摘要
针对变形飞行器变形机理及协调控制问题,从分析变形需求入手,以巡航导弹变后掠变展长为例,基于Datcom计算气动数据分析了变后掠及变展长对飞行器气动特性的影响,以此揭示了飞行器变形机理。在此基础上,结合巡航导弹作战使用特点,阐述了可变形巡航导弹气动外形寻优原则和方法。最后,提出分级递阶的变形协调控制体系结构,并对比分析了变形/控制开环独立和闭环一体两种协调控制机制的特点。
According to morphing mechanism and coordination control problem of morphing aircraft, analysis of the requirments of morphing was developed. The cruise missile which can change wingspan and sweepback angle was taken for example. In order to reveal the morphing mechanism, the morphing influnce on the aerodynamic characteristics was analyzed, based on the aerodynamic data calculated by using Datcom. Combining with the using characteristics of cruise missile, the principle and method of aerodynamic shape optimization were expounded. Finally, the hierarchical classification of morphing coordination control system structure was put forward, and two kinds of mechanism of coordination control were paralled, one is morphing/control open-loop method, the other is morphing/control close-loop integrative method.
出处
《战术导弹技术》
北大核心
2016年第2期10-15,共6页
Tactical Missile Technology
关键词
变形飞行器
变形机理
气动寻优
协调控制
morphing aircraft
morphing theory
aerodynamic shape optimization
coordination control
