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飞机载荷的计算关系到飞机的安全与重量。针对某双座电动飞机的载荷,分别采用ASTM F2245-11中的简化准则以及一般方程求解的方法对载荷进行了计算。结果表明采用一般方程求解的方法计算机翼的机动载荷,在法向方向的载荷比简化方法求解的结果小10%以上,在切向方向上小50%以上。平尾的机动载荷在采用一般方程后的计算结果要比采用简化方法获得的结果小20%以上。平尾的严重载荷主要来自阵风。偏航载荷的计算结果表明,两种方法相差不多。相应地,飞机结构重量可以减轻10%以上。将该重量用于增加电池的重量,可以提高飞机的续航能力28%以上。
Aircraft load calculation relates to the safety and weight of the aircraft. For the load of a two-seater electric aircraft, the load is calculated by adopting the simplified criterion in ASTM F2245-11 and solving the general equation respectively. The results show that using the method of general equation to calculate the mechanical load of wing, the load in the normal direction is more than 10% less than the result of the simplified method and over 50% in the tangential direction. The maneuver load at the end of the tail is more than 20% smaller than that obtained by the simplified method after the general equation is adopted. The serious load of the flat tail comes mainly from gusts. Yaw load calculation results show that the two methods are similar. Accordingly, the weight of the aircraft structure can be reduced by more than 10%. The weight used to increase the weight of the battery can improve the aircraft’s battery life of 28% or more.