Modeling of aircraft effects on external store ejection

Date

2019-08-01

Author

Kozak, Mustafa Tugrul
Yıldız, Erdinc Nuri
Yazıcıoğlu, Yiğit
Ciğeroğlu, Ender

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

248
views

0
downloads

Modern fighter aircraft, together with their interceptor roles, are utilized as aerial bomb and long-/short-range missile carriers. Separation of those external stores from aircraft is still a challenge where the external store has to clear the carrier aircraft following the ejection process. Aircraft and store aerodynamics coupled with their individual flight conditions may result in an unsafe ejection where the store may interfere with the carrier aircraft instead of a clear separation. Store ejection is the initial phase of the launching process, which dominates the separation of the store by generating the initial conditions. Any error introduced to the store separation analysis during this phase will propagate to the complete trajectory solution, which is used for determining whether the store separation is safe or not. The objective of this paper is to present a computational methodology that includes not only the store aerodynamics but also the interactions of the store with aircraft rigid body motions and deformations, together with ejector dynamics. In this study, store aerodynamics, aircraft aerodynamics, aircraft aeroelasticity, and pylon elasticity are used to characterize the ejector dynamics for determining the ejection end-of-stroke parameters.

Subject Keywords

Mechanical Engineering, Aerospace Engineering

URI

https://hdl.handle.net/11511/42078

Journal

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING

DOI

https://doi.org/10.1177/0954410018803504

Collections

Department of Mechanical Engineering, Article

Suggestions

OpenMETU
Core

Design and analysis of a mode-switching micro unmanned aerial vehicle Cakici, Ferit; Leblebicioğlu, Mehmet Kemal (SAGE Publications, 2016-12-01) In this study, design and analysis of a mode-switching vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) with level flight capability is considered. The design of the platform includes both multirotor and fixed-wing (FW) conventional airplane structures; therefore named as VTOL-FW. The aircraft is modeled using aerodynamical principles including post-stall conditions. Trim conditions are obtained by solving constrained optimization problems. Linear analysis techniques are utilized for trim ...
Simulation of Rapidly Maneuvering Airfoils with Synthetic Jet Actuators Jee, SolKeun; Lopez Mejia, Omar D.; Moser, Robert D.; Muse, Jonathan A.; Kutay, Ali Türker; Calise, Anthony J. (American Institute of Aeronautics and Astronautics (AIAA), 2013-08-01) Synthetic jet actuators are investigated for rapidly maneuvering airfoils that are regulated by a closed-loop control system. To support active flow-control simulations performed here, the closed-loop system and vehicle dynamics are coupled with computational fluid dynamics. High-frequency sinusoidal pitching simulations with and without synthetic jet actuation indicate that the current synthetic jet actuators provide bidirectional change in aerodynamic forces during rapid maneuvers whose time scales are of...
Mathematical model development of the anti torque system of a notar helicopter Bakır, Hüseyin Murat; Yavrucuk, İlkay; Department of Aerospace Engineering (2008) The anti-torque mechanism of a NOTAR helicopter is a complex system including vertical tail and pressurized tail boom which provides air ejection used for both circulation control around the boom and creating directed jet air at the end of the boom. This thesis targets the modeling of this mechanism and integrating it to a helicopter simulation model. Flight tests are performed on the MD 600N helicopter to verify the results. Finally, the simulation is compared with flight test data.
Navigation and control studies on cruise missiles Ekütekin, Vedat; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2007) A cruise missile is a guided missile that uses a lifting wing and a jet propulsion system to allow sustained flight. Cruise missiles are, in essence, unmanned aircraft and they are generally designed to carry a large conventional or nuclear warhead many hundreds of miles with excellent accuracy. In this study, navigation and control studies on cruise missiles are performed. Due to the variety and complexity of the subsystems of the cruise missiles, the main concern is limited with the navigation system. Nav...
Optimization of Flapping Motion Parameters for Two Airfoils in a Biplane Configuration Kaya, Mustafa; Tuncer, İsmail Hakkı; Jones, Kevin D.; Platzer, Max F. (American Institute of Aeronautics and Astronautics (AIAA), 2009-03-01) Flapping motion parameters of airfoils in a biplane configuration are optimized for maximum thrust and/or propulsive efficiency. Unsteady, viscous flowfields over airfoils flapping in a combined plunge and pitch are computed with a parallel flow solver on moving and deforming overset grids. The amplitudes of the sinusoidal pitch and plunge motions and the phase shift between them are optimized for a range of flapping frequencies. A gradient-based optimization algorithm is implemented in a parallel computing...

Citation Formats

M. T. Kozak, E. N. Yıldız, Y. Yazıcıoğlu, and E. Ciğeroğlu, “Modeling of aircraft effects on external store ejection,” PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, pp. 3612–3626, 2019, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/42078.