Flight test maneuver design and aerodynamic parameter estimation for single use autonomous air vehicles

2017-01-01
Vefa Yavuzturk, N.
Topbas, Eren
Yazıcıoğlu, Yiğit
In this paper, a maneuver design and aerodynamic parameter estimation procedure is carried out for single use autonomous gliding air vehicles where allowable flight testing time is limited. At first, using the priori aerodynamics of a gliding vehicle, an aerodynamic model has been built and six degree of freedom simulation tool is generated. This priori aerodynamic knowledge is used to design a multi-sine input to excite the system at predetermined flight conditions during flight test. Afterwards, using the real flight test data with the designed inputs executed, a delta difference model, which is sought by utilizing stepwise regression method, has been built and used as a correction model to update the already existing aerodynamic database generated from wind tunnel tests and semi empirical analysis. The results of the study show that, proposed procedure is suitable for estimating delta difference aerodynamic model between the real world and the priori information for the air vehicle type. With the suitable design of input to excite the system on longitudinal plane of motion, it is possible to update the existing aerodynamic database for more reliable simulations, performance and range predictions. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

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Citation Formats
N. Vefa Yavuzturk, E. Topbas, and Y. Yazıcıoğlu, “Flight test maneuver design and aerodynamic parameter estimation for single use autonomous air vehicles,” presented at the AIAA atmospheric flight mechanics conference,( 5 - 09 Haziran 2017), Colorado, Amerika Birleşik Devletler, 2017, Accessed: 00, 2021. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85017357379&origin=inward.