飞机大迎角非定常气动力建模研究进展  

A review of unsteady aerodynamic modeling of aircrafts at high angles of attack

作　　者：汪清[1,2] 钱炜祺[1,2] 丁娣[1,2] 

机构地区：[1]中国空气动力研究与发展中心空气动力国家重点实验室,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《航空学报》2016年第8期2331-2347,共17页Acta Aeronautica et Astronautica Sinica

摘　　要：准确建立非定常气动力数学模型,是飞机大迎角飞行控制律设计、飞行动力学分析和飞行仿真的基础与前提。鉴于此,对大迎角非定常气动力建模研究进展,包括数学建模方法和人工智能建模方法两类进行了系统综述。其中:数学类建模方法是以对非定常流动现象和机理认识为基础的,主要有气动导数模型、非线性阶跃响应模型、状态空间模型、微分方程模型、非线性阶跃响应与状态空间混合模型以及迎角速率模型等;人工智能方法回避了复杂流动机理,属于黑箱非线性系统建模,主要有神经网络模型、模糊逻辑模型和支持向量机模型等。对于每种气动力模型,阐述了其建模思路和方法,给出了典型应用情况,并对其特点和局限性作了简要评述。最后,指出了当前大迎角非定常气动力建模研究工作存在的问题和未来研究方向。Accurate unsteady aerodynamic models are the basis of control law design,flight dynamics analysis,and flight simulation of aircraft at high angles of attack.The advances in high angle-of-attack unsteady aerodynamic modeling are reviewed systematically.The developed modeling methods can be classed into two categories：mathematic methods and artificial intelligent methods.The mathematic models include those in the form of aerodynamic derivatives,nonlinear indicial response,internal state-space,differential equations,hybrid representation of nonlinear indicial response and internal statespace,flow incidence rate,etc.They are based on the understanding of unsteady flow phenomenon and mechanism.The intelligent methods,including fuzzy logic,neural networks,and support vector machines,avoid the complicated flow mechanism and are suitable to black-box system modeling especially.For individual aerodynamic models,their modeling ideas and methods and typical applications are described,and brief comments on their distinguishing features and limitations are put forward as well.Finally,the problems in current unsteady aerodynamic modeling researches and the future development directions are indicated.

关 键 词：大迎角 失速/过失速 非定常气动力 气动力模型 风洞试验 飞行试验 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]