Volume 35 Issue 6
Dec.  2021
Turn off MathJax
Article Contents
Abstract
References
Related Articles
WANG S，DONG J G，ZHANG C K，et al. The study of ejection mechanism and drop-test in high-speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2021，35（6）：73-78.. DOI: 10.11729/syltlx20200149
Citation: WANG S，DONG J G，ZHANG C K，et al. The study of ejection mechanism and drop-test in high-speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2021，35（6）：73-78.. DOI: 10.11729/syltlx20200149
shu

The study of ejection mechanism and drop-test in high-speed wind tunnel

  • China Academy of Aerospace Aerodynamics, Beijing　100074, China

More Information
  • Received Date: November 30, 2020
  • Revised Date: March 08, 2021
  • Available Online: November 11, 2021
    Graphical Abstract
    • Abstract
  • It is necessary to evaluate the separation safety of supersonic embedded weapons for the new generation fighter. According to the requirements of high-speed wind tunnel launching test of embedded weapons, a new type of double cylinder ejection mechanism is designed, which can realize the continuously adjustment of the initial velocity and the initial angular velocity. Firstly, the NX modeling software is used to design the structural and three-dimensional modeling of the ejection mechanism. Secondly, based on the pressure equations of the cylinder rod free cavity and rod cavity, and the flow equation of the rod free cavity and rod cavity connected with the atmosphere and the piston driving force equation, the mathematical model of the ejection process was established, and the design of the ejection mechanism was simulated and analyzed by using the motion simulation software to verify the rationality of the structure. According to the control requirements of the ejection mechanism, the servo control system of the ejection mechanism was designed by using the electric servo valve and related control elements. Finally, the wind tunnel test of Mach 1.5 was carried out. The experiment shows that the maximum ejection speed of the model can reach 5.68 m/s under the condition that the air pressure is not more than 1.0 MPa, and the initial attitude of the carrier is close to the simulation results, which can meet the design and use requirements.
    • FullText(HTML)
    • References (15)
  • [1]
    吴继飞. 内埋武器舱系统气动特性研究[D]. 绵阳: 中国空气动力研究与发展中心, 2012.

    WU J F. Investigation on aerodynamic characteristics of internal weapons bay system[D]. Mianyang: China Aerodynamics Research and Development Center, 2012.
    [2]
    FLORA T J. Freedrop testing and CFD simulation of ice models from a cavity into supersonic flow[R]. AFIT/GAE/ENY/12-SI5, 2012.
    [3]
    BAKER W B Jr, KEEN S, MORGRET C. Validation of weapon separation predictions using F/A-22 flight test results[R]. AIAA 2004-6803, 2004. doi: 10.2514/6.2004-6803
    [4]
    PURDON M L, HETREED C F, HUDSON M L. F-35 pre-flight store separation analyses: innovative techniques for affordability[R]. AIAA 2009-0102, 2009. doi: 10.2514/6.2009-102
    [5]
    冯金富, 杨松涛, 刘文杰. 战斗机武器内埋关键技术综述[J]. 飞航导弹, 2010(7): 71-74.
    [6]
    BJORGE S T,REEDER M F,SUBRAMANIAN C,et al. Flow around an object projected from a cavity into a supersonic free-stream[J]. AIAA Journal,2005,43(7):1465-1475. doi: 10.2514/6.2004-1253
    [7]
    尉建刚,桑为民,雷熙薇. 内埋式武器舱的流动及气动特性分析[J]. 飞行力学,2011,29(2):29-32.

    YU J G,SANG W M,LEI X W. Analysis of the flow characteristics and aerodynamic problems in internal weapons bay[J]. Flight Dyna-mics,2011,29(2):29-32.
    [8]
    薛飞,金鑫,王誉超,等. 内埋武器高速投放风洞试验技术[J]. 航空学报,2017,38(1):120114.

    XUE F,JIN X,WANG Y C,et al. Wind tunnel test technique on high speed weapon delivery from internal weapons bay[J]. Acta Aeronau-tica et Astronautica Sinica,2017,38(1):120114.
    [9]
    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):744-749, 802. DOI: 10.7638/kqdlxxb-2015.0195

    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):744-749, 802. doi: 10.7638/kqdlxxb-2015.0195
    [10]
    刘兰荣,马胜钢,刘晓龙,等. 贮气瓶供气弹射系统性能的仿真研究[J]. 机床与液压,2013,41(11):170-172. DOI: 10.3969/j.issn.1001-3881.2013.11.048

    LIU L R,MA S G,LIU X L,et al. Simulation research on the performance of ejection system supplied by air bottle[J]. Machine Tool & Hydraulics,2013,41(11):170-172. doi: 10.3969/j.issn.1001-3881.2013.11.048
    [11]
    陈晓光,吕蒙,李超锋,等. 贮气弹射机构发射过程建模及其影响因素分析[J]. 导弹与航天运载技术,2019(3):16-20. DOI: 10.7654/j.issn.1004-7182.20190304

    CHEN X G,LYV M,LI C F,et al. Modeling and influencing factors analysis of launch process of a gas storage ejection device[J]. Missiles and Space Vehicles,2019(3):16-20. doi: 10.7654/j.issn.1004-7182.20190304
    [12]
    杜尧. 开口缸气动弹射装置动力学分析与优化[D]. 南京: 南京理工大学, 2018.
    [13]
    刘救世. 贮气瓶供气无人机弹射器弹射过程的研究[D]. 郑州: 郑州大学, 2013.

    LIU J S. Study on the ejection process of the UAV catapult supplied by gas cylinder[D]. Zhengzhou: Zhengzhou University, 2013.
    [14]
    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 Techno-logy, 2012.
    [15]
    徐张宝. 高压气动弹射过程控制研究[D]. 南京: 南京理工大学, 2018.

    XU Z B. Research on high pressure pneumatic launching process control[D]. Nanjing: Nanjing University of Science and Technology, 2018.
    • Related Articles

  • Related Articles

    [1]LIAN Jianxin, CHEN Weijie, QIAO Weiyang, DU Jun, LIU Yuanshi, LIU Bin. Experimental study on the directivity and noise reduction of the blade leading-edge noise using Inverse Method SODIX based on microphone array[J]. Journal of Experiments in Fluid Mechanics, 2024, 38(1): 67-78. DOI: 10.11729/syltlx20230020
    [2]SHI Dewei, CHEN Letian, FAN Ziye, JIANG Nan, ZUO Zhigang, TANG Zhanqi. Experimental study on stall characteristics of wing sections with leading-edge protuberances inspired by humpback whale flipper[J]. Journal of Experiments in Fluid Mechanics. DOI: 10.11729/syltlx20230165
    [3]ZHU Xinxin, WANG Hui, HU Dezhou, HUANG Zhenjun, ZHAO Wenfeng. Research on stagnation point heat flux measurement methods of the sharp leading edge model in arc-heated wind tunnel test[J]. Journal of Experiments in Fluid Mechanics. DOI: 10.11729/syltlx20230051
    [4]CHEN Suyu, DING Tao, KONG Rongzong, TIAN Runyu, LIU Jichun, GONG Hongming. Heat flux measurement of small scale gap corner at high Mach numbers[J]. Journal of Experiments in Fluid Mechanics, 2022, 36(6): 89-96. DOI: 10.11729/syltlx20210063
    [5]Zhang Yang, Jia Guangsen, Sha Xinguo, Chen Xing. Precise stagnation point heat flux measurement technique of sharp leading edges[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(6): 59-64. DOI: 10.11729/syltlx20180112
    [6]Chen Guangqiang, Dou Xiuxin, Yang Yunjun, Zhou Weijiang, Dou Guohui. Study on calibration of FADS system for air-breathing air-to-air missile[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(5): 89-95. DOI: 10.11729/syltlx20170133
    [7]Zhang Enlai, Li Zhufei, Li Yiming, Yang Jiming. Investigation on the shock interactions between an incident shock and a plate with V-shaped blunt leading edge[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(3): 50-57. DOI: 10.11729/syltlx20180002
    [8]Li Binbin, Yao Yong, Gu Yunsong, Cheng Keming. Experimental investigation on separation flow control of backward facing step with synthetic j et[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(3): 53-60. DOI: 10.11729/syltlx20150137
    [9]HUANG Ming-qi, LAN Bo, YANG Yong-dong, PENG Xian-min. Φ5m立式风洞直升机垂直升降试验台研制[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(5): 94-97. DOI: 10.3969/j.issn.1672-9897.2013.05.018
    [10]HUANG Ming-ke. Stationary stability of free vortex in the flow over the backward-facing step[J]. Journal of Experiments in Fluid Mechanics, 1999, 13(3): 21-24. DOI: 10.3969/j.issn.1672-9897.1999.03.003

  • Cited by

    Periodical cited type(7)

    1. 陈舒越，郭向东，陈晨，刘森云，赖庆仁. 基于多种测试平台喷雾粒径特性实验研究. 装备环境工程. 2022(06): 59-67 .
    2. 陈舒越，郭向东，王梓旭，刘森云，吴迎春. 结冰风洞过冷大水滴粒径测量初步研究. 实验流体力学. 2021(03): 22-29 . 本站查看
    3. 沈贺，魏搏，姜禹，郭文峰，李岩. 叶片数对垂直轴风力机结冰分布影响风洞试验. 实验流体力学. 2021(04): 67-72 . 本站查看
    4. 申连洋，任永鹏，周少伟，万雷. 船用燃气轮机导流罩结冰试验研究. 黑龙江科学. 2020(14): 4-6 .
    5. 杜骞，赵伟伟，刘宇，蔡玉飞，朱春玲. 小型冰风洞液滴平均容积直径测量研究. 空气动力学学报. 2018(04): 627-633 .
    6. 李岩，孙策，郭文峰，王绍龙，冯放，姜禹. 利用自然低温的旋转叶片结冰风洞试验系统设计. 实验流体力学. 2018(02): 40-47 . 本站查看
    7. 陈旦，李树成，张永双，盖文，黄威凯. 某结冰风洞喷雾水压控制系统设计. 计算机测量与控制. 2017(09): 68-71 .

    Other cited types(7)

Catalog

    Get Citation
    PDF
    XML

    Article Metrics

    Article views (478) PDF downloads (33) Cited by(14)
    Related

    Submit Article

    Submission Guidelines

    Contact Us

    Qrcode

    Copyright © Editorial Department of Experimental Fluid Mechanics All Rights Reserved京ICP备14006930号-5

    Address: P. O. Box 11-9, 6 South Section of Second Ring Road, Mianyang, Sichuan 621000, China

    Tel: 0816-2463376 Email: syltlx@163.com

    Supported by: Beijing Renhe Information Technology Co., Ltd.  Baidu Analytics

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return
    x Close Forever Close