带控制舵飞行器机动特性研究  

A study on conic maneuverability of a biconic vehicle with flaps

作　　者：唐伟[1] 马强[1] 张勇[1] 李为吉[2] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000 [2]西北工业大学,陕西西安710072

出　　处：《空气动力学学报》2006年第1期80-84,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(项目号:10072074)

摘　　要：研究带控制舵双锥外形再入飞行器的机动特性。文章首先利用“部件叠加法”,通过对干扰因子和等效攻角等概念的引入,发展了一套可以计算该类飞行器纵横向气动力的工程计算方法。其次,文章通过大量计算,分析研究了该类飞行器的配平特性。最后,利用气动力与六自由度弹道耦合方法,研究分析了此类飞行器实现射面拉起/下压机动飞行及空间锥形机动的舵面控制规律。The maneuverability of a biconic vehicle with cruciform flaps has been studied. This kind of vehicle is one of the typical missile concepts for hypersonic maneuvering, and its tactical movement includes draw back and/or push down in reentry section plane, and space conic movement, simultaneously it will fly at high angle of attack, high angle of sideslip, together with high angle of flaps, the aerodynamic non-linearity, the disturbance between body and flaps will be generated and unavoidable, the control laws and the coherent effect between pitch, yaw and roll are very complicated. Using the concepts of interferential factors and effective angles of attack, an engineering component built-up method has been developed to predict the aerodynamic characteristics of this vehicle during hypersonic reentry flight. The comparison of the results with that of Euler equation numerical simulation shown that the accuracy of the presented method is sufficient for the conceptual design, and the correctness and effectiveness of the method are validated. Then the trimming efficiency of the vehicle has been analyzed. The vehicle has a high control efficiency, and because of the unstable design of the main body, the actually angle of attack of the flaps is much smaller than that of the body, which is of math beneficial to the heat protection and structural design. The angle of sideslip will diminish the trimming efficiency, and will induce the rolling moment unavoidably, thus the rolling control is essential for the vehicle. Finally, coupling aerodynamics prediction method and 6-D trajectory equation, the flaps control mles with squeeze model condition and corresponding flight performance have been investigated and simulated numerically for the pull-up/pull-down movement and conic maneuver. The results show that the rolling control may be one of the vital challenges for the successful design of this vehicle.

关 键 词：部件叠加法 锥形机动 控制舵 再入飞行器 

分 类 号：O357.1[理学—流体力学]