摘要
在飞机试飞定型过程中,为了验证飞机的电源系统、APU电源系统的功能和性能在满载及超载情况下是否满足有关设计要求,需要研制电负载系统,提取并消耗发电机的剩余功率。系统由控制子系统、负载子系统和补水排水子系统3个模块组成。以PLC为下位机,上位机以LabWindows/CVI为开发平台,配合高速数据采集卡组成的控制子系统具有高可靠性、高采集精度、高控制响应能力等特点。实验表明,该系统运行稳定可靠,控制效率高,并在试飞中获得了良好的效果。
In order to verify the function and performance of the aircraft power system,and whether auxiliary power unit power system canmeet the design requirements in the full load and overload condition or not,it is needed to design the electric load system to extract and expend the residual power in the course of flight test and model determination.The system is composed of the control subsystem,load subsystem and filling water drainage subsystem.The lower computer is based on PLC while the PC uses the LabWindows/CVI development platform with the control subsystem consisting of high-speed data acquisition card.It has the features such as high reliability,high collection accuracy,high-control response capability and so on.The experiment proves that this system is steady,trusty and efficient.It has obtained the good effect in the flight test.
出处
《电子技术应用》
北大核心
2014年第11期92-94,共3页
Application of Electronic Technique
