• 论文 •

### 基于WDPR-8支撑与弯刀尾支撑的风洞对比试验研究

1. 1. 厦门大学 航空航天学院, 厦门 361102;
2. 中国空气动力研究与发展中心, 绵阳 621000
• 收稿日期:2020-04-03 发布日期:2021-05-28
• 通讯作者: 林麒 E-mail:qilin@xmu.edu.cn
• 作者简介:潘家鑫,男,硕士研究生。主要研究方向:绳系并联机器人、风洞试验技术;林麒,女,博士,教授,博士生导师。主要研究方向:绳系并联机器人、风洞试验技术、实验流体力学。
• 基金资助:
国家自然科学基金（11472234，11702232，11072207）；中央高校基本科研业务费专项资金（20720180071）

### Comparative experimental study on wind tunnel based on WDPR-8 and machetes tail support

PAN Jiaxin1,2, LIN Qi1, WU Huisong1, ZHOU Fangui1, WANG Xiaoguang1

1. 1. School of Aerospace Engineering, Xiamen University, Xiamen 361102;
2. China Aerodynamics Research and Development Center, Mianyang 621000, China
• Received:2020-04-03 Published:2021-05-28

Abstract: For a dynamic test model designed in China in recent years with a typical advanced fighter layout, Wire-Driven Parallel Robot with 8 Wires (WDPR-8) support and a traditional machetes tail support were used in a FL-5 wind tunnel for a comparative blow test. According to the wind tunnel test environment and the system's stiffness and working space, WDPR-8 wire structure and supporting mechanism were designed, and the prototype was built; for the blocking ratio and the distance between the two centers are small, the versatility of the model in the two support systems was ensured, and the test model of the built-in six-component bar balance was designed; the wire tension signal is used to parallel the WDPR-8 vision acquisition system and the wind tunnel VSS acquisition system to achieve that the three systems work synchronously. Repeatable tests, longitudinal tests, and transverse tests were performed under conditions in which the test conditions are consistent except for the support system. During data processing, the WDPR-8 was not modified for the tail bracket, and the tail support was modified for the tail bracket. The comparison of the test results of the two supports shows that the maximum mean square error of the lift coefficient obtained by the repeated tests in longitudinal test is near. The maximum mean square error of lift coefficient, drag coefficient, pitching moment coefficient obtained by the two supports do not exceed 3.6%. In the transverse test, the variation law of the derivative of the lateral force coefficient to the side slip angle obtained by the two supports are basically the same throughout the test angle of attack. The lift coefficient hysteresis loop curve obtained from the single-degree-of-freedom pitch oscillation test performed with WDPR-8 is consistent with the static lift coefficient curve. The lift coefficient hysteresis loop was continuous from beginning to end, and the area of the unsteady hysteresis loop increases with the shrinkage frequency, which is in line with the physical meaning. The experimental research results reflect the feasibility and effectiveness of the WDPR-8 support.