待机状态下机翼结冰的快速计算方法

飞机在飞行过程中遭遇结冰气象，尤其是过冷大水滴结冰条件所导致的机翼结冰，将严重影响飞机的气动性能与操纵品质，从而导致飞行故障或飞行事故，是飞机飞行安全的重要影响因素，是飞机研制中必须重点解决的难题。虽然针对结冰已建立有多种计算仿真程序，但快速获得结冰模拟冰形，包括过冷大水滴条件下的结冰模型是工程师们一直追求的解决方案。利用前向多层神经网络，尝试建立了一种针对待机状态下的机翼结冰模型。此方法基于坐标转换原理，将获取的采用直角坐标表达的标准翼型的机翼结冰数据转换为对应的极坐标表达的数据，以飞行参数、气象参数和极坐标角度作为输入，极坐标模值作为输出训练构建出此种机翼结冰模型。使用所建立的模型，仿真预测结果表明该计算方法具备快速性和精确性，其计算精度可满足实际要求。

Approximately fast calculation method of aircraft icing under standby conditions

The aircraft encounters icing weather during flight, especially the wing icing caused by the icing conditions of supercooled large water droplets, which will seriously affect the aerodynamic performance and handling quality of the aircraft, resulting in flight faults or flight accidents. It is an important factor for the flight safety of the aircraft and a difficult problem that must be solved in the development of the aircraft. Although a variety of calculation and simulation programs have been established for icing, it is a solution that engineers have been pursuing to quickly obtain the simulated icing shape, including the icing model under the condition of supercooled large water droplets. This paper attempts to establish a wing icing model in standby mode by using forward multilayer neural network. Based on the coordinate transformation principle, this method converts the obtained wing icing data of the standard airfoil expressed in rectangular coordinates into the data expressed in corresponding polar coordinates. The wing icing model is constructed with flight parameters, meteorological parameters and polar coordinate angles as inputs and polar coordinate modulus as output training. Using the established model, the simulation and prediction results show that the method is fast and accurate, and its calculation accuracy can satisfy the actual requirements.