翼伞空投系统的动力学建模与飞行控制仿真

Dynamic Modeling and Flight Control Simulation of Parafoil Aerial Delivery Systems

针对翼伞系统设计及翼伞归航方案的研究需求,提出翼伞系统动力学建模与仿真分析方法,利用动力学仿真软件ADAMS对翼伞空投系统飞行动力学过程进行了计算。针对翼伞系统精确空投任务,利用分段归航方法规划翼伞系统飞行轨迹并搭建PID控制系统对翼伞系统的飞行轨迹进行控制。结果表明:翼伞系统受到单侧下偏操纵时,影响的是翼伞系统的转弯性能,翼伞的飞行轨迹为螺旋形曲线,并且翼伞系统在下降过程中,其转弯半径保持不变,分段归航方法简单,易于实现,满足翼伞归航对落点精度的要求。

For the need of design and homing project research of parafoil- payload systems, a method of dynamic modeling and simulation is presented. The flight dynamics of parafoil are calculated by the AD- AMS software. According to the precise airdrop of Parafoil System＇s task ,the theory of multiphase design is used to plan the homing trajectory of parafoil system and a pid control system is set up to control the flight path of the parafoil system. The computational results show that, when the parafoil- payload system under the one side edge deflection controlled ,the system＇s turning performance will be affected, the flight path of the system is a spiral curve, and with the height of the system declining, the turning radius remains unchanged, the method of muhiphase design is simple and is easy to implement, to meet the requirements of parafoil homing accuracy.