关于大型运输机机翼翼载设计方法的探讨

Discussion on Wing Load Design Method of Large Transport Aircraft

飞机的空机重量可以分为系统重量和结构重量,其中结构重量是由飞机的载荷水平来决定的,而按照国家军用标准的说法,基本飞行设计重量和最大机动过载系数基本决定了一架飞机的载荷水平。当基本飞行设计重量和最大机动过载系数确定后,飞机的载荷水平基本就确定了,翼载也就基本确定了,对于其他部件而言,机身主要承受增压载荷和惯性载荷,以及尾翼传递的载荷,受机身装载和尾翼传递载荷的影响较大。对于尾翼的载荷,由于对操纵舵面的运动非常敏感,可以在合理可行的范围内通过限制舵面的偏转来限制尾翼的载荷水平。但是对于一架大展弦比、平直翼的大型运输机而言,飞机的许多部件的严重载荷设计情况出现在突风情况。因此,在确定飞机的基本飞行设计重量和最大机动过载系数的时候,不应该忽视突风载荷的影响。

The empty weight of the aircraft can be divided into system weight and structural weight;in which the structural weight is determined by the load level of the aircraft;and according to the national military standard,the basic flight design weight and the maximum maneuver overload factor basically determine the load level of an aircraft.When the basic flight design weight and the maximum maneuver overload factor are determined.,the aircraft load level and wing load are basically determined,for other components,the fuselage mainly bears the pressurization load and inertia load,as well as the load transmitted by the tail,which is greatly affected by the fuselage loading and the load transmitted by the tail;for the load of the tail,because it is very sensitive to the movement of the control surface,the load level of the tail can be limited by limiting the deflection of the control surface to a reasonable and feasible extent.But for a large transport plane with large aspect ratio and flat wings,the severe load design of many parts of the aircraft occurs in the case of sudden wind,therefore;when determining the basic flight design weight and maximum maneuver overload factor of the aircraft,the effect of sudden wind load should not be ignored.