Flight dynamics and control, vehicle design, optimization and its nume rical method are employed to optimize the ascent trajectories and airbreathing propulsion system performance of two-stage-to-orbit (TSTO) launch vehicles with horizontal takeoff (HTO).

• 基于Sanger的气动外形、推进系统模型、质量模型等，采用飞行力学、最优控制理论及其数值计算等方法，研究了二级入轨水平起飞载机最小起飞质量的上升轨迹，得到了给定任务需求条件下吸气式组合发动机总体性能（推力、燃料消耗率随飞行轨迹的变化规律）要求。