小型无人机尾翼对称机动飞行载荷计算  

Flight Maneuver Loads Calculation of the Small UAV's Tail

作　　者：刘斌[1] 王和平[1] 王建培[1] 

机构地区：[1]西北工业大学无人机所,陕西西安710072

出　　处：《飞行力学》2003年第3期52-55,共4页Flight Dynamics

摘　　要：在《军用飞机强度和刚度规范》指导下,结合无人机的特点,计算了小型无人机尾翼对称机动飞行载荷,同时与按《飞机强度规范》(试用本)计算的结果进行了比较。结果表明,按后一规范的计算结果偏于保守。此外还初步讨论了《飞机强度规范》(试用本)在计算小型无人机尾翼对称机动飞行载荷中的适用性问题。The flight maneuver loads design and calculation of the small UAV's tail were studied in the paper. First of all, on the basis of Military Aircraft Strength and Rigidity Specification, the symmetrical flight maneuver loads of the small UAV's tail were given for the conditions of the steady pitching maneuver and the abrupt pitching maneuver. Secondly, based on the Airplane Strength Specification (1975) and the flight features of the small UAV, the flight maneuver loads of the small UAV's tail were calculated. By understanding the two strength specifications and analyzing the results calculated by the two specifications, a preliminary conclusion could be drawn that the specification of 1975 was suitable for the flight maneuver loads calculation of the small UAV's tail and the results calculated by the specifications were conservative. 

关 键 词：小型无人驾驶飞机 尾翼 对称机动飞行载荷 计算 飞机强度 

分 类 号：V215.9[航空宇航科学与技术—航空宇航推进理论与工程]