2.4m跨声速风洞虚拟飞行试验支撑装置研制

R&D of the virtual-flight test support based on the 2.4 m transonic wind tunnel

风洞虚拟飞行试验是开展气动/飞行力学一体化研究的有效手段,也是连接地面模拟与飞行试验的桥梁和纽带,为了实现风洞虚拟飞行试验真实模拟飞行器机动运动的要求,需要研制一种模型支撑机构研究风洞虚拟飞行试验技术。文中以2.4 m跨声速风洞虚拟飞行试验为背景,设计了风洞虚拟飞行试验支撑装置,并对其进行了力学建模,根据得到的数学模型对结构静力学特性和动力学特性进行了仿真分析,同时也利用CFD技术对其进行了支撑干扰分析。仿真分析结果和试验结果均表明风洞虚拟飞行试验支撑装置设计合理,具有较好的强度特性、刚度特性和较小的支撑干扰,满足风洞虚拟飞行试验研究要求,为该类试验的风洞支撑问题提供了一个可行的技术方案。

The virtual-flight test based on the wind tunnel is effective for the study on the integrated pneumatic and flight mechanics,and it links the ground-based simulation and the flight test.In order to accurately simulate the motions of aircraft in the wind-tunnel virtual-flight test,a model-support device is developed for technical exploration.In this article,a virtual-flight test support based on the 2.4 m transonic wind tunnel is presented and modeled mechanically;based on the mathematical model,the simulation analysis is conducted on its characteristics of static mechanics and dynamics.In addition,the analysis is made on the support interference by means of the CFD technology.The simulation and test results show that the wind-tunnel support,characterized with strong strength,high rigidity and minor support interference,meets the requirements of the wind-tunnel virtual-flight test,and provides a feasible technical scheme for those issues related to wind-tunnel supports.