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针对大型飞机全机静力试验中承载结构大变形特征，提出了一套完整的飞机大变形结构强度试验方案，开展了大变形试验误差分析和试验系统设计要求研究，突破了试验件载荷处理、飞机支持、载荷施加、配平设计、姿态修正等关键技术，最后以某型飞机大变形试验工况为研究对象完成了试验技术的应用与验证。试验结果表明，提出的试验方案科学合理，可以精确完成机翼大变形状态下考核结构的强度验证，验证了技术方案的有效性，为大型飞机大变形试验技术标准化提供了重要参考。
Abstract：Aiming at the large deformation characteristics of the load-bearing structure in the full-scale static test of large aircraft, a set of structural static test schemes for aircraft with large deformation was proposed. Research on error analysis and test system design requirements for large deformation test was carried out, and the key technologies such as load process, aircraft support, load application, load balancing design and attitude revised were also broken through. Finally, the application and verification of test technology were completed based on the large deformation test condition of one certain type of aircraft. The test results show that the proposed test scheme is scientific and reasonable, and it can accurately apply the test load of the assessment structure under the large deformation of the wing, verifing the effectiveness of the technical scheme. The results can also provide important references for the standardization of large deformation test technology for large aircraft.
[1]中国民用航空局.运输类飞机适航标准：CCAR-25-R4—2011[S/OL].[2025-09-20]. http：∥www. caac. gov.cn/XXGK/XXGK/MHGZ/201606/t20160622_38638.html.China Civil Aviation Administration. Airworthiness standards for transport airplane:CCAR-25-R4—2011[S/OL].[2025-09-20]. http：∥www. caac. gov. cn/XXGK/XXGK/MHGZ/201606/t20160622_38638.html.(in Chinese)
[2]SHIM J Y. Evaluating the accuracy of load application for static structural testing of aerospace flight vehicles[J]. International Journal of Aeronautical and Space Sciences, 2020, 21(1):133-152.
[3]王彬文，聂小华，万春华，等.全机静强度虚拟试验技术研究及应用[J].航空学报，2022, 43(6):526273.WANG B W, NIE X H, WAN C H, et al. Research and application of virtual test technology for static strength of full scale aircraft structure[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(6):526273.(in Chinese)
[4]郑建军，唐吉运，王彬文. C919飞机全机静力试验技术[J].航空学报，2019, 40(1):522364.ZHENG J J, TANG J Y, WANG B W. Static test technology for C919 full-scale aircraft structure[J].Acta Aeronautica et Astronautica Sinica, 2019, 40(1):522364.(in Chinese)
[5]刘兴科，刘冰，张建锋.全尺寸飞机大展弦比机翼静力试验技术研究[J].工程与试验，2014, 54(1):17-20, 28.LIU X K, LIU B, ZHANG J F. Study on static test technology for high-aspect ratio wing of full scale aircraft[J]. Engineering&Test, 2014, 54(1):17-20,28.(in Chinese)
[6]张廷玉，董天智，何川，等.基于大变形加载及精确测量的轻质机翼静强度试验技术[J].内燃机与配件，2024(10):128-131.ZHANG T Y, DONG T Z, HE C, et al. Static strength test technology for light wing based on large deformation loading and accurate measurement[J].Internal Combustion Engine&Parts, 2024(10):128-131.(in Chinese)
[7]刘冰，张赟，刘玮，等.基于误差控制的大展弦比机翼静强度试验载荷处理技术[J].科学技术与工程，2017, 17(30):356-360.LIU B, ZHANG Y, LIU W, et al. Load process technology based on error control for static strength test of high-aspect ratio wing[J]. Science Technology and Engineering, 2017, 17(30):356-360.(in Chinese)
[8]宋晓鹤，李健，王利国，等.大展弦比机翼考虑结构变形的试验载荷设计技术研究[C]∥第八届中国航空学会青年科技论坛论文集.[出版地不详：出版者不详]，2018:1206-1211.SONG X H, LI J, WANG L G, et al. Research of the technology to design test load taking into account the effect of structure deformation in high-aspect-ratio wing full scale test[C]∥Proceedings of the 8th youth science and technology forum of the Chinese society of aeronautics and astronautics.[S. l.:s. n.], 2018:1206-1211.(in Chinese)
[9]田文朋，夏峰，宋鹏飞，等.水陆两栖飞机静力试验优化机翼变形的载荷配平[J].航空学报，2020, 41(11):223956.TIAN W P, XIA F, SONG P F, et al. Load balancing for wing deformation optimization in amphibious aircraft static test[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(11):223956.(in Chinese)
[10]段连国.面向大展弦比机翼静力试验的加载机构研究与分析[D].秦皇岛：燕山大学，2015:21-27.DUAN L G. The research and analysis of static test loading mechanism for high-aspect ratio wing[D]. Qinhuangdao:Yanshan University, 2015:21-27.(in Chinese)
[11]李小欢，张蕾.大展弦比机翼试验随动加载系统研究[J].航空工程进展，2019, 10(2):221-227.LI X H, ZHANG L. Research on the servo loading systems of high aspect ratio wing test[J]. Advances in Aeronautical Science and Engineering, 2019, 10(2):221-227.(in Chinese)
[12]刘玮，郑建军.大型客机结构试验主起落架随动加载技术[J].航空科学技术，2020, 31(12):42-47.LIU W, ZHENG J J. Self-adaptable loading technique for main landing gears in structural test of large airliner[J]. Aeronautical Science&Technology, 2020, 31(12):42-47.(in Chinese)
[13]王鑫，杜峰，杨海.基于随动加载试验技术的双垂尾结构强度[J].科学技术与工程，2018, 18(7):259-262.WANG X, DU F, YANG H. The structural strength of double vertical tail based on the technique of dynamic loading test[J]. Science Technology and Engineering,2018, 18(7):259-262.(in Chinese)
[14]燕晨耀，尹伟，杜星，等.大型飞机结构强度试验姿态转换与控制[J].机床与液压，2024, 52(4):56-62.YAN C Y, YIN W, DU X, et al. Attitude conversion and control in structural strength test of the large aircraft[J]. Machine Tool&Hydraulics, 2024, 52(4):56-62.(in Chinese)
[15]张清勇，李宏亮.基于坐标系转换的刚体位移修正方法研究[J].工程与试验，2019, 59(4):78-79, 115.ZHANG Q Y, LI H L. Rigid body displacement amendatory method based on coordinate system transformation[J]. Engineering&Test, 2019, 59(4):78-79,115.(in Chinese)
[16]付志超，仲维国，陈志平，等.大展弦比柔性机翼的结构动力学特性试验研究[J].航空学报，2013, 34(9):2177-2184.FU Z C, ZHONG W G, CHEN Z P, et al. Experimental study on structural dynamic characteristics of flexible high-aspect-ratio wings[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(9):2177-2184.(in Chinese)
[17]郭琼，夏峰，刘冰，等.全尺寸飞机结构静力试验约束点载荷计算及应用[J].科学技术与工程，2020, 20(19):7934-7940.GUO Q, XIA F, LIU B, et al. Calculation and application of restraint load in full-scale aircraft static test[J]. Science Technology and Engineering, 2020, 20(19):7934-7940.(in Chinese)
[18]朱昆鹏.民机襟翼运动机构可靠性试验研究[D].南京：南京航空航天大学，2011:55-62.ZHU K P. Test and research of flap movement mechanism reliability for the civil aircraft[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2011:55-62.(in Chinese)
[19]李小军，陆慧莲，李凯.一种主动驱动随动加载的前缘缝翼和襟翼疲劳试验技术[J].民用飞机设计与研究，2014(3):17-20, 91.LI X J, LU H L, LI K. Fatigue test technology of slat and flap with active driving and servo loading device[J]. Civil Aircraft Design&Research, 2014(3):17-20, 91.(in Chinese)
[20]庞宝才，董登科，弓云昭，等.襟缝翼可动翼面的随动加载方法研究[J].机械科学与技术，2014, 33(10):1590-1593.PANG B C, DONG D K, GONG Y Z, et al. Study on tracking loading method of locomotory wing for flap and slat[J]. Mechanical Science and Technology for Aerospace Engineering, 2014, 33(10):1590-1593.(in Chinese)
[21]陈建国.飞机襟缝翼收放功能试验随动加载研究[J].工程与试验，2015, 55(3):1-4.CHEN J G. Study on tracking-loading for retractable function test of flap and slat of aircraft[J]. Engineering&Test, 2015, 55(3):1-4.(in Chinese)
[22]杜峰.某飞机襟缝翼疲劳试验系统随动加载技术研究[J].工程与试验，2017, 57(4):68-73.DU F. Study on tracking-loading technology for fatigue test system of flap and slat of aircraft[J]. Engineering&Test, 2017, 57(4):68-73.(in Chinese)
[23]何志全，刘杨，李泽江.大型民用飞机缝翼全尺寸静力试验载荷设计[J].航空学报，2019, 40(2):522197.HE Z Q, LIU Y, LI Z J. Load design for full scale static test of slat on large civil aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(2):522197.(in Chinese)
[24]张柁，张园，杨兆林，等.基于轨迹模拟的活动翼面随动加载技术及应用[J].科学技术与工程，2019, 19(18):324-328.ZHANG T, ZHANG Y, YANG Z L, et al. Application of moving airfoil following loading technology based on trajectory simulation[J]. Science Technology and Engineering, 2019, 19(18):324-328.(in Chinese)
基本信息:
中图分类号:V216.1
引用信息:
[1]刘冰,张建锋,周銮良.大载荷大变形飞机全机静力试验技术[J].中国科技论文,2026,21(02):104-115.