宽速域气动设计是水平起降空天飞机研制的瓶颈问题之一。空天飞机在全包线飞行过程中经历极宽的速域和极广的空域，不同速域下的飞行动压存在量级上的差异，飞行器匹配自身重力所需的升力面大小存在显著不同，使得气动布局设计过程中升力匹配设计存在很大挑战。在优先满足低速起飞升力设计要求时，高速飞行的设计升力状态会显著偏离其最大升阻比状态，导致可用升阻比不足。首先，结合空天飞机宽域飞行环境，分析了水平起降空天飞机宽速域升力匹配设计需求。其次，发展了一种考虑升力匹配的全局气动优化设计方法，并针对Sanger空天飞机载机的机翼开展了考虑升力匹配的机翼平面及剖面外形气动优化设计研究，优化机翼在满足起飞升力约束的前提下，在超声速和高超声速状态下的可用升阻比分别提升了20.0%和8.1%，显著缓解了高速可用升阻比不足的难题。最后，开展了机体干扰下考虑升力匹配的机翼平面外形优化设计，验证了发展的方法在全机构型下的适用性。

Wide-speed-range aerodynamic design remains one of the critical bottlenecks in the development of horizontal takeoff and landing spaceplanes. These vehicles operate across an exceptionally broad flight envelope, encountering significant variations in both dynamic pressure and atmospheric conditions. The disparity in required lift across low-speed and high-speed regimes leads to conflicting demands on the lifting surface sizing, introducing considerable challenges in achieving an aerodynamically balanced configuration throughout the entire mission profile. Specifically, satisfying the lift require-ments for low-speed takeoff typically results in excessive lifting surface area at high-speed conditions, causing a marked deviation from the optimal lift-to-drag ratio and limiting the vehicle’s aerodynamic efficiency. To address this challenge, this study first analyzes the lift matching requirements associated with wide-speed-range operations of horizontal takeoff spaceplanes. A global aerodynamic optimization framework is then developed, explicitly incorporating lift matching con-straints into the configuration design process. The proposed methodology is applied to the wing planform and airfoil shape optimization of the Sanger spaceplane carrier aircraft. Under the constraint of meeting low-speed takeoff lift requirements, the optimized wing achieves an improvement of 20.0% in the available lift-to-drag ratio under supersonic conditions and 8.1% under hypersonic conditions, effectively mitigating the aerodynamic efficiency degradation at high speeds. Fur-thermore, the optimization framework is extended to account for fuselage-wing aerodynamic interference effects, and its applicability to full-vehicle configuration aerodynamic optimization is demonstrated.