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摘要:
基于某运输机带冰风洞试验数据和结冰升力特性分析，得出结冰对小迎角(AOA)范围内升力系数影响较小的结论。设计一种基于该先验知识增强的升力系数多项式在线主成分估计方法，克服由于激励不足和回归量之间共线性导致的数据矩阵病态问题。利用结冰后升力曲线斜率变化量与最大升力系数呈现的良好线性关系估计了最大升力系数和失速迎角。与现有方法相比，所设计方法具有成熟度高、实时性好、不依赖主动激励的显著优点。仿真结果表明：所设计方法估计精度可以满足迎角保护要求，具有良好的工程应用前景。
Abstract:Based on the wind tunnel test data of a transport aircraft with ice and the analysis of icing lift characteristics, it is concluded that icing has little effect on the lift coefficient in the small angle of attack (AOA) range. An online principal component estimation algorithm of lift coefficient polynomial based on prior knowledge enhancement was designed to overcome the ill-conditioned problem of data matrix due to insufficient excitation and collinearity between regression variables. The maximum lift coefficient and stall AOA were estimated by using the good linear relationship between the slope variation of the lift curve and the maximum lift coefficient after icing. Compared with traditional methods, the designed method has significant advantages such as high maturity, good real-time performance, and no need for active excitation. Simulation results show that the estimation accuracy can meet the requirements of AOA protection, and the designed method has good engineering application prospects.
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图 2 构型0升力系数多项式拟合曲线
Figure 2. Polynominal fitting curves of lift coefficient of configuration 0
图 3 构型3升力系数多项式拟合曲线
Figure 3. Polynominal fitting curves of lift coefficient of configuration 3
图 4 构型4升力系数多项式拟合曲线
Figure 4. Polynominal fitting curves of lift coefficient of configuration 4
图 5 $ \Delta C_y^\alpha $与$ {C_{y\max }} $的线性关系
Figure 5. Linear relationship between $ \Delta C_y^\alpha $and$ {C_{y\max }} $
图 8 水平飞行迎角保护仿真曲线
Figure 8. Simulation curves of angle of attack protection for horizontal flight
图 9 30°坡度转弯迎角保护仿真曲线
Figure 9. Simulation curves of angle of attack protection for 30° bank turn
表 1 飞机结冰强度等级划分
Table 1. Classification of aircraft icing intensity
结冰等级 单位时间结冰厚度/(mm·min−1) 微量结冰 <0.6 轻度结冰 0.6~1.0 中等结冰 1.1~2.0 严重结冰 >2.0 
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表 2 不同稳态迎角下的参数估计值
Table 2. Parameter estimates at different steady-state angles of attack
稳态迎角/(°) $ {\left. {C_y^\alpha } \right|_{\alpha = {9^ \circ }}} $ ${\left. {\bar C_y^\alpha } \right|_{\alpha = {9^ \circ }}} $ ${\left. {\Delta C_y^\alpha } \right|_{\alpha = {9^ \circ }}} $ $\Delta {\left. {\bar C_y^\alpha } \right|_{\alpha = {9^ \circ }}} $ $ {\hat \alpha _{\mathrm{m}}} $/(°) 7 0.0665 0.9210 0.0336 1.2043 12.414 9 0.0785 1.0872 0.0216 0.7741 14.069 11 0.0793 1.0983 0.0208 0.7455 14.180 13.2 0.0736 1.0193 0.0265 0.9498 13.394
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