低速风洞飞行器模型编队飞行绳系并联支撑机构

doi:10.7527/S1000-6893.2019.123144

流体力学与飞行力学

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低速风洞飞行器模型编队飞行绳系并联支撑机构

吴惠松, 林麒, 彭苗娇, 柳汀, 冀洋锋, 王晓光

厦门大学航空航天学院, 厦门 361102

收稿日期:2019-05-13 修回日期:2019-05-20 出版日期:2019-12-03 发布日期:2019-12-03
通讯作者: 林麒 E-mail:qilin@xmu.edu.cn
基金资助:
国家自然科学基金（11472234，11702232）；中央高校基本科研业务费专项资金（20720180071）

Wire-driven parallel suspension mechanism for aircraft model of formation flight in low-speed wind tunnel

WU Huisong, LIN Qi, PENG Miaojiao, LIU Ting, JI Yangfeng, WANG Xiaoguang

School of Aerospace Engineering, Xiamen University, Xiamen 361102, China

Received:2019-05-13 Revised:2019-05-20 Online:2019-12-03 Published:2019-12-03
Supported by:
National Natural Science Foundation of China (11472234, 11702232); the Fundamental Research Funds for the Central Universities (20720180071)

摘要/Abstract

摘要： 设计了一种用于飞行器双机编队飞行的风洞试验模型绳系并联支撑机构，模拟在周边有障碍物的有限空间通道中的飞行运动。以直升机为例，根据工况参数设计了双绳牵引并联机构作为飞行器模型的支撑，建立了基于可移动的滑轮铰点与直升机模型编队协同飞行的运动学模型，对系统的静刚度进行了分析，并通过试验验证了旋翼转动对该绳系支撑系统动刚度的影响，给出了在有限空间通道中模拟双机编队飞行与着陆过程中绳与绳之间、绳与模型之间的干涉算法，并对该支撑机构的绳系结构进行了干涉分析。结果表明，所设计的支撑机构能有效解决模拟飞行器模型双机编队在有限空间中飞行运动时的支撑干涉问题，而且系统刚度达到低速风洞试验的稳定性要求，是低速风洞中支撑飞行器模型进行编队飞行试验的有效解决方案。

关键词: 低速风洞, 飞行器编队飞行, 并联支撑机构, 刚度分析, 干涉分析

Abstract: In this paper, a wire-driven parallel suspension mechanism for two aircraft models in formation flight is designed to simulate the flight motion in a limited space channel with obstacles around it in wind tunnel test. Taking the helicopter as an example, based on the working condition parameters, the double wire-driven parallel mechanisms are designed as the support of the aircraft model, and the kinematic model of the helicopter for cooperative motion between the movable pulley suspension point and the helicopters in formation flight is established. Furthermore, the static stiffness of the system is analyzed, and the influence of rotor rotation on the dynamic stiffness of the wire-driven parallel suspension system is verified by experiments. Additionally, the algorithm of interference between the wire and the wire, the wire and the model in the process of two aircraft models in formation flight simulated flying and landing in the limited space channel is given, and the interference analysis of the wire structure of the support mechanism is carried out. The results show that the support mechanism designed in this paper can effectively solve the support interference problem for two aircraft models in formation flight in the limited space channel, and the system stiffness meets the stability requirements of the low-speed wind tunnel test, making it an effective solution for aircraft model formation flight test in low-speed wind tunnel.

Key words: low-speed wind tunnel, aircraft formation flight, parallel suspension mechanism, stiffness analysis, interference analysis

中图分类号:

V216

吴惠松, 林麒, 彭苗娇, 柳汀, 冀洋锋, 王晓光. 低速风洞飞行器模型编队飞行绳系并联支撑机构[J]. 航空学报, 2019, 40(11): 123144-123144.

WU Huisong, LIN Qi, PENG Miaojiao, LIU Ting, JI Yangfeng, WANG Xiaoguang. Wire-driven parallel suspension mechanism for aircraft model of formation flight in low-speed wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(11): 123144-123144.

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低速风洞飞行器模型编队飞行绳系并联支撑机构

Wire-driven parallel suspension mechanism for aircraft model of formation flight in low-speed wind tunnel

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