高超声速飞行器地面颤振评估技术研究  

Study on Ground Flutter Test Method for Hyper-Sonic Vehicle

作　　者：王彬文[1] 宋巧治 陈浩宇 WANG Binwen;SONG Qiaozhi;CHEN Haoyu(Key Laboratory of Aviation Acoustics and Vibration Aviation Science and Technology,Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所航空声学与振动航空科技重点实验室,西安710065

出　　处：《南京航空航天大学学报》2022年第5期899-907,共9页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：针对高超声速飞行器飞行过程中颤振边界变动范围大、试验测试难的问题,本文开展了考虑气动热效应的翼面结构地面颤振试验技术研究。首先基于工程法对结构所受的气动加热进行了分析,在此基础上开展了结构的热颤振特性评估并作为地面颤振试验结果的参考标准。考虑实际飞行中结构温升效应影响,建立了基于多工况点的气动力综合优化降阶算法,确保了整个温升过程的气动力模拟的精度。通过建立基于模糊逻辑比例、积分和微分(Proportional integral derivative,PID)控制的多点协调控制系统,实现了温升过程中时变系统的激振力控制器设计。最终搭建了地面颤振试验系统,按照典型飞行状态对结构的热颤振特性进行了测试,试验测试结果与仿真结果对比相对误差约10%。Due to the large flutter boundary variation and the difficulty of conducting flutter tests on the ground of hyper-sonic vehicles,the thermal flutter test technology of wing surface structure on the ground is studied.Firstly,the aerodynamic heating of the structure is analyzed based on the engineering method,and then the thermal flutter characteristics of the structure are evaluated.Considering the influence of structure temperature rise on the actual flight,an aerodynamic force comprehensive optimization order reduction algorithm based on multi-condition points is established to ensure the accuracy of aerodynamic force simulation during the whole temperature rise process.By establishing a multi-point coordinated control system based on the fuzzy logic proportional integral derivative(PID)control,the excitation force controller of the time-varying system in the process of temperature rise is designed.Finally,the ground flutter test system is built,and the thermal flutter characteristics of the structure are tested according to the typical flight conditions.The relative error between the test results and the simulation results is about 10%.

关 键 词：热颤振 地面颤振试验 气动力模型重构 模糊逻辑控制 

分 类 号：V391.1[航空宇航科学技术]