带控制舵钝双锥削面体的气动特性研究  

Aerodynamic analysis for a reentry vehicle with slice-flaps

作　　者：唐伟[1] 桂业伟[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2009年第1期93-96,共4页Acta Aerodynamica Sinica

摘　　要：提出了带控制舵的钝双锥削面体飞行器气动布局概念,计算分析了其压心特性、升阻比特性、配平特性及操纵效率问题,同时还研究了纵向稳定配平条件下的航向安定性问题及动稳定性问题,并与带配平翼的钝双锥削面体外形进行了比较。两类外形的典型空间机动动作不同,操纵方式也各不相同:控制舵削面体具有更大的配平攻角变化范围和操纵效率,较小的舵面等效攻角有利于舵面防热及结构设计,而且俯仰配平时的航向安定性及动稳定性较好;而配平翼钝双锥削面体可采用迎风及背风进行俯仰控制,结合侧翼的扩张及迎风翼的差动实现空间"Z"形机动。The design of a maneuverable hypersonic reentry vehicle configuration is an extremely challenging process which is still an art than a science. A blended blunt biconie vehicle with slice and four triangular flaps combining the configurations of AMaRV and Perxing Ⅱ is proposed. An engineering model based on Embedded Newtonian Flow Theory and three dimensional separation flow correction is developed to estimate the aerodynamic characteristics of this vehicle. The characteristics of center of pressure, lift-to-drag ratio, trimming angles of attack and control effectiveness are predicted and analyzed, the directional stability and the dynamic stability under the condition of pitch trimming are investigated, and the comparisons with that of vehicle with slice-aileron are presented simultaneously. The typical space maneuvering movement of the vehicle with slice-flaps is conic movement, the pair of pitch control flaps and the pair of yaw flaps deflects alter- nately to trim the vehicle longitudinally and laterally at different angles of attack and angle of sideslip, while the total angles of attack keep constantly. The vehicle has a higher trimming efficiency and wider range of trimming angles of attack, the unstable main body design makes the actual equivalent angle of attack of the flap much smaller which is of mach beneficial to the heat protection and structural design, and the directional stability and the dynamic stability under the condition of pitch trimming are within rationality. The vehicle with slice-ailerons adopts windward control or leeward control technique to achieve a typical ＂Z＂ form space maneuvering, and a differential control model is needed to control its rolling movement. The present work indicates that the concept of biconic vehicle with slice-flaps is one of the potential choices for hypersonic maneuver, and further investigation is prospected.

关 键 词：控制舵 配平翼 配平效率 航向安定性 动稳定性 机动飞行器 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]