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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。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。
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. In this paper, a cross-sectional control point is designed by using the die-line design method, and a set of engineering calculation methods that can predict the vertical and horizontal aerodynamic forces of the wing-body combination aircraft is 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 lift-drag ratio, centroid design, stability problems, gliding flight characteristics and aerodynamic thermal environment were predicted and discussed. The research shows that the scheme of wing-body combination with aft-swept-back wing can obtain a large lift-drag ratio at small angle of attack, stable in the longitudinal and transverse directions, and has a large gliding distance and lag time. It is a potential hypersonic Motorized program.