水平风洞模型自由飞试验技术研究现状及展望  

Present research status and prospective application of wind-tunnel free-flight test technique

作　　者：孙海生[1] 岑飞[2] 聂博文[2] 刘志涛[2] 

机构地区：[1]西北工业大学,西安710072 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2011年第4期103-108,共6页Journal of Experiments in Fluid Mechanics

摘　　要：介绍国外水平风洞模型自由飞试验技术研究现状,阐述水平风洞模型自由飞试验平台的组成、作用与意义,重点展望该试验技术的应用前景。对试验平台中动力相似模型设计加工技术、动力模拟技术、舵机运动控制技术、模型姿态实时精确测量技术、飞行控制系统设计与集成技术等关键技术问题进行分析,对发展该试验技术具有指导作用。完善水平风洞模型自由飞试验技术,把传统风洞试验拓展到流动-飞行-控制一体化试验,有利于全面研究和充分挖掘飞行器的气动性能与控制性能,对新一代飞机器的发展、新概念新技术的工程应用将起到重要的推动作用。This paper introduces the research status of wind-tunnel free-flight test technique and the constitution of its hardware platform, and discusses its important function and application. Further more, it analyzes several key technical issues, including design of dynamically scaled model, simulation of the thrust vector, control of high bandwidth electro mechanical actuators, real-time measurement, system integration, etc, which may have some meanings in developing the test technique. The consummated wind-tunnel free-flight test technique is able to expand the function of wind tunnel experment from traditional test to an integrative areodynamic/dynamic/ control test technique, which is helpful for studying the aerodynamic and controlling performance of the aircrafts fully,and has a great impact on the development of next generation aircrafts and application of new techniques.

关 键 词：自由飞 风洞试验 飞行控制 系统辨识 过失速机动 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]