摘要
气囊缓冲主动控制技术是提高气囊缓冲性能的一项技术,旨在排气阶段通过控制排气口面积的大小来控制囊内气体的压强以保持恒定,从而使得这一过程中的过载得以较为均匀分布。文章通过建立动力学模型和控制系统模型,对气囊缓冲主动控制技术进行了仿真研究。在建立气囊缓冲动力学模型时,没有采用通常的等熵方法来近似求解排气阶段的囊内气体温度,而是考虑了囊内气体的能量变化,并采用龙哥库塔法求解出了囊内气体温度、压强以及缓冲过载等重要变量,将气囊缓冲动力学模型在Simulink软件中写入为自定义函数,建立气囊排气控制系统模型,进行仿真。通过仿真分析了驱动机构响应时间与着陆速度对缓冲效果的影响,并结合主动控制气囊的工作特点尝试给出了合适的排气控制执行机构。文章对气囊排气主动控制技术进行了有益的探索研究。
As a method to promote airbag cushioning effect, active airbag buffer control technology can change vent area during venting process, so as to keep pressure in the airbag and overload of the loading stable.This paper builds a kinetic model and control model of active buffer control airbag, and then studies active airbag buffer control technology by simulation. While building the mathematic model of this process, this paper doesn't use isentronic method to approximately solve temperature of air in airbag, but with consideration about the energy change of the air in airbag, uses Runge-Kutta interation to obtain solutions of some useful variables, such as temperature and pressure of air in airbag and overload. Then, it puts the mathematic model of cushioning process into User-Defined Functions of Simulink, and builds the model of vent control system. Finally, the paper makes simulation to analyse the influences of driving mechanism's response time and initial velocity error, and tries to find a suitable mechanism to control the vent, based on characteristics of active vent control airbags. All above make an investigation of the technology of active airbag vent control.
出处
《航天返回与遥感》
北大核心
2016年第3期39-47,共9页
Spacecraft Recovery & Remote Sensing
基金
国家重大科技专项工程
关键词
气囊
排气主动控制
驱动机构
仿真
回收着陆
airbag
active vent control
driving mechanism
simulation
landing