高超声速变后掠翼战术导弹概念设计与弹道优化

Morphing Swept Wing Tactical Missile Conceptual Design and Optimization Trajectory of Hypersonic Vehicle

针对日益复杂的战场环境对飞行器性能的需求,为了进一步拓宽现有飞行器的性能包线,研究了一种基于剪切变后掠翼的概念飞行器。分析了这类变后掠翼飞行器不同后掠角的升阻比特性,提出了保持最优气动特性滑翔飞行的攻角和后掠角变化的一般规律。采用Radau伪谱法(RPM)分别对可变后掠翼飞行器与固定翼飞行器的弹道以最大射程为目标进行优化,结果表明剪切变后掠翼战术导弹射程最优弹道具有明显的优势,且后掠角、攻角的优化结果与气动特性分析得到的规律一致。

To meet the demand of the ever-increasing complexity of battlefield environment for the characteristics of aircraft and to extend performance envelop of the existing tactical missiles,a variable-sweep mode of shearing variable-sweep airfoil was designed. At first,the lift-to-drag ratio characteristics of this kind of variable sweep vehicle was anlyzed,and the impact mechanism of variable-sweep wings on aerodynamic characteristics is explained. A general law that change the attack angle and sweep angle at the same time is presented to give consideration to the aerodynamic characteristics. Finally,the Radau Pseudospectral Method（RPM） is adopted to achieve the optimization trajectory of two vehicle with variable-sweep wings and fixed wings respectively. The result show that the variable-sweep wings tactical missile has significant extended-range effect and the optimization result of the attack angle and sweep angle satisfied that given laws.