摘要
太阳能无人机有高空、长航时、巡航速度低、铺设太阳能电池板、大展弦比等特点,这对其结构要求更加严格.本文根据气动载荷分析了主梁的受载情况,根据翼梁受载对机翼主梁进行等强度初步设计,并在此基础上,采用多目标粒子群优化方法对主梁的上、下边缘的复合材料层进行优化,并与传统翼梁结构进行比较.优化结果表明,优化后的梁可以满足翼梁的设计要求.
Solar UAV has the characteristics of high altitude, long voyage, low cruising speed, laying solar panels,and high aspect ratio, which is more stringent for its structural requirements. In this paper, the load of main beam was analyzed according to aerodynamic load, and the equal strength initial design of wing beam was carried out according to the loading of wing beam. Based on the initial design of the wing beam, the multi-objective particle swarm optimi.zation was used to optimize the composite layer of the upper and lower edges of the main beam, and was compared with the traditional wing beam structure. The optimization results showed that the optimized beam could meet the de.sign requirements of the wing beam.
作者
张利国
王冠
许萌
ZHANG Liguo 1,2, WANG Guan 2 ,XU Meng 3(1.Liaoning Ruixiang General Aviation Co.Ltd.,Shenyang Liaoning 110136;2.Shenyang Aerospace University,ShenyangLiaoning 110136;3.Liaoning General Aviation Academy,Shenyang Liaoning 11013)
出处
《河南科技》
2018年第10期106-109,共4页
Henan Science and Technology
关键词
太阳能无人机
复合材料
铺层优化
翼梁
solar UAV；composite material；stacking-sequence optimization；wing spar
