Aerodynamic Design Analysis Of Missiles With Strake Configurations At Supersonic Mach Numbers

Date

2015-09-10

Author

Usta, Engin
Kıvanç, Arslan
Tuncer, İsmail Hakkı

Metadata

Show full item record

Item Usage Stats

357
views

0
downloads

In this study a neural network based method is developed for the prediction of separation characteristics of external store weapons carried under aircraft wings. The method is based on an artificial neural network trained by high fidelity unsteady flow solutions. The unsteady flow solutions as the store separates from the carriage and the resulting six degrees of freedom motion of the store are computed conditions by a commercial flow solver for various flight conditions. The trajectory of the store and the unsteady aerodynamic loads acting on it are used to train a neural network. A simulation is used for evaluating the 6 degrees of freedom motion of a store based on the aerodynamic loads predicted by the neural network as a function of the flight conditions and the instantaneous position of the store. The efficiency and the accuracy of the method developed are determined by comparing the predicted and computed trajectories of the store for flight conditions not used in the training set. It is shown that the method developed can successfully predict the store separation characteristics.

URI

http://aiac.ae.metu.edu.tr/paper.php?No=AIAC-2015-104
https://hdl.handle.net/11511/84818
http://aiac.ae.metu.edu.tr/paper.php?No=AIAC-2015-104

Conference Name

8th Ankara International Aerospace Conference (10-12 Eylül 2015)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

MODELING OF STORE SEPARATION BEHAVIOR BASED ON A NEURAL NETWORK AND UNSTEADY FLOW SOLUTIONS Erinç, Erdoğan; Tuncer, İsmail Hakkı (null; 2015-09-10) In this study a neural network based method is developed for the prediction of separation characteristics of external store weapons carried under aircraft wings. The method is based on an artificial neural network trained by high fidelity unsteady flow solutions. The unsteady flow solutions as the store separates from the carriage and the resulting six degrees of freedom motion of the store are computed conditions by a commercial flow solver for various flight conditions. The trajectory of the store and the...
Nonlinear aeroservoelastic modelling and analysis of aircraft with control surface freeplay Yurtsever, Utku; Şahin, Melin; Kayran, Altan; Department of Aerospace Engineering (2022-11-24) In this study, nonlinear aeroservoelastic analysis of aircraft with control surface freeplay is performed using the fictitious mass approach. For the demonstration of the nonlinear aeroservoelastic analysis methodology, an available very light aircraft (VLA) design configuration is selected. The aeroelastic model of the aircraft is obtained by combining the structural and aerodynamic models of the aircraft, which are prepared by the finite element modelling and analysis tool MSC.Patran/MSC.Nastran and the a...
Trajectory tracking of a quadrotor unmanned aerial vehicle (UAV) via attitude and position control Suiçmez, Emre Can; Kutay, Ali Türker; Department of Aerospace Engineering (2014) In this thesis, trajectory tracking of a quadrotor UAV is obtained by controlling attitude and position of the quadrotor simultaneously. Two independent control methods are used to track desired trajectories accurately. One of these methods is a nonlinear control approach called as "backstepping control". The other method is a more unique optimal control approach called as "Linear Quadratic Tracking(LQT)". In addition, fixed-gain LQR controller which is widely used in literature is also used for comparison ...
ESTIMATION OF AERODYNAMIC LOADS OF A PROPELLER THROUGH IMPROVED BLADE ELEMENT AND MOMENTUM THEORY AND PROPELLER DESIGN OPTIMIZATION KAYA, DERYA; Kutay, Ali Türker; Department of Aerospace Engineering (2021-6) This study focuses on accurate prediction of total forces and moments acting on a propeller in all flight conditions through Blade Element and Momentum Theory (BEMT) and design optimization of a UAV propeller. Under various flight conditions such as hover, vertical climb, and forward flight, propeller generates different aerodynamic loads in different free-stream velocities, propeller disk angles of attack, and propeller’s angular speeds. For this reason, it is important to have a mathematical model that p...
Aerodynamic design and performance analyses of grid fin in supersonic flow using design of experiments and computational fluid dynamics Dinçer, Erdem; Sezer Uzol, Nilay; Department of Aerospace Engineering (2022-2) Control surfaces are key components of missile aerodynamic performance that can create the necessary forces and moments to make maneuvers. Grid fins are unconventional control surfaces used for aerodynamic control of missiles. In this thesis, parametric design of grid fin is performed in terms of aerodynamic performance using Design of Experiments and Computational Fluid Dynamics. The 3-D, steady-state, compressible, viscous flow CFD simulations are performed for the complex grid fin geometries in supersoni...

Citation Formats

E. Usta, A. Kıvanç, and İ. H. Tuncer, “Aerodynamic Design Analysis Of Missiles With Strake Configurations At Supersonic Mach Numbers,” Ankara, Türkiye, 2015, p. 1, Accessed: 00, 2021. [Online]. Available: http://aiac.ae.metu.edu.tr/paper.php?No=AIAC-2015-104.