Research on the dynamic derivatives test technology of 4.5 m × 3.5 m low speed wind tunnel
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摘要: 动导数是飞行器操稳特性分析、控制律设计过程中的关键参数。为满足大型飞行器研制对高精度动导数数据的获取需求，中国航空工业空气动力研究院基于4.5 m × 3.5 m低速风洞开发了具备5种振荡试验能力的低速动导数试验系统。该试验系统利用伺服液压摆动马达和伺服液压缸作为运动的驱动元件，经过伺服阀的控制直接产生任意波形的强迫运动，具有运动传递间隙小、运动控制精度高、系统自动化程度高等特点。可实现2.5 m量级模型的动导数试验，风速范围30～60 m/s，迎角范围−36°～36°，侧滑角范围−40°～40°。利用动态标模及某翼身融合布局模型进行了动导数验证试验，结果表明该系统获得的动导数数据规律合理，数据精度在3%以内，可为大型飞行器研制提供高质量的动导数试验数据。Abstract: The dynamic derivatives are the a necessary parameters in the process of analyzing the stability of the aircraft and designing the control law, in order to meet the demand for obtaining high-precision dynamic derivatives data for large-scale aircraft. Aerodynamics Research Institute of Aviation Industry Corporation of China （AVIC） developed a dynamic derivatives test system with five kinds of oscillations in the 4.5 m × 3.5 m low-speed wind tunnel. The test system uses servo hydraulic swing motor and servo hydraulic cylinder as the driving components of the motion, and directly generates arbitrary waveform motion with the control of the servo valve. The driving mode of the system has the characteristics of small movement transmission gap, high movement control precision, and high automation. The scale of the test model is up to 2.5 m, with the wind speed v =30～60 m/s, the angle of attack α= −36°～36°, and the sideslip angle β= −40°～40°. The verification tests of the dynamic standard model and a wing-body model were carried out, and the test results show that the dynamic derivatives data obtained by the test system is reasonable, the accuracy of the repeatability test data is within 3%, and the test system can provide high-quality dynamic derivatives data for large-scale aircraft.
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图 3 平移振荡动导数试验装置示意图
Figure 3. Schematic of translational oscillation dynamic derivatives test device
图 9 1 m量级动态标模滚转振荡试验对比曲线
Figure 9. Comparison curve of rolling oscillation test of standard dynamic model
表 1 角振荡动导数试验装置模态分析结果
Table 1. Modal analysis results of angular oscillation test device
模态阶数 频率/Hz 1 16.06 2 19.35 3 34.29 4 37.62 5 46.83 6 48.91 
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表 2 平移振荡试验装置模态分析结果
Table 2. Modal analysis results of translational oscillation test device
模态阶数 频率/Hz 1 23.16 2 32.82 3 35.36 4 98.11 5 99.55 6 117.61
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表 3 角振荡运动曲线与给定标准信号的差异
Table 3. Differences between angular oscillation motion curve and given standard signal
振幅/（°） 频率/Hz 幅值差/（°） 相位差/（°） 3 0.5 0.015 0.13 3 1.0 0.020 0.16 3 1.5 0.025 0.16 3 2.0 0.032 0.07 3 2.5 0.040 0.05
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表 4 平移振荡运动曲线与给定标准信号的差异
Table 4. Differences between translational oscillation motion curve and given standard signal
振幅/m 频率/Hz 幅值差/m 相位差/（°） 0.12 0.5 0.0014 1.48 0.12 1.0 0.0021 1.1 0.12 1.5 0.0028 0.70 0.12 2.0 0.0031 0.3 0.12 2.5 0.0032 0.04
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表 5 翼身融合布局飞机动导数试验模型参数
Table 5. Dynamic derivative test model parameters of wing-body
参数 值 模型比例 1∶15 参考面积S/m2 1.072 平均气动弦长cA/m 0.691 展长b/m 2.4
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表 6 动导数重复性精度
Table 6. Dynamic derivatives repeatability accuracy
α/（°） $ （{C}_{mq} + {C}_{m\dot{\alpha }}） $/% $ （{C}_{lp} + {C}_{l\dot{\beta }}\mathrm{sin}\alpha ） $/% $ （{C}_{nr}-{C}_{n\dot{\beta }}\mathrm{cos}\alpha ） $/% 0 1.0 0.2 0.4 8 0.4 0.4 0.3 16 0.4 1.0 1.0 20 1.7 0.3 2.0 24 2.9 0.1 2.8
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