应用简化准则与应用一般方程计算载荷的对比研究  

Comparison of loading calculation results between simplified design load criteria and general equations

作　　者：李淑萍[1,2] 岳海龙[1] 高峰 

机构地区：[1]沈阳航空航天大学航空航天工程学部(院),沈阳110136 [2]辽宁通用航空研究院设计与制造部,沈阳110136

出　　处：《沈阳航空航天大学学报》2017年第2期33-37,共5页Journal of Shenyang Aerospace University

摘　　要：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。Loading calculation of airplane involves its safety and weight. The loading of electric airplane with some double-seat was calculated using both simplified design load criteria（ ASTM F2245 - 11） and gen-eral equations. The results show the normal load of wing resulting from general equations decreased by more than 10% comparing the simplified criteria,the tangential load reduced by more than 50% ,but loading of horizontal wing decreased by more than 20%. The overload of horizontal wing came from gust mainly. The results from loading calculation of yaw indicated the two calculation methods were similar. Consequently, the structure weight of airplane decreased by more than 10%. If the reduced weight is substituted by batteries, the flight endurance of airplane will increase by more than 28 %.

关 键 词：载荷 一般方程 简化准则 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]