型;

16. Experiment study on supersonic inlet in dual-model scramjet

双模态冲压发动机高超进气道的实验研究

17. dual-mode scramjet engine

双模态超燃冲压发动机

18. The core of airbreathing technology is scramjet and airframe/propulsion integrated hypersonic flight vehicle.

吸气式高超声速技术的核心是超燃冲压发动机技术和机体／推进一体化飞行器技术。

19. Keywords air-breathing hypersonic vehicle;aerodynamic force;aerodynamic heat;advanced wall functions;space marching;region marching;PNS equations;automatic design optimization;Scramjet;

吸气式高超声速飞行器;气动力;气动热;壁面函数;空间推进;区域推进;PNS方程;自动优化设计;超燃冲压发动机;

20. Influence of Injection Mode on Flame Stability in Dual-mode Scramjet Combustor

喷注方式对双模态冲压发动机燃烧稳定性的影响

21. The Chinese allowed a peek into multiple aspects of their scramjet efforts at the recent American Institute of Aeronautics and Astronautics Joint Propulsion Conference in Cincinnati.

在最近辛辛那提举行的美国航空航天联合推进技术研究所大会上，中国让外界得以一窥其在冲压发动机方面的多个进展。

22. Then the flow fields of scramjet combustor with fix geometry and isolator are simulated at different inflow Mach number and the influence of direction of injection fuel to flow structure are analyzed.

在此基础上对固定几何、带隔离段的双模态超燃冲压发动机在不同飞行马赫数下的流场进行了模拟，最后分析了不同的燃料喷射方向对燃烧室和隔离段流场的影响。

23. The uniform design and response surface methodology(RSM) are applied to the multi-objective optimization of a 2-D mixed compression scramjet inlet.

基于响应面法进行了二维混合压缩超燃冲压发动机进气道的多目标优化研究。

24. and the thrust force increment and CII are controlled efficiently.This work lays a foundation for further study of scramjet combustor control.

对目标推力增益和燃烧室一隔离段交互的控制有效，并为进一步深入研究超燃冲压发动机燃烧室控制问题奠定了基础。

25. Experimental and numerical investigation of a forward sweep sidewall compression scramjet inlet with forebody compression

带前体压缩的前掠侧压式进气道实验及数值研究

26. DONBAR J,POWELL O,GRUBER M,JACKSON T.Post-test analysis of flush-wall fuel injection experiments in a scramjet combustor[R].AIAA 2001-3197.

张鹏,俞刚.超燃燃烧室一维流场分析模型研究[J].流体力学实验与测量,2003,17(1):88-92.

27. The main performance parameters of a fixed geometry scramjet are observed,and the effective thrust coefficient,effective specific impulse and effective specific thrust are determined.

探讨了固定几何尺寸（不可调）的超燃冲压发动机有效推力系数、有效比冲和有效单位推力等主要性能参数变化的定量范围。

28. A simple performance analysis model for dual-fuel scramjet is proposed to evaluate the fuel selection effect on vehicle performance,as range selected as mission performance measure.

提出了双燃料超燃冲压发动机方案,以航程为高超声速巡航飞行器性能目标,建立了双燃料超燃冲压发动机的性能分析模型,得到了超燃冲压发动机燃料类型的选择准则。

29. Abstract A numerical study of the cold flowfield of a hydrocarbon fueled model scramjet combustor have been completed with the NUMECA, which is a famous computational fluid dynamic software .

摘 要 超声速燃烧一直以来被视为人类采用吸气式推进器实现高超声速飞行的最关键的技术难题之一。

30. Configurations of sidewall and location of cowl have significant influence on the performance of sidewall-compression scramjet inlets.

摘要侧板构型和唇口位置是影响侧压式进气道性能的关键参数。

31. Catalytic reforming gas generator is the effective method of producing on-line hydrogen, which is good for the ignition and combustion of hydrocarbon fuel in the scramjet.

摘要催化重整燃气发生器是在线产生氢气的有效途径，有助于碳氢燃料超燃冲压发动机的着火和燃烧。

32. The thermal environment of the scramjet strut leading edge is rigorous.

摘要在超燃冲压发动机工作过程中，支板前缘的热环境非常恶劣。

33. Based on the thermal environment of the inlet surface of the scramjet, the structure thermal protection was proposed to provide efficient protection for the inlet surface.

摘要基于超燃冲压发动机进气道表面的热环境，考虑采用结构防热来实现进气道表面的有效热防护。

34. Hypersonic propulsion test facility is important for the scramjet ground tests.

摘要高超声速推进风洞是进行超燃冲压发动机模型地面模拟的重要试验设备。

35. In this thesis, the scramjet nozzle has been designed and optimized by the method of characteristic line.

本文应用简易特征线方法对超燃冲压发动机尾喷管进行了优化设计。

36. Abstract: Firstly, the understanding of realization of combustion mode control is introduced and the idea of controlling combustion mode of scramjet by distributing oil is put forwards.

本文首先介绍了对燃烧模态控制实现的认识，提出了超燃冲压发动机燃烧模态控制的配油思路。

37. The necessity about using supersonic combustion ramjet(scramjet)for the single stage to orb(?)t aerospace plane is demonstrated.

本文首先说明了单级入轨的空天飞机采用超声速燃烧冲压发动机的必要性。

38. Chinese engineers from several research facilities presented about a dozen papers on their scramjet developments, as well as details on the new wind tunnel.

来自几家研究机构的中国工程师发表了十多篇关于冲压技术的发展和新风洞细节的论文。

39. Hydrogen injection and scramjet ignition testing.

氢注入及冲压点火测试。

40. The Effect of Mass Vapor in Gas on Performance of Scramjet

水组分对高超声速冲压发动机性能的影响

41. scramjet eombustor

火焰稳定器

42. Numerical Simulation for the Fuel Jet and Inner Flowfield of Scramjet Combustion Chamber

燃冲压发动机燃烧室燃料喷注及其内流场的数值模拟

43. Effects of Fuel Injection Scheme on the Mixing and Combustion Efficiency of a Scramjet Combustor

燃料引射方式对超燃冲压燃烧室混合及燃烧效率的影响

44. The airframe and engine highly integration nature of hypersonic vehicle results in the asymmetry and cowl adjustable characters of the scramjet nozzle.

由于高超声速飞行器机体与发动机高度一体化的构型,使超燃冲压发动机尾喷管具有非对称,面罩可调等特点。

45. Numerical study of the cold flowfield of a hydrocarbon fueled model scramjet combustor with a streamwise vortices mixer

碳氢燃料流向涡掺混超燃模型燃烧室冷态流场数值研究

46. Experimental investigation of ignition technology in liquid hydrocarbon fueled scramjet combustor

碳氢燃料超燃冲压发动机点火技术试验

47. Impulse combustion wind tunnel and its application in rocket and scramjet research

脉冲燃烧风洞及其在火箭和超燃发动机研究中的应用

48. Analysis of Comparative Numerical Simulation of Free-jet Scramjet Combustor

自由射流超燃冲压发动机燃烧室流场对比计算研究

49. Scramjet ignition technology and work on cooling the internal walls of a scramjet are also being assessed, the Chinese say.

该中国人透露，超燃冲压发动机点火技术和冷却超燃冲压发动机内壁的工作也在评估之中。

50. Scramjet ignition technology and work on cooling the internal walls of a scramjet are also being assessed, the Chinese say. Computer modeling of scramjet combustion instability is also being modeled.

该中国人透露，超燃冲压发动机点火技术和冷却超燃冲压发动机内壁的工作也在评估之中。超燃冲压发动机燃烧不稳定性的计算机模型也正在构建之中。

51. Keywords supersonic combustion;scramjet;cavity;flame holder;lean blowout limit;drag;

超声速燃烧;超燃冲压发动机;凹腔;火焰稳定器;贫油极限;阻力;

52. scramjet engine

超燃冲压发动机

53. Keywords Scramjet;Two-equations turbulence model;Chemical equilibrium;Finite rate reacting;Turbulent combustion;Flamelet model;

超燃冲压发动机;两方程湍流模型;化学平衡;有限速率反应;湍流燃烧;火焰面模型;

54. Keywords Scramjet;Asymmetric supersonic flow;Isolator design;Shock train;Curve spacer;

超燃冲压发动机;超声速非对称流;隔离段设计;激波串;弯曲隔板;

55. Keywords Scramjet;unstructured grids;massively parallel simulations;hydrogen and hydrocarbon fuels;turbulence models;

超燃冲压发动机;非结构网格;大规模并行计算;氢燃料;碳氢燃料;湍流模型;

56. The scramjet has some advantages of high flow velocity, high specific impulse and wide operating range which become a viewpoint in the research field of power of Aeronautics and Astronautics.

超燃冲压发动机以其高速、高比冲和工作范围宽广的特点,正逐渐成为当今航空航天动力领域的研究焦点。

57. Numericla Simulation to Scramjet Nozzle's Performance under Different External Flow Condition and Nozzle Pressure Ratio

超燃冲压发动机尾喷管数值分析

58. Research on Design of Nozzle in Scramjet

超燃冲压发动机尾喷管设计方法研究

59. This paper summarized the latest domestic and foreign development status of scramjet engine and focused on the key technologies.

超燃冲压发动机技术是一项新型的、具有广阔发展前景的推进技术。

60. In recent years the supersonic combustion ramjet (scramjet) has been undergone extensive researches.There is established a Hypersonic Propulsion Testing Facility and conducted a lot of experiments.

超燃冲压发动机是近年来航空航天方面的研究热点，国内建立的超燃实验台进行了大量的模拟实验。

61. Flow Field Calculation for Designing a Kerosene Heater Used for Scramjet

超燃冲压发动机煤油燃烧加热器设计中的流场计算

62. Keywords Scramjet combustor;Performance analysis;Design parameter analysis;Ignition performance;Combustion performance;Theoretical analysis;Experimental investigation;Numerical simulation;

超燃冲压发动机燃烧室;性能分析;设计参数分析;点火特性;燃烧性能;理论分析;试验研究;数值模拟;

63. The Design of Combustion Efficiency Sampling-Probe in. Scramjet Engine

超燃冲压发动机燃烧效率取样探针设计

64. A preliminary study of the arc flow field for scramjet research

超燃冲压发动机电弧加热器试验流场调试

65. Influence Factor Analysis of the MHD Controlled Scramjet Inlet Design

超燃冲压发动机磁控进气道设计影响因素分析

66. Numerical Simulation of the Flowfield in a Scaled down Scramjet Combustor

超燃冲压发动机缩比燃烧室流场数值模拟

67. The most difficult problem in the design of scramjet is that, how to design an optimization configuration of supersonic combustor.

超燃冲压发动机设计技术中的难点之一是超音速燃烧室结构设计。

68. scramjet inlet

超燃冲压发动机进气道

69. Numerical simulation of single expansion ramp nozzle for scramjet on the off-design point

超燃冲压发动机非对称喷管非设计状态性能计算

70. scramjet combustor

超音速燃烧室

71. Experimental Investigation of Hydrocarbon-fuel Ignition in Scramjet Combustor

超音速燃烧室碳氢燃料点火实验研究

72. In the recent ten years, scramjet design, computational and experimental studies has been developed rapidly in the world.

近十年来国内外在超燃冲压发动机设计、数值模拟及试验研究方面发展迅速。

73. Numerical Simulation Study of Inlet Cowl Effect on Scramjet Isolator

进气道外罩长度对隔离段性能的影响数值模拟

74. Through the analysis of the configuration of Scramjet nozzle flow field, some design methods of scramjet nozzle and the characteristics of its performance variation were found.

通过对流场结构和喷管性能的分析,得出了一些超燃冲压发动机喷管设计方法和喷管性能变化的规律。

75. First,hydrogen-air scramjet combustor is numerically simulated and analyzed by solving the general one-dimensional unsteady Euler equation. Second,compressible,reacting,turbulent flow solutions are obtained.

通过求解广义一维非定常Euler方程，数值模拟了氢燃料的燃烧室，并和实验结果进行了比较和分析。

76. The scramjet supersonic combustor and its test facility have been designed by enthalpy method and characteristic line method.

采用热焓法、特征线法等进行了超音燃烧室试验器的计 算和设计工作。

77. An isolator includes two important functions: one is to provide a wide work scope to inlet;another is to make scramjet engine work within the dual-mode.

隔离段作为双模态超燃冲压发动机的重要部件,除了可以隔离进气道和燃烧室的相互干扰外,还在超燃冲压发动机模态转换中扮演着重要的角色。

78. Issues associated with long duration high enthalpy scramjet combustor testing

高焓超音速燃烧冲压喷气发动机燃烧室长期试验的结果

79. Test of a generic sidewall compression scramjet inlet in the high-enthalpy impulse wind tunnel

高超侧压式进气道高焓脉冲风洞实验

80. Spillage characteristics of sidewall compression scramjet inlets

高超声速侧压式进气道溢流特性研究