目的 采用多元线性回归及等效疲劳特性方法寻求直升机平尾动载荷规律。方法 基于平尾载荷及结构特征,设计载荷测试参数及数据采集桥路,开展地面试验,采取多元线性回归理论对其进行标定、解耦,获得满足工程使用的标定方程,并进一步获得典型飞行工况下直升机平尾载荷。采用等效疲劳特性方法对平尾挥舞、摆振动载荷进行分析,研究其变化规律。结果 根据直升机平尾主要载荷特征,设计了挥舞、摆振测试桥路,并基于多元线性回归方法对标定数据进行解耦,结果表明,标定方程误差大部分在5%以内。对典型状态实测数据的分析表明,平尾摆振动载荷相对较大,且与速度、操纵等关系密切。结论 直升机平尾动载荷受多种因素影响,导致其典型状态下相对挥舞动载荷占比超过45%,远远超过气动载荷所占比例,在后续疲劳设计时不可忽略。平尾动载荷和平飞速度有较为强烈的相关性,也和尾桨操纵有关系。
Abstract
The work aims to investigate the dynamic loads of a helicopter's stabilizer with multiple linear regression and equivalent fatigue characteristics methods. Based on the stabilizer's load and structural characteristics, load test parameters and data acquisition bridge circuits were designed, ground tests were conducted, and calibration and decoupling were performed with the multiple linear regression theory to obtain calibration equations suitable for engineering applications. These equations were further used to determine the stabilizer's dynamic loads under typical flight conditions. The equivalent fatigue characteristics method was applied to analyze the flapping and lag dynamic loads of the stabilizer, investigating their variation patterns. According to the primary load characteristics of the stabilizer, flapping and lag test bridge circuits were designed, and calibration data were decoupled with multiple linear regression methods. Results indicated that most of the calibration equations error margin was within 5%. Analysis of actual measurement data under typical conditions showed that the stabilizer's lag dynamic loads were relatively significant and closely related to speed and control inputs. The stabilizer's dynamic loads are affected by multiple factors, leading to the relative flapping dynamic load exceeding 45% in typical conditions, far surpassing the proportion of aerodynamic loads, and thus cannot be neglected in subsequent fatigue design. The stabilizer's dynamic loads exhibit strong correlation with cruise speed and are also related to tail rotor control inputs.
关键词
直升机 /
平尾 /
动载荷 /
挥舞 /
摆振 /
耦合
Key words
helicopter /
stabilizer /
dynamic load /
flapping moment /
lag moment /
coupling
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参考文献
[1] 中国民用航空局. 运输类旋翼航空器适航规定:CCAR-29-R2[S]. 北京:中国民用航空局, 2017.
CAAC. Civil Aviation Regulations of China:CCAR- 29-R2[S]. Beijing:CAAC, 2017.
[2] 国防科学技术工业委员会. 军用直升机结构强度规范:GJB 720.4A—2006[S].北京:国防科工委军标出版发行部, 2006.
Commission of Science, Technology and Industry for National Defense. Military Helicopter Structural Strength Specification:GJB 720.4A—2006[S]. Beijing:Military Standard Publishing and Distribution Department of COSTIND, 2006.
[3] 《飞机设计手册》总编委会. 飞机设计手册-直升机设计[M].北京:航空工业出版社, 2005:147-157.
“Flight Design Manual” Editorial Board. Flight Design Manual-Helicopter Design[M]. Beijing:Aviation Industry Press, 2005:147-157.
[4] 龙海斌, 吴裕平. 直升机平尾纵向气动特性计算与试验相关性分析[J]. 直升机技术, 2021(1):8-12.
LONG H B, WU Y P.Correlation Analysis between Calculation and Test of Longitudinal Aerodynamic Characteristics of Helicopter Horizontal Tail[J]. Helicopter Technique, 2021(1):8-12.
[5] 龙海斌, 吴裕平. 平垂尾大角度气动特性计算与试验结果相关性分析[J]. 直升机技术, 2020(2):6-9.
LONG H B, WU Y P.Correlation Analysis between Calculation and Wind Tunnel Test Results of Large- Angle Aerodynamic Characteristics of Horizontal Tail and Vertical Tail[J]. Helicopter Technique, 2020(2):6-9.
[6] 吕少杰, 曹义华, 肖阳. 直升机机身、平尾、垂尾的气动干扰[J]. 航空动力学报, 2014, 29(5):1122-1127.
LYU S J, CAO Y H, XIAO Y.Aerodynamic Interaction of Fuselage, horizontal Stabilator and Vertical Stabilator of Helicopter[J]. Journal of Aerospace Power, 2014, 29(5):1122-1127.
[7] 谭剑锋, 吴超, 王浩文, 等. 旋翼/平尾气动干扰对直升机配平特性的影响分析[J]. 北京航空航天大学学报, 2016, 42(11):2349-2357.
TAN J F, WU C, WANG H W, et al.Analysis on Influence of Rotor/Empennage Aerodynamic Interaction on Helicopter Trim Characteristic[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(11):2349-2357.
[8] 袁胜弢, 王永和, 王威. 某直升机平尾有限元仿真与试验验证[J]. 计算机辅助工程, 2015, 24(3):9-18.
YUAN S T, WANG Y H, WANG W.Finite Element Simulation and Test Verification on Horizontal Stabilizer of Helicopter[J]. Computer Aided Engineering, 2015, 24(3):9-18.
[9] 赵燕, 王永和, 王威. 某中央翼盒对飞行载荷实测的影响[J]. 航空学报, 2016, 37(4):1234-1242.
ZHAO Y, WANG Y H, WANG W.Effect of Central Wing Box on Flight Load Measurement[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(4):1234-1242.
[10] 张书明, 高建民, 冯炳元, 等. 大型结构部件载荷标定试验方法研究[J]. 农业机械学报, 2000, 31(4):85-88.
ZHANG S M, GAO J M, FENG B Y, et al.Study on Load Calibration Test for Large Sized Structural Components[J]. Transactions of the Chinese Society of Agricultural Machinery, 2000, 31(4):85-88.
[11] 侯玉洁, 杨月. 直升机平尾载荷标定工装夹具设计[J]. 中国设备工程, 2019(6):103-104[J]. China Plant Engineering, 2019(6):103-104.
[12] SKOPINSKI T H, AIKEN W S Jr, HUSTON W B. Calibration of Strain-Gage Installations in Aircraft Structures for the Measurement of Flight Loads:NACA- TN-2993[R]. Washington:National Advisory Committee for Aeronautics, 1953
[13] 曹嘉旻. 基于飞行试验的直升机平尾尺寸研究[J]. 兵器装备工程学报, 2021, 42(S1):125-128.
CAO J M.Research on Tailplane Size of Helicopter Based on Flight Test[J]. Journal of Ordnance Equipment Engineering, 2021, 42(S1):125-128.
[14] REX W, HAJEK M, RINKER M.Sensitivity Study of Helicopter Vibrations and Loads with Elastic Fuselage Coupling and Dynamic Empennage Loads from Free Wake Analysis[C]//Vertical Flight Society 76th Annual Forum Technology Display. Virtual:[s. n.], 2020.
[15] NIU M C.Airframe Stress Analysis and Sizing[M]. Granada Hills:Conmilit Press LTD, 1997:249-256.
[16] 阎楚良, 张书明, 卓宁生, 等. 飞机机翼结构载荷测量试验力学模型与数据处理[J]. 航空学报, 2000, 21(1):56-59.
YAN C L, ZHANG S M, ZHOU N S, et al.Mechanical Model and Data Processing of Load Measurement Test for the Airplane's Wing Structure[J]. Acta Aeronautica et Astronautica Sinica, 2000, 21(1):56-59.
[17] SKORUPKA Z, SOBIESZEK A.Strain Gauge Pin Based Force Measurement in Helicopter Landing Gear[J]. Journal of Aerospace Engineering, 2018, 25(2):335-340.
[18] 王泽峰, 谢强. 某涵道式尾桨直升机垂尾载荷实测研究[J]. 工程与试验, 2018, 58(1):24-26.
WANG Z F, XIE Q.Experimental Study on Vertical Tail Load of a Ducted Tail Rotor Helicopter[J]. Engineering & Test, 2018, 58(1):24-26.
[19] 郑甲宏, 王泽峰, 沈雳. 直升机载荷标定方程回归变量的优选方法[J]. 科学技术与工程, 2017, 17(24):299-303.
ZHENG J H, WANG Z F, SHEN L.Screening Method of Regressor Variable for Load Calibration Strain Parameter[J]. Science Technology and Engineering, 2017, 17(24):299-303.
[20] 高腾龙, 孟敏, 何发东, 等. 中央肋对接平尾结构非对称载荷测量技术[J]. 力学与实践, 2023, 45(3):551-558.
GAO T L, MENG M, HE F D, et al.Asymmetric Load Measurement Technology for Central Rib Butted Horizontal Tail Structure[J]. Mechanics in Engineering, 2023, 45(3):551-558.
[21] 孙韬, 谭剑锋, 王浩文. 典型飞行状态下的旋翼振动载荷计算与分析[J]. 南京航空航天大学学报, 2011, 43(3):302-307.
SUN T, TAN J F, WANG H W.Prediction and Analysis of Rotor Vibration Loads in Typical Flight Conditions[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2011, 43(3):302-307.
[22] 赵岩, 周瑞鹏, 贾甜. 移动随机荷载作用下梁桥非平稳随机振动的PEM-FFT方法[J]. 计算力学学报, 2019, 36(1):65-70.
ZHAO Y, ZHOU R P, JIA T.PEM-FFT for Non- Stationary Random Vibration Analysis of Simple-Supported Beam Bridge under Moving Random Load[J]. Chinese Journal of Computational Mechanics, 2019, 36(1):65-70.
[23] 穆志韬, 曾本银, 金平, 等. 直升机结构疲劳[M]. 北京:国防工业出版社, 2009:248-260.
MU Z T, ZENG B Y, JIN P, et al.Fatigue of Helicopter Structures[M]. Beijing:National Defense Industry Press, 2009:248-260.
[24] MINER M A.Cumulative Damage in Fatigue[J]. Journal of Applied Mechanics, 1945, 12(3):A159-A164.
[25] 刘诗鸾, 王云, 张高望, 等. 变距旋翼无人机悬停气动性能分析与试验[J]. 航空科学技术, 2014, 25(5):104-108.
LIU S L, WANG Y, ZHANG G W, et al.Hovering Aerodynamic Performance Analysis and Experiment of Variable Pitch Rotor UAV[J]. Aeronautical Science & Technology, 2014, 25(5):104-108.
[26] LEISHMAN J G.Principles of Helicopter Aerodynamics[M]. 2nd ed. Cambridge:Cambridge University Press, 2006:425-460.
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