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

Date

2017-01-01

Author

Vefa Yavuzturk, N.
Topbas, Eren
Yazıcıoğlu, Yiğit

Metadata

Show full item record

Item Usage Stats

178
views

0
downloads

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.

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85017357379&origin=inward
https://hdl.handle.net/11511/87984

Conference Name

AIAA atmospheric flight mechanics conference,( 5 - 09 Haziran 2017)

Collections

Department of Mechanical Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Aerodynamic parameter estimation using flight test data Kutluay, Ümit; Platin, Bülent Emre; Mahmutyazıcıoğlu, Gökmen; Department of Mechanical Engineering (2011) This doctoral study aims to develop a methodology for use in determining aerodynamic models and parameters from actual flight test data for different types of autonomous flight vehicles. The stepwise regression method and equation error method are utilized for the aerodynamic model identification and parameter estimation. A closed loop aerodynamic parameter estimation approach is also applied in this study which can be used to fine tune the model parameters. Genetic algorithm is used as the optimization ker...
Flight control system design of an uncommon quadrotor aerial vehicle Baskın, Mehmet; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2021-9-01) In this thesis, design of a flight control system for an uncommon quadrotor aerial vehicle is discussed. This aerial vehicle consists of two counter-rotating big rotors on longitudinal axis to increase the lift capacity and flight endurance, and two counter-rotating small tilt rotors on lateral axis to stabilize the attitude. Firstly, full nonlinear dynamic model of this vehicle is obtained by using Newton-Euler formulation. Later, derived approximate linear model around hover is statically decoupled to sim...
Aerodynamic parameter estimation of a missile in closed loop control and validation with flight data Aydın, Güneş; Kutay, Ali Türker; Department of Aerospace Engineering (2012) Aerodynamic parameter estimation from closed loop data has been developed as another research area since control and stability augmentation systems have been mandatory for aircrafts. This thesis focuses on aerodynamic parameter estimation of an air to ground missile from closed loop data using separate surface excitations. A design procedure is proposed for designing separate surface excitations. The effect of excitations signals to the system is also analyzed by examining autopilot disturbance rejection pe...
Mathematical Modeling of the NOTAR Antitorque System for Flight Simulation Yavrucuk, İlkay; Uzol, Oğuz (2013-04-01) In this paper, a mathematical model of a helicopter NO TAil Rotor (NOTAR) antitorque system is developed for real-time flight simulations. The model consists of the circulation control tail boom, direct jet thruster, and the vertical stabilizers. The airflow inside the tail boom is modeled by dividing the flow into aerodynamic control volumes. The model features a bladeelement-type approach for modeling the mass flow through the axial fan blades as well as aerodynamic mass and momentum conservation calculat...
Aerodynamic modeling and parameter estimation of a quadrotor helicopter Kaya, Derya; Kutay, Ali Türker (2014-01-01) This study focuses on aerodynamic modeling of a quadrotor helicopter and the estimation of the model parameters in wind tunnel tests for hover, vertical climb, and forward flight conditions. The motion of a quadrotor is mainly affected by the aerodynamic forces and moments generated by rotors. Accurate calculation of rotor loads is essential for high fidelity simulation of a quadrotor. Momentum and blade element theories are used to obtain expressions for rotor forces and moments for a traveling vehicle. Th...

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.