Aircraft longitudinal unsteady aerodynamic modeling using indicial function
- Resource Type
- Conference
- Authors
- Zhou, Chijun; Zhu, Jihong; Lei, Humin
- Source
- 2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC) Guidance, Navigation and Control Conference (CGNCC), 2016 IEEE Chinese. :1293-1298 Aug, 2016
- Subject
- Aerospace
Communication, Networking and Broadcast Technologies
Components, Circuits, Devices and Systems
Computing and Processing
Fields, Waves and Electromagnetics
Power, Energy and Industry Applications
Robotics and Control Systems
Signal Processing and Analysis
Aerodynamics
Atmospheric modeling
Data models
Computational modeling
Mathematical model
Aircraft
- Language
To describe the unsteady aerodynamics in high angle-of-attack maneuvers, a novel unsteady model based on indicial function is established for aircraft longitudinal dynamics. This model involves unsteady state expressed by first-order differential equation and squared terms of pitch rate, which effectively reflects the hysteresis characteristics and enhances the nonlinear representation ability. The static and dynamic data of large amplitude forced-oscillation test are employed to identify the parameters. Through using maximum likelihood principle and engineering experiences, the modeling procedure is significantly simplified and the reliance on dynamic derivative test is also removed simultaneously. Strong generalization performance and effectiveness of the developed unsteady model are verified by test data and dynamic derivative simulation results.