吸气式组合动力飞行器爬升轨迹设计方法研究 -- 西北工业大学学报,2015,33(1):104-109
论文:2015,Vol:33,Issue(1):104-109
引用本文:
贾晓娟, 闫晓东. 吸气式组合动力飞行器爬升轨迹设计方法研究[J]. 西北工业大学学报
Jia Xiaojuan, Yan Xiaodong. Ascent Trajectory Design Method for Air-Breathing Powered Propulsion System[J]. Northwestern polytechnical university

吸气式组合动力飞行器爬升轨迹设计方法研究
贾晓娟1, 闫晓东1,2
1. 西北工业大学航天学院, 陕西西安 710072;
2. 航天飞行动力学技术重点实验室, 陕西西安 710072
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。
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   
Ascent Trajectory Design Method for Air-Breathing Powered Propulsion System
Jia Xiaojuan1, Yan Xiaodong1,2
1. College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Science and Technology on Aerospace Flight Dynamics Laboratory, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
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.
Key words:    angle of attack    computer simulation    damping    density(specific gravity)    drag coefficient    electronic guidance systems    feedback linearization    functions    lift    Mach number    natural frequencies    tracking(position)    velocity    air-breathing vehicle    ascent phase    trajectory design   
收稿日期: 2014-04-29     修回日期:
DOI:
基金项目: 航天技术支撑基金(2013-HT-XGD-014)资助
通讯作者:     Email:
作者简介: 贾晓娟(1989-),女,西北工业大学硕士研究生,主要从事空天飞行器动力学与制导控制研究。
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