基于马赫数分布可控曲面外/内锥形基准流场的前体/进气道一体化设计

doi:10.7527/S1000-6893.2014.0263

Abstract

Abstract:

Design method of external conical basic flow field for hypersonic waverider forebody with controllable Mach number distribution surface is proposed to improve their flexibility in this paper. The basic flow field is designed reversely from assigned conical surface Mach number distribution utilizing the rotational method of characteristics. The characteristic of this basic flow field is that the incoming flow can be efficiently compressed by concave cone shock and isentropic compression waves within short length. With the basic flow field of antitangent Mach number distribution, the waverider forebody is designed with high volume ratio, good waverider characteristics and exit uniformity. On-design lift-drag ratio is 1.89 under viscous condition. Then, based on this waverider forebody and inward turning inlet with controllable Mach number distribution, a dual waverider configuration integrated with forebody and inlet is proposed which achieves the internal and external flows waverider respectively, maximizing their own advantages.

Key words: hypersonic inlets, waverider forebody, basic flow field, Mach number distribution, dual waverider, integrated design

CLC Number:

V231.3

LI Yongzhou, ZHANG Kunyuan. Integrated design of forebody and inlet based on external and internal conical basic flow field with controlled Mach number distribution surface[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 289-301.

References

[1] Lewis M J, Takashima N. Engine/airframe integration for waverider cruise vehicles, AIAA-1993-0507[R]. Reston:AIAA, 1993.

[2] Goonko Y P, Mazhul I I. Some factors of hypersonic inlet/airplane interactions[J]. Journal of Aircraft, 2002, 39(1): 37-50.

[3] Berens T M, Bissinger N C. Forebody precompression effects and inlet entry conditions for hypersonic vehicles[J]. Journal of Spacecraft and Rockets, 1998, 35(1): 30-36.

[4] Anderson J D, Lewis M J. Hypersonic waveriders-where do we stand?, AIAA-1993-0399[R]. Reston: AIAA, 1993.

[5] You Y C, Liang D W. Design concept of three dimensional section controllable internal waverider hypersonic inlet[J]. SCIENTIA SINICA Technologica, 2009, 39(8): 1483-1494 (in Chinese). 尤延铖, 梁德旺. 基于内乘波概念的三维变截面高超声速进气道[J]. 中国科学:技术科学, 2009, 39(8): 1483-1494.

[6] Sobieczky H, Zores B, Wang Z. High speed flow design using the theory of osculating cones and axisymmetric flows[J]. Chinese Journal of Aeronautics, 1999, 12(1): 1-8.

[7] Rasmussen M L, Jischke M C, Daniel D C. Experimental forces and moments on cone-derived waveriders for Ma=3 to 5[J]. Journal of Spacecraft and Rockets, 1982, 19(6): 592-598.

[8] Nonweiler T R F. Delta wings of shapes amenable to exact shock-wave theory[J]. Journal of the Royal Aeronautical Society, 1963, 67(1): 39-40.

[9] Rasmussen M P. Waverider configurations derived from inclined circular and elliptic cones[J]. Journal of Spacecraft and Rockets, 1980, 17(5): 537-545.

[10] Takashima N, Lewis M J. Waverider configurations based on non-axisymmetric flow fields for engine-airframe integration, AIAA-1994-0380[R]. Reston: AIAA, 1994.

[11] Goonko Y P, Mazhul I I, Markelov G N. Convergent flow derived waveriders[J]. Journal of Aircraft, 2000, 37(4): 647-654.

[12] He X Z, Ni H L. Osculating inward turning cone (OIC) wave rider-design methods and performance analysis[J]. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(5): 803-808 (in Chinese). 贺旭照, 倪鸿礼. 密切内锥乘波体设计方法和性能分析[J]. 力学学报, 2011, 43(5): 803-808.

[13] He X Z, Ni H L. Osculating curved cone (OCC) waverider: design methods and performance analysis[J]. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(6): 1077-1082 (in Chinese). 贺旭照, 倪鸿礼. 密切曲面锥乘波体——设计方法与性能分析[J]. 力学学报, 2011, 43(6): 1077-1082.

[14] Qian Y J. Computer program of supersonic axisymmetric rotational characteristic method[J]. Journal of Beijing University of Aeronautics and Astronautics, 1996, 22(4): 454-459 (in Chinese). 钱翼稷. 超音速轴对称有旋流特征线法的计算程序[J]. 北京航空航天大学报, 1996, 22(4): 454-459.

[15] Wang Z, Qian Y J. Waverider configuration design[J]. Journal of Beijing University of Aeronautics and Astronautics, 1999, 25(2): 180-183 (in Chinese). 王卓, 钱翼稷. 乘波机外形设计[J]. 北京航空航天大学学报, 1999, 25(2): 180-183.

[16] Qiao W Y, Huang G P, Xia C, et al. Development of inverse characteristic method for matching design of high-speed aircraft forebody/inlet[J]. Journal of Aerospace Power, 2014, 29(6): 1444-1452 (in Chinese). 乔文友, 黄国平, 夏晨, 等. 发展用于高速飞行器前体/进气道匹配设计的逆特征线法[J]. 航空动力学报, 2014, 29(6): 1444-1452.

[17] Lawing P L, Johnson C B. Inlet boundary-layer shapes on four aircraft forebodies at Mach 6[J]. Journal of Aircraft, 1978, 15(1): 62-63.

[18] Li Y Z, Zhang K Y, Nan X J. Design concept of controllable Mach number distribution hypersonic inward turning inlets[J]. Journal of Aerospace Power, 2012, 27(11): 2484-2491 (in Chinese). 李永洲, 张堃元, 南向军. 基于马赫数分布规律可控概念的高超声速内收缩进气道设计[J]. 航空动力学报, 2012, 27(11): 2484-2491.

[19] Li Y Z, Zhang K Y, Wang L, et al. Sensitivity analysis and optimization design of the basic flowfield with controllable Mach number distribution[J]. Journal of Aerospace Power, 2013, 28(4): 765-774 (in Chinese). 李永洲, 张堃元, 王磊, 等. 马赫数分布可控的基准流场灵敏度分析与优化设计[J]. 航空动力学报, 2013, 28(4): 765-774.

[20] Lewis M J. A hypersonic propulsion airframe integration overview, AIAA-2003-4405[R]. Reston: AIAA, 2003.

[21] You Y C. An overview of the advantages and concerns of hypersonic inward turning inlets, AIAA-2011-2269[R]. Reston: AIAA, 2011.

[22] You Y C, Liang D W, Guo R W. Overview of the integration of three-dimensional inward turning hypersonic inlet and waverider forebody[J]. Advances in Mechanics, 2009, 39(5): 513-525 (in Chinese). 尤延铖, 梁德旺, 郭荣伟. 高超声速三维内收缩式进气道/乘波前体一体化设计研究评述[J]. 力学进展, 2009, 39(5): 513-525.

[23] He X Z, Qin S, Zhou Z, et al. Integrated design and performance analysis of waverider forebody and inlet[J]. Journal of Aerospace Power, 2013, 28(6): 1270-1276 (in Chinese). 贺旭照, 秦思, 周正, 等. 一种乘波前体进气道的一体化设计及性能分析[J]. 航空动力学报, 2013, 28(6): 1270-1276.

[24] You Y C, Zhu C X, Guo J L. Dual waverider concept for the integration of hypersonic inward-turning inlet and airframe forebody, AIAA-2009-7421[R]. Reston: AIAA, 2009.

[25] Nan X J, Zhang K Y. Numerical and experimental investigation on hypersonic inward turning inlets with basic flow field using arc tangent curve law of pressure rise, AIAA-2011-2270[R]. Reston: AIAA, 2011.

Integrated design of forebody and inlet based on external and internal conical basic flow field with controlled Mach number distribution surface

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Lili CHEN, Jianxia LIU, Juntao ZHANG, Zheng GUO, Anping WU, Zhongxi HOU. Waverider forebody design method with longitudinal segments and multi-stage compression [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(4): 128744-128744.
[2]	Weihong ZHANG, Han ZHOU, Shaoying LI, Jihong ZHU, Lu ZHOU. Material⁃structure integrated design for high⁃performance aerospace thin⁃walled component [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(9): 627428-627428.
[3]	Shuai HAO, Tielin MA, Yi WANG, Jinwu XIANG, Hongzhong MA, Baifeng JIANG, Jun CAO. Progress and application of key technologies of SensorCraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 27034-027034.
[4]	Yuanyuan TU, Dayi WANG, Xiangyan ZHANG, Jiaxing LI, Xiaofeng HUANG. Reconfigurability and autonomous reconfiguration methods of spacecraft [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 628855-628855.
[5]	Yulin DING, Zhonghua HAN, Jianling QIAO, Han NIE, Wenping SONG, Bifeng SONG. Research progress in key technologies for conceptual-aerodynamic configuration design of supersonic transport aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(2): 626310-626310.
[6]	Yongzhou LI, Di SUN, Renhua WANG, Kunyuan ZHANG. Design of inward turning inlet with controlled Mach number under non-uniform inflow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127857-127857.
[7]	WANG Zhixiang, LEI Yongjun, DUAN Jingbo, OUYANG Xing, ZHANG Dapeng, WANG Jie. Multi-region integrated design and optimization of concentrated-force diffusion component in heavy-lift launch vehicle [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 225135-225135.
[8]	ZHANG Wenhao, LIU Jun, DING Feng. Integrated design method of inward turning inlet/Von Karman waverider [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(3): 123502-123502.
[9]	ZHOU Hang, JIN Zhiguang. Micro osculating axisymmetric flow method for 3D shock wave design under nonuniform flows [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(12): 124035-124035.
[10]	JIANG Yongsong, ZHENG Wentao, ZHAO Hang, YANG Mingsui, WANG Yongmei. Low noise design of fan outlet guide vane, part Ⅰ: Method and optimization [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 122955-122955.
[11]	ZHENG Wentao, JIANG Yongsong, ZHAO Hang, PAN Ruochi, ZHAO Yong. Low noise design of fan outlet guide vane, part Ⅱ: Numerical verifications [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 122956-122956.
[12]	SHEN Zhengyang, CHEN Xiaoming, HUANG Lingcai. Challenges for aircraft design due to special mission models of large-scale amphibious aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(1): 522400-522400.
[13]	QIAO Wenyou, YU Anyuan, YANG Dawei, LE Jialing. Integration design of inward-turning inlets based on forebody shock wave [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(10): 122078-122078.
[14]	LI Yongzhou, ZHANG Kunyuan, SUN Di. Off-design performance characteristics of inward turning inlet with rectangular-to-circular shape transition with controlled Mach number distribution [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(11): 3263-3272.
[15]	LI Yongzhou, ZHANG Kunyuan, SUN Di. Experimental investigation on a hypersonic inward turning inlet of rectangular-to-circular shape with controlled Mach number distribution [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(10): 2970-2979.