摘 要：根据现代飞机鸭翼结构特点及载荷测量要求，提出了在鸭翼大轴外缘选择一个剖面进行测载应变计改装的方法，并采用不同侧应变计以特定方式组成惠斯通电桥。在载荷校准试验中，左右鸭翼同时对称向上施加校准载荷，利用飞机重量和后机身托架即可平衡加载载荷引起的飞机移动和转动，不需要对飞机进行复杂的约束和固定。通过对校准试验数据分析，某种应变电桥只对与其对应的载荷敏感，而对其它载荷响应较小，实现了对鸭翼弯矩、扭矩、剪力的机械解耦，据此数据可建立高精度的鸭翼载荷模型。对飞机各种机动情况下的鸭翼飞行载荷实测数据进行了分析研究，结果表明：采用此种方法进行飞机鸭翼载荷测量，改装和试验方法简便，载荷实测结果可信、可靠。
Abstract: According to the structural characteristics of modern canard aircraft and load measurement equirements，Presented a strain gauge modified method at the outer shaft canard profile，And composed of the certain Wheatstone bridge with different side strain gauge. In the load calibration tests, applying the symmetrical calibration load on Canard at the same time, Keep the aircraft balance with the aircraft weight and rear fuselage bracket, The aircraft is not required a fixed complex constraints. Through the analysis of the calibration test data，A strain gauge bridge load on the corresponding sensitive response,and smaller to the other load, To realize the mechanical decoupling of canard wing bending moment, torque, shear，according to the data can establish high precision Duck wing load model. On the aircraft of various motor case duck wing flight loads measured data are analyzed, The results showed that: Using this method to measure the aircraft duck wing loading, Refit and test method is simple, the Results of load measurement are trusted and reliable.
参考文献
［1］蒋祖国，田丁栓.飞机结构载荷/环境谱［M］.北京:电子工业出版社 2012：260—267 (Jiang Zuguo,Tian Dingshuan Environment load/spectrum of aircraft structure［M］.
Beijing: Publishing House of electronics industry 2012：260—267 (in Chinese))
［2］ 李为吉，王正平.飞机总体设计［M］.西安:西北工业大学出版
社2005: 129—135 (Li Weiji,Wang Zhengping The aircraft conceptual design ［M］.Xi’an Northwestern Polytechnical University press 2005：129—135 (in Chinese))
［3］Willain A.Lokos,* Candida D.Olney,and Tony Chen
Strain-gage loads calibration testing of the active
Aeroelastic wing F/A-18 airplane 2926［R］.NASA Dryden
Flight Research Center Edwards,California.2002.
［4］哈尔滨工业大学理论力学教研室 理论力学［M］:4版 北京:
高等教育出版社,1993：180-206（Theoretical mechanics
teaching and Research section of Harbin institute of technology, theoretical mechanics［M］. Beijing : Higher education press, 1993：180-206 (in Chinese)).
［5］张贤达 矩阵分析与应用［M］.北京：清华大学出版社，2004:1-10.(Zhang Xianda Matrix Analysis and
Applications［M］.Beijing : Tsinghua University press
(in Chinese))
［6］ Norman S.Currey 起落架设计手册［M］.王裕昌，孙书田 ,译.北京 航空工业部 1982：657-659（Norman S.Currey The landing gear design manual［M］.Wang Yuchang,Sun Shutian ,translated. Beijing : Ministry of aviation industry 1982：657-659 (in Chinese)）
［7］М.Л.克利亚奇科 飞机强度飞行试验(静载荷)［M］.汤吉晨,译.西安:航空航天部《ＡＳＳＴ》系统工程办公室,1992: 21-23.(М.Л. Kliqko. Aircraft strength test
(static load)［M］.Tang Jichen ,translated. Xi’an: ASST Engineering office of Ministry of Aeronautics and Astronautis,1992:21-23.(in Chinese))
［8］ skopinski T H ,Aiken William S,Jr,Huston Wilber
B.Calibration strain-gage installations in aircraft
structures for the measurement of flight loads,NACA
Report1178［R］. Hampton: Langley Aeronautical
Laboratory .1954.
［9］ 李庆杨，关治，白峰杉 数值计算原理［M］.北京：清华
大学出版社，2000.154-168（Li Qingyang,Guan Zhi,Bai
Fengshan.Numerical calculation principle［M］.Beijing:
Tsinghua University Press,2000 154-168 (in Chinese))
［10］阎楚良，张书明，卓宁生 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 Chuliang,Zhang Shuming,Zhuo Ningsheng,Mechanical model and data treatment of load measurement test for aircraft wing strutures［J］.Acta Aeronautica et Astronautica Sinica, 2000,21(1):56-59.(in Chinese)）
CJA