摘要
提出了一种水平起飞吸气式组合动力飞行器的爬升轨迹设计方法。将爬升轨迹分为起飞爬升段、等动压段和等热流段,分别考虑过载、动压、热流约束,在高度-速度剖面内给出了轨迹设计的约束边界,以及3个飞行段的爬升轨迹设计方法,并利用反馈线性化方法设计了参考轨迹的跟踪制导律。仿真结果表明,参考轨迹能够满足各种飞行约束,可准确跟踪,为吸气式组合动力飞行器主动段的爬升轨迹提供一种可行的设计方法。
Air-breathing combined cycle propulsion is a promising thruster for aerospace vehicle in the future. Since trajectory has an important influence on the performance of the propulsion, reasonable trajectory design is necessary. Supposing that the aerospace vehicle takes off horizontally and powered by air-breathing combined cycle propulsion, this paper divides the ascent climbing trajectory into three phases： take-off climbing phase, constant dynamic pressure phase and constant heating rate phase. Considering the constraints of load, dynamic pressure and heating rate, we put forward respectively trajectory design methods for the three phases. Finally, the tracking law of the reference trajectory is derived with the feedback linearization method. The simulation results and their analysis show preliminarily that the designed reference trajectory is able to satisfy the constraints and to do tracking well.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2015年第1期104-109,共6页
Journal of Northwestern Polytechnical University
基金
航天技术支撑基金(2013-HT-XGD-014)资助
关键词
攻角
计算机仿真
阻尼
密度
阻力系数
电子制导系统
反馈线性化
函数
升力
马赫数
固有频率
跟踪(位置)
速度
吸气式飞行器
主动段
轨迹设计
angle of attack, computer simulation, damping, density（ specific gravity）, drag coefficient, electronicguidance systems, feedback linearization, functions, lift, Mach number, natural frequencies,tracking（position）, velocity
air-breathing vehicle, ascent phase, trajectory design
