风洞投放试验技术的研究现状与应用综述

doi:10.7527/S1000-6893.2020.24417

综述

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

风洞投放试验技术的研究现状与应用综述

宋威, 张宁, 朱剑, 董垒, 蒋增辉

中国航天空气动力技术研究院, 北京 100074

收稿日期:2020-06-15 修回日期:2020-06-22 出版日期:2021-06-15 发布日期:1900-01-01
通讯作者: 宋威 E-mail:qxj19860128@126.com

Research status and application of wind tunnel drop test technology: Review

SONG Wei, ZHANG Ning, ZHU Jian, DONG Lei, JIANG Zenghui

China Academy of Aerospace Aerodynamics, Beijing 100074, China

Received:2020-06-15 Revised:2020-06-22 Online:2021-06-15 Published:1900-01-01

摘要/Abstract

摘要： 多体分离是航空、航天和武器系统总体部门一直极为关注的关键问题，多体间的流场干扰效应产生的气动力和力矩对悬挂物分离相容性有重要影响，基于运动动力学相似的风洞投放试验技术是预测和评估多体分离是否相容的一种非定常试验方法。根据飞行器多体分离相容性的研究需求，结合作者在风洞投放试验技术的研究成果和经验，对风洞投放试验技术的国内外研究现状进行综述。首先回顾了风洞投放试验技术的发展历史，然后对低速和高速风洞投放试验的相似准则及缩比关系进行详细地论述与分析，进而对风洞投放试验的几个关键技术进行综述，最后对风洞投放试验技术存在的问题提出思考与展望。

关键词: 多体分离, 相容性, 风洞投放试验, 相似准则, 非定常试验

Abstract: The compatibility of multi-body separation is a key issue that has always been paid close attention to by the general departments of aviation, aerospace and weapon systems. The aerodynamic force and moment generated by flowfield interference of multi-bodies have an important impact on the compatibility of store separation. The wind tunnel drop test technology based on dynamic similarity is an unsteady test method for the prediction and evaluation of multi-body separation compatibility. Based on the research findings and the author's experience in the study of the wind tunnel drop test technology, this paper summarizes the research status of this technology at home and abroad. The development history of the technology is reviewed, followed by discussions and analyses of the similarity-criteria and scaling-relationship of the wind tunnel drop test. Several key technologies of the wind tunnel test are then summarized, and some thoughts and prospects on the technology are finally presented.

Key words: multi-body separation, compatibility, wind tunnel drop test, similarity criteria, unsteady tests

中图分类号:

宋威, 张宁, 朱剑, 董垒, 蒋增辉. 风洞投放试验技术的研究现状与应用综述[J]. 航空学报, 2021, 42(6): 24417-024417.

SONG Wei, ZHANG Ning, ZHU Jian, DONG Lei, JIANG Zenghui. Research status and application of wind tunnel drop test technology: Review[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 24417-024417.

参考文献

[1] WANG G, CHEN X, XING Y, et al. Multi-body separation simulation with an improved general mesh deformation method[J]. Aerospace Science and Technology, 2017, 71:763-771.
[2] TOMARO R F, WITZEMAN F C, STRANG W Z. Simulation of store separation for the F/A-18C using Cobalt60[J]. Journal of Aircraft, 2000, 37(3):361-367.
[3] 常兴华,马戎,张来平. 并行化非结构重叠网格隐式装配技术[J]. 航空学报, 2018, 39(6):121780. CHANG X H, MA R, ZHANG L P. Parallel implicit hole-cutting method for unstructured overset grid[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(6):121780(in Chinese).
[4] 刘瑜. 内埋式弹舱武器发射分离过程研究[D]. 南京:南京航空航天大学, 2010. LIU Y. Fluid dynamics analysis on missile launching and separating from weapon bay[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2010(in Chinese).
[5] 冯必鸣, 聂万胜, 车学科, 等. 安装角度对内埋式导弹分离特性的影响[J]. 空气动力学学报, 2010, 28(6):672-675. FENG B M, NIE W S, CHE X K, et al. Effect of fixing angle to separation characteristics of internal store[J]. Acta Aerodynamica Sinica, 2010, 28(6):672-675(in Chinese).
[6] HAYWARD D M, DUFF A K. F-35 weapons design integration[C]//AIAA Aviation Forum. Reston:AIAA, 2018.
[7] DISSEL A F, KOTHARI A P, LEWIS M J. Investigation of two-stage-to-orbit air-breathing launch vehicle configurations:AIAA-2005-3244[R]. Reston:AIAA, 2005.
[8] 王金龙, 王浩, 陶如意, 等. 子母弹不同舱段分离流场特性及运动特性研究[J]. 空气动力学学报, 2016, 34(4):490-496. WANG J L, WANG H, TAO R Y, et al. The movement characteristics analysis of interference flow field on the separation of multi-bay cluster munition[J]. Acta Aerodynamica Sinica, 2016, 34(4):490-496(in Chinese).
[9] DAGAN Y, ARAD E. Analysis of shroud release applied for high-velocity missiles[J]. Journal of Spacecraft and Rockets, 2014, 51(1):57-66.
[10] MURPHY K J, BUNING P G, PAMADI B N, et al. Overview of transonic to hypersonic stage separation tool development for multi-stage-to-orbit concepts:AIAA-2004-2595[R]. Reston:AIAA, 2004.
[11] 宋威, 艾邦成, 蒋增辉, 等. 内埋武器投放分离相容性的风洞投放试验预测与评估[J]. 航空学报, 2020, 41(6):523415. SONG W, AI B C, JIANG Z H, et al. The prediction and assessment of drop separation compatibility of internal weapons by wind tunnel drop-test[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6):523415(in Chinese).
[12] 常超, 丁海河. 内埋弹射武器机弹安全分离技术综述[J]. 现代防御技术, 2012, 40(5):67-74. CHANG C, DING H H. Review on missile store safety separation technology of embedded ejection weapons[J]. Modern Defense Technology, 2012, 40(5):67-74(in Chinese).
[13] MOORE S B. Wind-tunnel systems and techniques for aircraft stores compatibility studies[J]. Journal of Aircraft, 1971, 8(2):1000-1008.
[14] 闫盼盼. 内埋武器舱气动特性及武器分离安全性研究[D]. 北京:北京交通大学, 2018. YAN P P. Study on aerodynamic characteristic and store safety separation for internal weapon bay[D]. Beijing:Beijing Jiaotong University, 2018(in Chinese).
[15] 李周复. 风洞特种试验技术[M]. 北京:航空工业出版社, 2010:104-113. LI Z F. Wind tunnel special tests technique[M]. Beijing:Aviation Industry Press, 2010:104-113(in Chinese).
[16] 艾邦成, 宋威, 董垒, 等. 内埋武器机弹分离相容性的研究进展综述[J]. 航空学报, 2020,41(10):023809. AI B C, SONG W, DONG L, et al. Review on aircraft-store separation compatibility for the internal weapons[J]. Acta Aeronautica et Astronautica Sinica, 2020,41(10):023809(in Chinese).
[17] 吴继飞, 王元靖, 罗新福, 等. 高超声速风洞多体干扰与分离试验技术[J]. 实验流体力学, 2010, 24(3):99-102. WU J F, WANG Y J, LUO X F, et al. A test for multi-body interference and separation in hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(3):99-102(in Chinese).
[18] CHING T K. Grid survey approach to store separation trajectory prediction[J]. Journal of Aircraft, 2000, 37(4):736-738.
[19] GARCON F,TARAVEL P H,RAFFIN J C. Recent developments in captive trajectory systems of the ONERA Modane wind-tunnel:AIAA-2001-0579[R]. Reston:AIAA,2001.
[20] 谢峰,洪冠新,张晨凯,等. 捕获轨迹系统并联并联机构地面标定方法[J]. 航空学报, 2020, 41(1):423175. XIE F, HONG G X, ZHANG C K, et al. Ground calibration method of captive trajectory system parallel mechanism[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(1):423175(in Chinese).
[21] 宋威, 鲁伟, 蒋增辉, 等. 内埋武器高速风洞弹射投放模型试验关键技术研究[J]. 力学学报, 2018, 50(6):1346-1355. SONG W, LU W, JIANG Z H, et al. The crucial technique investigation of wind-tunnel drop-model testing for the supersonic internal weapons[J]. Chinese Journal of Theoretical and Applied Mechanics, 2018, 50(6):1346-1355(in Chinese).
[22] DAVIDS S, CENKO A. Grid based approach to store separation:AIAA-2001-2418[R]. Reston:AIAA,2001.
[23] 金鑫, 袁兵, 张利珍, 等. 一种折叠弹翼悬挂物的分离轨迹实验技术[J]. 实验流体力学, 2014, 28(1):80-84. JIN X, YUAN B, ZHANG L Z, et al. A technique of separation trajectory test for stores with folding wing[J]. Journal of experiments in Fluid Mechanics, 2014, 28(1):80-84(in Chinese).
[24] KEEN K S,MORGRET C H,LANGHAM T F. Trajectory simulations should match flight tests and other lessons learned in 30 years of store-separation analysis:AIAA-2009-99[R]. Reston:AIAA, 2009.
[25] THOMAS J F, REEDER M F. Dynamic store release of ice models from a cavity into Mach 2.9 flow[J]. Journal of Aircraft, 2014, 51(6):1927-1941.
[26] BAMBER M L. Two methods of obtaining aircraft store trajectories from wind tunnel investigation:Aero Report 970(AD233198)[R]. 1960.
[27] 张召明. 飞机外挂物投放低速风洞试验技术研究[J]. 南京航空航天大学学报, 2003, 35(3):318-321. ZHANG Z M. Experiment research of jettison of aircraft external store in low speed wind tunnel[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2003, 35(3):318-321(in Chinese).
[28] 蔡国华. 载机投放外挂物低速风洞模拟技术[J]. 空气动力学学报, 1999, 17(4):477-483. CAI G H. Research of experimental techniques about dropping test of external stores in the low speed wind tunnel[J]. Acta Aerodynamica Sinica, 1999, 17(4):477-483(in Chinese).
[29] 张竹坡. 高速风洞自由投放实验[R]. 绵阳:中国空气动力研究与发展中心, 1983. ZHANG Z P. Free-drop model testing in high speed wind tunnel[R]. Mianyang:China Aerodynamics Research and Development Centre, 1983(in Chinese).
[30] 程仁全, 于夕民. NH-1风洞外挂物高速投放实验技术:HJB-85-2359.[R]. 南京:南京航空航天大学, 1984. CHENG R Q, YU X M. Experimental technique of high speed store-dropping in the NH-1 wind tunnel:NHJB-85-2359[R]. Nanjing:Nanjing University of Aeronautics & Astronautics,1984(in Chinese).
[31] 蒋增辉, 宋威, 陈农, 等. 高超声速风洞子母弹大迎角抛壳投放试验[J]. 实验流体力学, 2016, 30(5):42-48. JIANG Z H, SONG W, CHEN N, et al. Hypersonic wind tunnel drop-model test on cover ejection from cargo projectile at large angle of attack[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(5):42-48(in Chinese).
[32] 程仁全, 周东轩. 外挂物风洞投放实验技术研究[J]. 气动实验与测量控制, 1989, 3(1):31-37. CHENG R Q, ZHOU D X. Studies of experimental techniques of store-dropping in the wind tunnel[J]. Aerodynamic Experiment and Measurement & Control, 1989, 3(1):31-37(in Chinese).
[33] MERRICK J D. Influence of Mach number and dynamic pressure on cavity tones and free-drop trajectories:AFIT-ENY-14-M-36, ADA599108[R]. Air Force Institute of Technology, 2014.
[34] 金时彧. 内埋式弹舱流场及武器投放轨迹研究[D]. 南京:南京航空航天大学,2014. JIN S Y. Research on the flow field of weapon bay and the trajectory of missile separating[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2014(in Chinese).
[35] 宋威, 鲁伟, 蒋增辉. 超声速飞行器头罩分离风洞投放模拟试验[J]. 实验流体力学, 2017, 31(6):45-51. SONG W, LU W, JIANG Z H. Wind tunnel drop model test of nose cap separation of supersonic vehicle[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(6):45-51(in Chinese).
[36] LAWSON S J, BARAKOS G N. Review of numerical simulations for high-speed, turbulent cavity flows[J]. Progress in Aerospace Sciences, 2011, 47(3):186-216.
[37] RAINEY R W. A wind-tunnel investigation of bomb release at a Mach number of 1.62:NACA RM-L53L29[R]. Washington,D.C.:NACA, 1954.
[38] 范洁川. 风洞试验手册[M]. 北京:航空工业出版社, 2002:393-400. FAN J C. Handbook of wind tunnel test[M]. Beijing:Aviation Industry Press, 2002:393-400(in Chinese).
[39] 夏玉顺. 风洞特种实验[M]. 西安:西北工业大学出版社, 1990. XIA Y S. Wind tunnel special testing[M]. Xian:Northwestern Polytechnical University Press, 1990(in Chinese).
[40] MARSHALL J C. Analytic evaluation of the limitations of the various scaling laws for free-drop store separation testing[C]//The Fourth JTCG Aircraft/Stores Compatibility Symposium, 1977:197-234.
[41] DESLANDES R M,DONAUER S. Scaled-drop-tests WYSIWYG or Not:AIAA-2010-681[R]. Reston:AIAA, 2010.
[42] CARTER H S, LEE J B. Investigation of the ejection release of several dynamically scaled bluff internal stores at Mach numbers of 0.8, 1.39, and 1.98:NACA RM-L56H28[R]. Washington,D.C.:NACA, 1956.
[43] LEE J B, CARTER H S. An investigation of ejection releases of submerged and semisubmerged dynamically scaled stores from a simulated bomb bay of a fighter-bomber airplane at supersonic speeds:NACA RM L56I10[R]. Washington,D.C.:NACA, 1956.
[44] FAGET M A, CARLSON H W. Experimental techniques for predicting store motions:NACA RM L55L20b[R]. Washington,D.C.:NACA, 1955.
[45] CARLSON H W, GEIER D J, LEE J B. Comparison and evaluation of two model techniques used in predicting bomb-release motions:NACA-RM-L57 J23[R]. Washington,D.C.:NACA, 1957.
[46] SANDAHL C A, FAGET M A. Similitude relations for free-model wind-tunnel studies of store-dropping problems:NACA TN-390793R14088[R]. Washington,D.C.:NACA, 1957.
[47] HILSON W F. Transonic and supersonic ejection release characteristics of six dynamically scaled external-store shapes from an 0.086-scale model of a current fighter airplane:NASA TM X-128[R]. Washington,D.C.:NACA, 1959.
[48] STEPHENS T, ADAMS R. Wind tunnel simulation of store jettison with the aid of magnetic artificial gravity:NASA-CR-1955[R]. Washington,D.C.:NACA, 1955.
[49] COVERT E E. Wind-tunnel simulation of store jettison with the aid of an artificial gravity generated by magnetic fields[J]. Journal of Aircraft, 1967, 4(1):48-51.
[50] SMITH M C. Comment on "Wind-tunnel simulation of store jettison with the aid of an artificial gravity generated by magnetic fields"[J]. Journal of Aircraft, 1968, 4(6):570-572.
[51] BLACK R L. High-speed store separation-correlation between wind-tunnel and flight-test data[J]. Journal of Aircraft, 1969, 6(1):42-45.
[52] REED J F, CURRY W H. A comparison between transonic wind-tunnel and full-scale store separation characteristics[J]. Journal of Aircraft, 1969, 6(3):281-283.
[53] HOLDEN M S, SMOLINSKI G J, MUNDY E, et al. Experimental studies for hypersonic vehicle design and code validation of unsteady flow characteristics associated with free flight shroud and stage separation and mode switching:AIAA-2008-642[R]. Reston:AIAA, 2008.
[54] THOMAS J F. Freedrop testing and CFD simulation of ice models from a cavity into supersonic flow[R]. Wright Patterson Air Force Base:Air Force Institute of Technology, 2012.
[55] 钱锟,孔维梁. F-35武器系统和载荷分离飞行试验的预先研究[J]. 国际航空, 2009(12):64-68. QIAN K, KONG W L. F-35 store separation studies prior to flight test[J]. International Aviation, 2009(12):64-68(in Chinese).
[56] CHRISTOPHER J P, CARLETON W E. Captive trajectory store separation system of the AEDC-PWT 4-foot transonic tunnel:AEDC-TR-68-200(AD839743)[R]. 1968.
[57] 刘俊,蔡晋生,杨党国,等. 超声速空腔流动波系演化及噪声控制研究进展[J]. 航空学报, 2018, 39(11):022366. LIU J, CAI J S, YANG D G, et al. Research progress in wave evolution and noise control for supersonic cavity flows[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(11):022366(in Chinese).
[58] 王勋年, 李军, 刘晓晖. 空气动力对飞机内藏式导弹分离轨迹影响的低速风洞试验研究[J]. 流体力学实验与测量, 1999, 13(2):38-43. WANG X N, LI J, LIU X J. A test research in wind tunnel for aerodynamic loads effect on separation trajectories of the internal missile of fighter[J]. Experiments and Measurements in Fluid Mechanics, 1999, 13(2):38-43(in Chinese).
[59] 董金刚,谢峰,张晨凯,等. 风洞模型投放试验轻模型法重力效应影响[J]. 航空学报, 2020, 41(6):523434. DONG J G, XIE F, ZHANG C K, et al. Gravity effects of light model method in wind tunnel model drop-test[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6):523434(in Chinese).
[60] MICHAEL C P. Experimental measurements of store separation using dry ice models in a subsonic flow[D]. Wright Patterson Air Force Base:Air Force Institute of Technology, 2011.
[61] CARY A C, WESLEY L P. Airframe integration of modern stores (AIMS), delivery order 0031:phase II & III analytical predictions & validation:AFRL-VA-WP-TR-2006-3079[R]. 2006.
[62] BOWER W W, KIBENS V. Separation enhancement and acoustic reduction (SEAR) Phase I:AFRL-VA-WP-TR-2007-3061[R]. 2007.
[63] RUDY A J,MICHAEL J S,JAMES E G. Store separation trajectory deviations due to unsteady weapons bay aerodynamics:AIAA-2008-0188[R]. Reston:AIAA,2008.
[64] KEEN K S, MORGRET C H, ARTERBURY R L. An analytic investigation of accuracy requirements for onboard instrumentation and film data for dynamically scaled wind tunnel drop models:AEDC-TR-96-7[R]. 1997.
[65] CARMAN J B. Store separation testing techniques at the Arnold Engineering Development Center Volume IV:description of dynamic drop store separation testing:AEDC-TR-79-4[R]. 1979.
[66] MERRICK J D, REEDER M F. Sphere release from a rectangular cavity at Mach 2.22 freestream conditions[J]. Journal of Aircraft, 2016, 53(3):822-829.
[67] CHIN D, GRANLUND K. Stochastic store trajectory of ice models from a cavity into supersonic flow[J]. Journal of Aircraft, 2019, 56(4):1313-1319.
[68] MURRAY N E, JANSEN B J, GUI L, et al. Measurements of store separation dynamics:AIAA-2009-105[R]. Reston:AIAA, 2009.
[69] 鲁伟. 超声速内埋导弹风洞投放试验研究[D]. 北京:中国航天空气动力技术研究院, 2018. LU W. Experimental study of the missiles separation from internal weapon bay in supersonic wind tunnel[D]. Beijing:China Academy of Aerospace Aerodynamics, 2018(in Chinese).
[70] BOWER W W, KIBENS V, CARY A W. High-frequency excitation active flow control for high-speed weapon release (HIFEX):AIAA-2004-2513[R]. Reston:AIAA, 2004.
[71] KIBENS V. BOWER W W, SCHWARTZ D R. Active flow control for high-speed weapon release from a bay:RTO-MP-AVT-108-30[R]. 2007.
[72] CENKO A, DESLANDES R, DILLENIUS M, et al. Unsteady weapon bay aerodynamics-urban legend or flight clearance nightmare:AIAA-2008-189[R]. Reston:AIAA, 2008.
[73] WOLOWICZ C H, BOWMAN J S, GILBERT W P. Similitude requirements and scaling relationships as applied to model testing:NACA Technical Paper 1435[R]. Washington,D.C.:NACA, 1979.
[74] 李浩. 风洞虚拟飞行试验相似准则和模拟方法研究[D]. 绵阳:中国空气动力研究与发展中心, 2012. LI H. Study on the similarity criteria and simulation method of the wind tunnel based virtual flight testing[D]. Mianyang:China Aerodynamics Research and Development Center, 2012(in Chinese).
[75] 蒋增辉, 宋威, 鲁伟, 等. 高速风洞投放模型试验技术的关键问题及应用领域[J]. 空气动力学学报, 2016, 34(6):744-750. JIANG Z H, SONG W, LU W, et al. Critical problems and applied fields of drop-model testing technique in high speed wind tunnel[J]. Acta Aerodynamica Sinica, 2016, 34(6):744-750(in Chinese).
[76] 何威. 内置气动式弹射装置设计与虚拟样机仿真研究[D]. 大连:大连理工大学, 2012. HE W. The design and virtual prototype simulation study of internal pneumatic ejection device[D]. Dalian:Dalian University of Technology, 2012(in Chinese).
[77] 尚志亮. 副油箱模型风洞自由投实验技术研究[D]. 大连:大连理工大学, 2015. SHANG Z L. Study on store separation experiment for auxiliary fuel tank model in a wind tunnel[D]. Dalian:Dalian University of Technology, 2015(in Chinese).
[78] 宋晓伟. 双目视觉位姿测量算法研究[D]. 北京:中国地质大学, 2011. SONG X W. Binocular vision position and attitude measurement algorithm[D]. Beijing:China University of Geosciences, 2011(in Chinese).
[79] 马鑫. 高速运动目标多维姿态视觉测量关键技术研究[D]. 大连:大连理工大学, 2017. MA X. Research on key technology of high-speed and multi-dimensional moving target pose measurement[D]. Dalian:Dalian University of Technology, 2017(in Chinese).
[80] 夏军营. 空间目标的单目视觉位姿测量方法研究[D]. 长沙:国防科学技术大学, 2012. XIA J Y. Researches on monocular vision based pose measurement for space targets[D]. Changsha:National University of Defense Technology, 2012(in Chinese).
[81] 黄鹏程, 江剑宇, 杨波. 双目立体视觉的研究现状及发展[J]. 光学仪器, 2018, 40(4):81-86. HUANG P C, JIANG J Y, YANG B. Research status and progress of binocular stereo vision[J]. Optical Instruments, 2018, 40(4):81-86(in Chinese).
[82] 刘双军. 高速投放模型位姿测量技术研究[D]. 大连:大连理工大学, 2012. LIU S J. Research on pose and positon measurement method for high speed motion model[J]. Dalian:Dalian University of Technology, 2012(in Chinese).
[83] MARTINEZ B. Free flight measurement technique in shock tunnel[C]//30th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston:AIAA, 2014.
[84] KENNELL C, NEELY A, TAHTALI M. Free flight testing in hypersonic flows:HEXAFLY-INT EFTV[C]//54th AIAA Aerospace Sciences Meetting. Reston:AIAA, 2016.
[85] 雷凯, 王小军. 背驮式空射火箭分离技术[J]. 导弹与航天运载技术, 2005(4):52-56. LEI K, WANG X J. Separation technology of captive-on-top air-launched vehicle[J]. Missile and Space Vehicle, 2005(4):52-56(in Chinese).
[86] 王元靖, 吴继飞, 陶洋, 等. 高超声速多体干扰与分离试验[J]. 航空动力学报, 2010, 25(4):902-906. WANG Y J, WU J F, TAO Y, et al. Hypersonic experimental investigation on interference and stage separation of a multi-body system[J]. Journal of Aerospace Power, 2010, 25(4):902-906(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

风洞投放试验技术的研究现状与应用综述

Research status and application of wind tunnel drop test technology: Review

RichHTML

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	宋威, 艾邦成. 多体分离动力学研究进展[J]. 航空学报, 2022, 43(9): 25950-025950.
[2]	宋威, 艾邦成, 蒋增辉, 鲁伟. 内埋武器投放分离相容性的风洞投放试验预测与评估[J]. 航空学报, 2020, 41(6): 523415-523415.
[3]	艾邦成, 宋威, 董垒, 蒋增辉. 内埋武器机弹分离相容性研究进展综述[J]. 航空学报, 2020, 41(10): 23809-023809.
[4]	唐静, 张健, 李彬, 崔鹏程, 周乃春. 非结构混合网格自适应并行技术[J]. 航空学报, 2020, 41(1): 123202-123202.
[5]	常兴华, 马戎, 张来平. 并行化非结构重叠网格隐式装配技术[J]. 航空学报, 2018, 39(6): 121780-121780.
[6]	徐颖强, 陈仙亮, 曹栋波. 样本量为2的极小样本相容性检验方法[J]. 航空学报, 2018, 39(5): 221936-221936.
[7]	邢宇, 刘沛清, 郭昊, 徐亮, 李玲. 简化起落架噪声相似准则及马赫数比例律[J]. 航空学报, 2017, 38(6): 120769-120769.
[8]	薛飞, 金鑫, 王誉超, 杨益农. 内埋武器高速投放风洞试验技术[J]. 航空学报, 2017, 38(1): 120114-120114.
[9]	王文虎, 韩冰. 亚轨道飞行器发动机故障下配平能力分析[J]. 航空学报, 2016, 37(12): 3646-3656.
[10]	王志强, 胡骏, 王英锋, 阮立群. 高压压气机低速模拟试验 [J]. 航空学报, 2012, (5): 828-838.
[11]	易贤;朱国林;王开春;桂业伟. 结冰风洞试验水滴直径选取方法[J]. 航空学报, 2010, 31(5): 877-882.
[12]	温显斌;田铮;林伟. 指数信号模型中参数的稳健估计[J]. 航空学报, 2003, 24(5): 439-442.
[13]	李乃宏;吴瑶华;崔平远;杨涤. 导弹飞行数据的相容性检验研究[J]. 航空学报, 1993, 14(1): 80-84.
[14]	张友民;王培德;张洪才. 估计理论在飞行数据相容性检验中的应用[J]. 航空学报, 1992, 13(7): 398-402.
[15]	史忠科. 飞行数据相容性检验的极大似然方法[J]. 航空学报, 1990, 11(8): 354-360.