一种翼身组合体的气动概念设计

翼身组合体具有较高的升阻比,可进行较大范围的机动,而且还可以提高落点精度、扩大再入走廊、降低热流峰值并降低过载.本文采用模线设计方法设计横截面控制点,借鉴航天飞机气动力工程计算方法发展了一套可以预估翼身组合体飞行器纵横向气动力的工程计算方法.提出并建立了翼身组合体飞行器的优化设计模型并进行了计算,获得了带后掠下反翼的翼身组合体优化方案.对其升阻比特性、质心设计、稳定性问题、滑翔飞行特性及气动热环境进行了预测和讨论.研究表明,带后掠下反翼的翼身组合体方案可以在较小攻角时获得较大升阻比,纵横向稳定且具有较大的滑翔距离和滞空时间,是一种潜在的高超声速机动方案.

Aerodynamic configuration conceptual design for a wing-body vehicle

Wing-body vehicles may have very high lift-to-drag ratio and maneuverability,and the key issue for high L/D is the design of windward surface.Using Spline Lofting design process,the cross-section control points and the external vehicle geometry are defined,and the vehicle shape can be constructed rapidly,conveniently and accurately.A multiple objectives configuration optimization model for a wing-body is defined to maximum the lift-to-drag ratio,and the optimum layout is a vehicle with aft-sweeping negative dihedral wings.The correctness and the effectiveness corresponding engineering estimation method are validated by the comparison with ADDB and CFD result.The L/D performance,the location of the center of gravity,the lateral direction stability,the trajectory and the heat flux environments are discussed.The present work indicates that a vehicle with aft-sweeping negative dihedral wings can achieve very high lift-to-drag ratio at relative very small angle of attack,together with good stability,long gliding distance and loiter time,and this wing-body concept is worth to be investigated further as one of the potential choices for hypersonic maneuverable transporter.