Flight testing of the X-31A post-stall experimental aircraft started in Oct. 1990. By the end of 1992, the X-31A flight regime had been expanded to 70 deg angle of attack, and a significant number of flight tests with dynamic post-stall maneuvers had been performed. Within the international 'Combined X-31A Flight Test Team,' DLR (the German Aerospace Research Establishment) contributes its system identification experience and capabilities to the determination of aerodynamic parameters and thrust vector control effectiveness from flight test data. After a brief description of the applied hardware and software, this paper presents recent results from flight test data compatibility checking. The identification models used for the separated evaluation of longitudinal and lateral-directional motion are introduced. This emphasizes the model reductions necessary for X-31A high angle of attack applications. Identification results of selected aerodynamic parameters are shown in comparison to wind-tunnel predictions. The identification of the X-31A thrust vector control effectiveness is addressed, and preliminary results are presented as well. An overview of future identification activities with respect to nonlinear/instationary effects in the high angle of attack regime is given.
X-31A System Identification Applied to Post-Stall Flight: Aerodynamics and Thrust Vectoring
1994
12 pages
Report
No indication
English
X-31A System Identification Applied to Post-Stall Flight - Aerodynamics & Thrust Vectoring
British Library Conference Proceedings | 1994
|Aerodynamics of thrust vectoring
NTRS | 1989
|Aerodynamics of Thrust Vectoring
NTIS | 1989
|