针对助推-滑翔飞行器同时满足最大/最小射程的要求，提出了有效而完备的宽射程范围可调的滑翔制导方法。首先，分析了大气层内基于攻角和倾侧角的气动力制导特点，明确了不同射程气动制导的关键难点。其次，基于总能量控制的思想，实时动态分配速度和高度的控制权限，提出了基于能量混合调节的远程滑翔制导方法，解决了攻角同时控制高度速度引起的欠驱动制导问题。再次，固定攻角剖面将过载、热流密度等约束条件转化为滑翔走廊边界，以阻力加速度和高度反馈为基础，设计了基于阻力加速度-速度剖面的气动减速近程滑翔制导方法，根据倾侧角符号的开关控制将终端方位角约束在横向走廊内。最后，在远/近射程飞行仿真验证中，2种制导方法将不同射程目标飞行器成功引导至相同的末端窗口，系统地解决了高升阻比大气层内滑翔射程管理的制导难题。

To satisfy the requirements of both maximum and minimum ranges for boost-glide vehicles， an effective and complete gliding guidance method with adjustable wide-range coverage is proposed. Firstly， the characteristics of aerodynamic guidance based on angle of attack and bank angle in the atmosphere are analyzed， and the key difficulties of aerodynamic guidance for different ranges are identified. Secondly， based on the idea of total energy control， the control authorities of velocity and altitude are dynamically allocated in real time. A long-range gliding guidance method based on hybrid energy regulation is proposed to solve the underactuated guidance problem caused by simultaneous control of altitude and velocity via angle of attack. Thirdly， with a fixed angle-of-attack profile， constraints such as load factor and heat flux are transformed into gliding corridor boundaries. On the basis of drag acceleration and altitude feedback， a short-range gliding guidance method with aerodynamic deceleration based on the drag acceleration-velocity profile is designed. Terminal azimuth is constrained within the lateral corridor via on-off control of the bank angle sign. Finally， in long-range and short-range flight simulation verifications， the two guidance methods successfully guide the vehicle to the same terminal window under different range targets， systematically solving the guidance problem of range management for high lift-to-drag ratio vehicles in atmospheric gliding.