一种翼身组合体的气动设计及优化

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。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。本方案在5°攻角时升阻比可达6.5,并给出了飞行器稳定配平的质心布置条件。在纵向稳定配平时,组合体飞行器在偏航及滚转方向均为静/动稳定的。研究表明,本方案可在较小攻角时获得较大升阻比,并具有纵横向稳定性,是高超声速机动的潜在可行方案。

Aerodynamic Design and Optimization for a Wing-Body Vehicle

Wing-body vehicles may have very high lift-to-drag ratio and maneuverability,and high L/D will benefit to increase the landing precision,enlarge the flight corridor,decrease the peak heat flux and the over load.The key issue for high L/D is the design of windward surface,and the leeward surface is more important for the inner volume and enclosed structure.Using Spline Lofting design process,the cross-section control points and the external vehicle geometry are defined.A multiple objectives optimization model is selected to maximum the lift-to-drag ratio and the lift with the restrictions of geometric limits,trimming condition,stability and volume utility.The optimum layout is a vehicle with aft-sweeping negative dihedral wings.The maximum L/D may be as high as near 6.5 for hypersonic at 5 degree angle of attack,and the maximum negative L/D achieves nearly to 6.0 at minus 4 degree.The present work indicates that the Spline Lofting method coupling with configuration optimization is an effective way for the design of a vehicle.The 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,and this wing-body concept is one of the potential choices for hypersonic maneuver,and worth to be investigated further in the future.