摘要
研究了导弹在飞行过程中,为获得不同空域和速域下的最佳气动状态,弹翼后掠角根据飞行环境的不同而变化的控制技术。弹翼后掠角的变化,必然带来弹体动力学模型和控制特性的改变。通过对弹翼后掠角变形机理和动力学特性的研究,建立了变后掠翼导弹的数学模型,然后采用变结构控制理论设计了变后掠翼导弹的控制系统。仿真结果表明,变后掠翼方案能在某些飞行条件下改善导弹的气动特性,提高其机动能力。
The control technique for missile with transformable sweepback is researched. Sweepbackchanges in different environment during the flight of missile in order to obtain optimal pneumatic state. The missile-body kinetics model and control character also alter when the sweepback varies. The principle of sweepback transformation is studied and math model for missile with transformable sweepback is established. Then a control system is designed using variable structure theory. Simulation results indicate that missile with transformable sweepback can improve its aerodynamic characteristic and maneuverability in some condition.
出处
《战术导弹技术》
2013年第2期82-85,103,共5页
Tactical Missile Technology
基金
航空科学基金(2008ZA12001)
关键词
变后掠翼
变形机理
变结构控制
transformable sweepback
the principle of sweep transformation
variable structure theory
