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对飞机座舱舒适性进行优化控制,可保证机组成员和乘客拥有安全、健康和舒适的环境。进行飞机座舱舒适性控制时,应构造飞机座舱环境优化控制目标函数,并获取飞机座舱环境最优控制参数,完成对飞机座舱舒适性优化控制,但是传统方法通过及孙输入输出变量的隶属度函数参数,对飞机座舱环境进行控制,但是没有得到准确的座舱舒适性控制目标函数和最优控制参数,存在控制响应性差、效果差的问题。提出一种采用模糊理论的飞机座舱舒适性优化控制方法。上述方法融合模糊理论计算座舱压力变化率,根据飞机高度垂直变化率、飞行高度以及座舱压力制度预定座舱压力变化率目标及限制值,组建座舱压力线性化方程,计算出控制系统的输出误差与误差间一阶微分变化,实时更改比例积分微分控制器参数,得到交换器热边流动长度、冷边流动长度和高度之间比例关系,计算出系统熵产与给定初始条件的函数关系,给出飞机座舱环境优化控制目标函数,并利用NSGA-Ⅱ方法计算出飞机座舱环境最优控制参数,完成对飞机座舱舒适性优化控制。仿真结果表明,所提方法对飞机环境控制系统的优化设计响应性强,具有一定指导作用。
Optimal control of the cockpit comfort ensures that crew members and passengers have a safe, healthy and comfortable environment. In order to control the comfort of aircraft cockpit, the objective function of aircraft cockpit environment optimization control should be constructed and the optimal control parameters of cockpit environment should be obtained so as to optimize the cockpit comfort control. However, the membership function of the traditional input and output variables Parameters to control the cockpit environment, but did not get accurate cockpit comfort control objective function and optimal control parameters, there is control of the poor response, the problem of poor performance. This paper presents a method to optimize comfort control of aircraft cockpit based on fuzzy theory. The above method integrates the fuzzy theory to calculate the cabin pressure rate of change, and according to the aircraft vertical rate of change, the flight altitude and the cabin pressure system, the cabin pressure rate of change target and the limit value are established, and the cockpit pressure linearization equation is established to calculate the control system output error and error First-order differential changes, real-time changes in the proportional-integral-derivative controller parameters, get the hot side flow length, cold flow length and height of the proportional relationship between the system entropy yield and the given initial conditions as a function of, given Aircraft cockpit environment optimization control objective function, and using NSGA-Ⅱ method to calculate the optimal cockpit environment control parameters to complete the cockpit comfort optimization control. The simulation results show that the proposed method has a good response to the optimal design of the aircraft environmental control system and has a certain guiding role.