CAJ | 학술논문

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.
익신조합체구유교고적승조비,가진행교대범위적궤동,이차환가이제고낙점정도、확대재입주랑、강저열류봉치병강저과재.본문채용모선설계방법설계횡절면공제점,차감항천비궤기동력공정계산방법발전료일투가이예고익신조합체비행기종횡향기동력적공정계산방법.제출병건립료익신조합체비행기적우화설계모형병진행료계산,획득료대후략하반익적익신조합체우화방안.대기승조비특성、질심설계、은정성문제、활상비행특성급기동열배경진행료예측화토론.연구표명,대후략하반익적익신조합체방안가이재교소공각시획득교대승조비,종횡향은정차구유교대적활상거리화체공시간,시일충잠재적고초성속궤동방안.
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 externalvehicle 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 correctnessand 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 theheat flux environments are discussed. The present work indicates that a vehiclewith aft-sweeping negative dihedral wings can achieve very high lift-to-dragratio 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.