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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。
The wing-body combination has a high lift-drag ratio for a wide range of maneuvers and improves placement accuracy, re-entry corridors, peak heat flow and overload reduction. A cross-sectional control point was designed by using the mold design method. A set of engineering calculation methods that could predict the vertical and horizontal aerodynamic forces of the wing-body combination aircraft was developed based on the aerospace engineering calculation method of the space shuttle. The optimal design model of the wing-body combined aircraft was proposed and established. The optimization scheme of the wing-body combination with the backward-swept-back wing was obtained. The proposed scheme achieves a lift-drag ratio of 6.5 at 5 ° attack angle and gives the mass-center placement conditions for a stable and balanced aircraft. In the case of vertical trim, the combined aircraft is both statically / dynamically stable in both yaw and roll directions. The results show that the proposed scheme can obtain a large lift-drag ratio at a small angle of attack and has vertical and horizontal stability, which is a potential solution to hypersonic maneuver.