Rolling maneuver load alleviation of aircraft with continuously variable-camber trailing edge
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摘要:
变弯度后缘机翼具有变形连续、阻力较小、气动噪声较低等优势，越来越多地应用于新概念飞行器的设计之中。基于此，提出一种基于变弯度后缘的飞行器刚弹耦合动力学建模方法，并针对变弯度后缘飞机缩比模型开展了滚转机动仿真分析与风洞试验。结果表明：变弯度后缘可以操纵飞机在2 s内进行180°滚转机动。相较于外侧后缘单独变形，通过内外后缘协同变形可以降低30%以上的滚转机动附加载荷。另外，对比表明滚转角仿真结果与风洞试验数据误差小于6%，验证了所提方法的准确性。
Abstract:The variable-camber trailing edge is frequently used in new concept aircraft design because of its advantages of continuous deformation, less resistance, and low aerodynamic noise. A rigid-elastic coupling dynamics modeling method based on the variable-camber trailing edge was proposed, and rolling maneuver simulation analysis and wind tunnel test were carried out using a scale model of aircraft with the variable-camber trailing edge. The results show that the variable-camber trailing edge can maneuver the aircraft to roll 180° within 2 s. Additional rolling maneuver load can be reduced by more than 30% through cooperative inner and outer trailing edge deformation compared to outer trailing edge deformation alone. In addition, a comparative study shows that the error between rolling maneuver simulation results and wind tunnel test data is less than 6%, which confirms the accuracy of the established theoretical model.
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图 1 弹性飞机滚转机动仿真框架
Figure 1. Framework of rolling maneuver simulation of elastic aircraft
图 7 变形翼肋结构有限元模型变形分布
Figure 7. Deformation distribution of structural finite element model of flexible rib
图 8 2种舵面模态构造方法对比
Figure 8. Comparison of two control surface mode construction methods
图 9 不同舵面模态下滚转机动开环响应随时间变化曲线
Figure 9. Variation of open-loop response of rolling maneuver with time in different control surface modes
图 10 弹性飞机滚转机动控制系统架构
Figure 10. Architecture of rolling maneuver control system of elastic aircraft
图 11 滚转机动闭环响应及载荷随时间变化曲线
Figure 11. Variation of close-loop response of rolling maneuver and load with time
图 21 风洞试验数据与仿真结果对比
Figure 21. Comparison of wind tunnel test data and simulation results
表 1 全机结构动力学特性
Table 1. Structural dynamics characteristics of aircraft
序号 频率/Hz 模态描述 1 0 全机滚转 2 18.53 机翼对称一弯 3 27.64 机翼反对称一弯 4 39.51 面内模态 5 47.14 机翼对称一扭 
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表 2 控制律参数优化结果
Table 2. Parameter optimization results of control law
控制律参数 Kp1 Kp2 Kp3 Ki K1 K2 基准控制 6.5176 0.0253 0 0.3323 −1 0 滚转机动载荷减缓控制 6.3895 0.0321 0.0973 0.5189 − 0.6750 − 0.0916
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表 3 地面模态试验结果
Table 3. Results of ground modal test
序号 频率/Hz 模态描述 1 1.52 全机滚转 2 11.09 机翼对称一弯 3 15.88 机翼反对称一弯 4 64.86 机翼对称一扭
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