Ice accretion on a helicopter’s aerodynamic surfaces during flight can lead to incidents and fatal accidents. An iced helicopter blade results in a decrease in stall angle, an increase in required torque, as well as potential damage from shed ice. While the high centrifugal forces on a rotor may serve as a natural deicing mechanism, they can also lead to uneven ice shedding, causing rotor imbalances or hitting other blades, the fuselage, or the tail rotor. Computational methods are important for predicting in-flight ice formation and are a vital tool in the design of ice protection systems. The objective of this paper is to present a computationally inexpensive methodology to determine for a helicopter in forward flight, following a period of ice accretion, rotor ice crack locations, shedding times, and potential impact zones.

在飞行过程中，直升机的气动表面上积冰可能导致事故和致命事故。结冰的直升机叶片会导致失速角减小，所需扭矩增加以及脱落的冰块可能造成损坏。尽管转子上的高离心力可以用作自然的除冰机制，但它们也可能导致不均匀的冰块脱落，从而导致转子失衡或撞击其他叶片，机身或尾桨。计算方法对于预测飞行中的冰形成很重要，并且是防冰系统设计中的重要工具。本文的目的是提出一种计算便宜的方法，以确定在一段时期的积冰，旋翼冰裂纹位置，脱落时间和潜在的撞击区域之后，向前飞行的直升机。