微小型变体飞行器建模与控制系统设计  

Modeling and Control System Designing of a Morphing Micro Aircraft

作　　者：金磊[1] 董晨[1] 王正杰[1] 

机构地区：[1]北京理工大学机电学院,北京100081

出　　处：《北京理工大学学报》2014年第8期796-800,830,共6页Transactions of Beijing Institute of Technology

基　　金：国家自然科学基金资助项目(11102019)

摘　　要：研究了机翼可后掠变形的微小型变体飞行器动力学建模和飞行控制系统设计方法,通过状态点选取、气动参数计算和数据拟合插值,建立了变体飞行器的动力学模型,针对模型的特点,提出了一种以参数空间方法为基础的变体飞行器飞行控制系统设计方法,通过计算机辅助算法,设计了纵向通道控制系统,仿真结果表明,所设计的公共固定增益控制器能够使得变体飞行器在不同飞行阶段始终具备要求的动态特性,具有可行性和工程实用性.A new method was presented for the dynamic modeling and control system designing of a morphing micro aircraft with variable sweep. Through operating point selecting, aerodynamic calculation and data fitting, dynamic model of the morphing aircraft was established. According to the characteristics of dynamic model, a flight control system design method was put forward based on parameter space approach for morphing aircraft. With computer aided design method, a longitudinal control system was designed. The simulation results show that the designed public fixed-gain controller can make the morphing aircraft have required dynamic characteristics in different flight stages, and show its feasibility and practicability.

关 键 词：变体飞行器 动力学建模 参数空间方法 飞行控制 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]