摘要
对一种利用高空风的风速差控制飞行轨迹的新型低能耗临近空间飞行器,进行了力学分析与配平计算。分析了这种临近空间飞行器的飞行原理,设定了飞行器参数。针对这种飞行器的各组成部分的力学特性不同和与周围空气相对速度差别大的特性,对各组成部分分别进行了受力分析,建立了力学平衡方程组,其中在三维空间里用分段分析的方法对缆绳进行了分析。利用迭代运算的方法,对各组件方程组的集合进行了联立配平计算,绘出了缆绳的空间分布图。计算结果表明,该飞行器利用平流层风速的差异,可以达到轨迹控制的目的,从而极大地节省了能量。
The mechanical analysis and the trimming were performed for a novel near space aircraft which uses the variation in wind speed at high altitude to control its flight path. The flight principle of the novel aircraft was analyzed, and its parameters were determined. Because of the differences in the mechanical characteristics and relative airspeeds of the aircraft components, the forces applied on the components were analyzed separately, and a force balance equation set was established, in which a tether was analyzed in 3D space by using a segmenting analytical method. Finally, for each component, the simultaneous trimming calculation of equation set was performed by using an iterative method, and the spatial profiles of the tether were plotted. The computational results show that the wind speed difference in the stratosphere can be used to control the flight path of aircraft with the result that its energy consumption is significantly decreased.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2008年第8期935-939,共5页
Acta Armamentarii
基金
国家自然科学基金资助项目(90605007)
南京航空航天大学博士研究生创新基金项目(BCXJ06-08)
关键词
流体力学
临近空间飞行器
配平
力学分析
高空风
fluid mechanics
near space aircraft
trimming
mechanical analysis
altitude wind
