基于物理解算的民用飞机气动参数辨识方法研究  

Research on Aerodynamic Parameters Identification of Civil Aircraft Based on Physical Calculation

作　　者：吴戴鹏 王磊 黎先平[1] 欧阳一方[1] Wu Daipeng;Wang Lei;Li Xianping;Ouyang Yifang(COMAC Shanghai Aircraft Design Research Institution, Shanghai 201206, China)

机构地区：[1]中国商飞上海飞机设计研究院,上海201206

出　　处：《航空科学技术》2018年第4期37-41,共5页Aeronautical Science & Technology

摘　　要：传统的风洞试验与理论计算无法满足建立高精确飞机飞行动力学模型的需求,有必要通过试飞后的气动参数辨识来修正其飞行动力学模型。以极大似然法为代表的传统动态激励气动参数辨识法极大地依赖于激励信号设计、辨识算法等,存在较大的不确定性。本文提出了一种基于物理解算的方法,利用飞机不同飞行条件下的配平数据,从物理机理出发,针对气动静导数条理进行一一解算,并形成了物理解算法的辨识流程和方案。这一方法可为后续动导数的动态激励辨识减少大量未知参数,从而提高了整个气动模型的修正精度和效率。研究结果表明这一方法具有较高的可靠性和准确性。Traditional wind tunnel tests or theoretical calculations cannot met the demand of establishing a high-precision aircraft flight dynamics model.It is necessary to correct the aerodynamic model through the aerodynamic parameter identification after the flight test.The traditional dynamic excitation aerodynamic parameters identification method,represented by maximum likelihood method greatly depends on the excitation signal design and identification algorithm,and has great uncertainly.In this paper,a method based on physical solution was proposed.This method used trim data under different flight conditions.It calculated the aerodynamic static derivatives in order according to the physical mechanism.The specific technical process and scheme for physical identification were formulated.This method reduces lots of unknown parameters for dynamic excitation method.It will improve the efficiency and accuracy.The results show that this method has high reliability and accuracy.

关 键 词：参数辨识 物理解算 气动静导数 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]