基于分布式架构及PAC技术的风洞测试及控制系统设计

Wind tunnel test and control system design based on distributed architecture and PAC technology

摘要:

为准确分析飞行器气动载荷的实际变化规律，降低舱门、舱体类结构部件所受到的冲击载荷作用，设计基于分布式架构及PAC技术的风洞测试及控制系统。在Hadoop集群安装环境中，设置HBase加载模块，借助压电传感器结构与压力控制子回路，实现对加热器供气管路的指向性连接，完成风洞测试控制系统分布式架构集群的建立，解决飞行器舱门及舱体结构的气动载荷获取问题。以驱动性程序作为软件控制基础，将所有待处理的传感器信息及测试数据显示至相同控制界面中，实现对风洞测试控制信号的准确分析，完成基于PAC技术的风洞测试自适应控制研究。仿真实验表明，不断增大压电传感器所承受的气动载荷总量，在风洞测试控制系统的支持下，舱门、舱体所受的实际冲击载荷作用均下降至4000GB左右，能够满足缓解飞行器气动载荷压力的测试初衷。

Abstract:

In order to accurately analyze the actual change law of the aerodynamic load of the aircraft and reduce the impact load of the doors and cabin structural components, a wind tunnel test and control system based on distributed architecture and PAC technology is designed. In the Hadoop cluster installation environment, set up the HBase loading module, use the piezoelectric sensor structure and the pressure control sub-circuit to realize the directional connection to the heater air supply pipeline, complete the establishment of the distributed architecture cluster of the wind tunnel test control system, and solve the aircraft The problem of obtaining aerodynamic load on the door and cabin structure. The driver program is used as the basis for software control, and all the sensor information and test data to be processed are displayed on the same control interface to achieve accurate analysis of the wind tunnel test control signals and complete the wind tunnel test adaptive control research based on PAC technology. Simulation experiments show that, with the increase of the total aerodynamic load sustained by the piezoelectric sensor, with the support of the wind tunnel test control system, the actual impact load on the door and the cabin body is reduced to about 4000GB, which can meet the requirements of mitigating the aircraft. The original intention of the pneumatic load pressure test.