Abstract:The cruising height of the stratospheric airship is 25 km from the ground. Due to the differences in air temperature and density, the propulsive force provided by the propeller is likely to be quite different from the ground experiment. A flight measurement system is designed for the airship propeller to measure the force and moment in real time, which are received by the propeller during flight. It is used to identify the aerodynamic parameters of the airship. A tube-type two-component strain gauge balance and a data acquisition system are included in the measurement system. The dimension of the balance is designed considering propeller's structure, which can minimize the interference with the airship. And sequence quadratic programming(SQP) method is used to optimize the balance to enhance the axial force signal output. The data acquisition system is used to transmit the load collected by the balance, and contains a variety of sensors to correct the signal. The calibration and the ground simulation test which include influencing factors such as temperature, air pressure, axial acceleration and vibration, are carried out to ensure the accuracy and reliability of the measurement system. The results of flight test data show that the accuracy, consistency and reliability of the system test are good, which can meet the needs of measurement.
曹天赐, 聂营, 王苏宁, 温昊驹, 马洪强. 基于管式应变天平的飞艇螺旋桨飞行测力系统[J]. 机械工程学报, 2022, 58(16): 301-308.
CAO Tianci, NIE Ying, WANG Suning, WEN Haoju, MA Hongqiang. Flight Measurement System for Airship Propeller Based on Tube-type Strain Gauge Balance. Journal of Mechanical Engineering, 2022, 58(16): 301-308.
[1] ZHAO Da, LIU Dongxu, SUN Kangwen, et al. Reasearch status, technical difficulties and development trend of stratospheric airship[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1): 45-56. 赵达, 刘东旭, 孙康文, 等. 平流层飞艇研制现状、技术难点及发展趋势[J]. 航空学报, 2016, 37(1): 45-56. [2] KOENIG R, WULFF G. In-flight gust and load measurements on an airship for model-building and comparison with the transport airship requirements[C/CD]// ICAS 2002 Congress, 2002. [3] HUANG Youwei, CHENG Weizhen, LI Yan, et al. Flight test system for measuring the aerodynamic parameters of rotor blades[J]. Optical Technique, 2012, 38(4): 403-409. 黄有为, 程卫真, 李岩, 等. 直升机旋翼桨叶气动力学参数飞行测试系统[J]. 光学技术, 2012, 38(4): 403-409. [4] HE Fadong. Technology Research of real flight test on hinge moment of aircraft's control surface[J]. Science Technology and Engineering, 2011, 11(31): 7835-7838. 何发东. 飞机舵面铰链力矩飞行实测技术研究[J]. 科学技术与工程, 2011, 11(31): 7835-7838. [5] CAO Gaofeng, YUAN Bo, GUO Bin. Using strain gauge to measure the pull forcw of propeller[J]. Engineering & Test, 2013, 53(2): 12-15. 曹高峰, 原博, 郭斌. 应变计法测量螺旋桨拉力[J]. 工程与试验, 2013, 53(2): 12-15. [6] WEN Haoju. Flight test research of airship propeller force measurement based on strain balance[D]. Beijing: China Academy of Aerospace Aerodynamics, 2016. 温昊驹. 基于应变天平的飞艇螺旋桨测力飞行实验研究[D]. 北京: 中国航天空气动力技术研究院, 2016. [7] PARKER P, DELOACH R. Structural optimization of a force balance using a computational experiment design (Invited)[R]. AIAA, 2002, 540: 14-17. [8] XIANG Guangwei, WANG Jie, SHI Yujie, et al. Research on optimal design method for wind tunnel strain gauge balance based on ISIGHT[J]. Journal of Experiment in Fluid Mechanics, 2015, 29(5): 45-49, 59. 向光伟, 王杰, 史玉杰, 等. 基于ISIGHT的风洞变天平优化设计方法研究[J]. 实验流体力学, 2015, 29(5): 45-49, 59. [9] KARKEHABADI R, RHEW R D. Structural integrity of a wind tunnel balance[C]. AIAA, 2004: 1293. [10] ZHANG Haitian. Reasearch and application of method for optimal design on wind tunnel strain gauge balance[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. 张海天. 杆式应变天平优化设计方法研究与应用[D]. 南京: 南京航空航天大学, 2012. [11] GREER D, HAMORY P, KRAKE K, et al. Design and predictions for high-altitude (low Reynolds number) aerodynamic flight experiment [J]. Journal of Aircraft 2000, 37(4): 684-689. [12] LIU Peiqing, MA Rong, DUAN Zhongzhe, et al. Ground wind tunnel test study of propeller of stratospheric airships[J]. Journal of Aerospace Power, 2011, 26(8): 1775-1781. 刘沛清, 马蓉, 段中喆, 等. 平流层飞艇螺旋桨地面风洞试验[J]. 航空动力学报, 2011, 26(8): 1775-1781.