一种临近空间高超声速飞行器翼舵干扰研究  

Research on Wing-Rudder Interference of Near-Space Hypersonic Vehicle

作　　者：邓帆[1] 任怀宇[1] 谢峰[2] 李绪国[2] 梁杰[2] 

机构地区：[1]中国运载火箭技术研究院空间物理重点实验室,北京100076 [2]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000

出　　处：《宇航学报》2013年第6期741-747,共7页Journal of Astronautics

摘　　要：在临近空间区域内飞行的高超声速飞行器对舵面操纵特性提出了严苛的要求,在高空高速条件下主翼对舵效有严重影响。通过风洞试验对带全动舵升力体的高超声速升阻特性进行了研究,发现由于主翼的遮挡效应,负舵偏比同舵偏值的正舵偏对升力体升阻特性影响更明显。数值模拟结果显示在舵偏角从-20°～20°变化过程中,由于主翼与舵面之间气流干扰造成舵面上下压差变化复杂,-12°～2°舵偏产生抬头铰链力矩,其余正负舵偏均产生低头铰链力矩,主翼后缘上表面的分离线随攻角增加逐渐前移,迎风面高压气流通过翼舵之间缝隙向上发展,使得舵上表面再附线后移,翼舵之间均有明显的横向流动。A hypersonic vehicle flying in near-space requires strict control characteristics of aerodynamic rudder.Rudder efficiency is seriously effected by wing at hypersonic speed in near-space,hypersonic aerodynamic characteristics of a lifting-body with the all-movable rudder is studied by using a wind tunnel test.Compared with positive rudder deflection,negative rudder deflection influences the aerodynamic characteristics of the lifting-body obviously because of wing sheltering effect,numerical simulation shows rudder surface pressure distribution varies with airstream interference between wing and rudder,rising moment is produced at-12°~2° rudder deflection while yielding moment is produced at other rudder deflection,the separate line of wing trailing edge moves toward to the warhead as the angle of attack increases,high pressure airstream develops upward through the gap between wing and rudder,causing the attach line of rudder leeward surface moves backward,and lateral flow could also be observed on their surfaces.

关 键 词：临近空间 高超声速飞行器 升力体 翼舵干扰 

分 类 号：V11[航空宇航科学与技术—人机与环境工程]