Flight Loads Analysis of a Maneuvering Transport Aircraft

Hui Zhang; Jie Li; Qiong Liu

doi:10.4028/www.scientific.net/AMR.1016.460

Paper Titles

Design and Development of Vertical Takeoff and Horizontal Transition Mini Unmanned Aerial Vehicle
p.436

Study on Serial MPPT Electrical Power System Stability for Space Application
p.441

Analysis of Orbital Thermal Environment for Inclined-LEO Small Satellite
p.446

State-Space Rotor Aeroelastic Modeling for Real-Time Helicopter Flight Simulation
p.451

Flight Loads Analysis of a Maneuvering Transport Aircraft
p.460

Effect of Reduced Frequency on Longitudinal Oscillatory Derivatives of an Airfoil Based on Wind Tunnel Data
p.465

SOA-Cloud Computing Based Fast and Scalable Simulation Architecture for Advanced Flight Management System
p.471

Effect of Radiation Induced Charge Neutralization on ELDRS
p.478

Using Low Temperature Irradiation for ELDRS Estimation
p.484

HomeAdvanced Materials ResearchAdvanced Materials Research Vol. 1016Flight Loads Analysis of a Maneuvering Transport...

Flight Loads Analysis of a Maneuvering Transport Aircraft

Abstract:

The paper provides a method applicable for the determination of flight loads for maneuvering aircraft, in which aerodynamic loads are calculated based on doublet lattice method, which contains three primary steps. Firstly, non-dimensional stability and control derivative coefficients are obtained through solving unsteady aerodynamics in subsonic flow based on a doublet lattice technical. These stability and control derivative coefficients are used in second step. Secondly, the simulation of aircraft dynamic maneuvers is completed utilizing fourth order Runge-Kutta method to solve motion equations in different maneuvers to gain response parameters of aircraft due to the motion of control surfaces. Finally, the response results calculated in the second step are introduced to the calculation of aerodynamic loads. Thus, total loads and loads distribution on different components of aircraft are obtained. According to the above method, abrupt pitching maneuvers, rolling maneuvers and yawing maneuvers are investigated respectively.

You might also be interested in these eBooks

View Preview

Info:

Periodical:

Advanced Materials Research (Volume 1016)

Pages:

460-464

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.1016.460

Citation:

Cite this paper

Online since:

August 2014

Authors:

Hui Zhang*, Jie Li, Qiong Liu

Keywords:

Control Surface, Doublet Lattice Method, Dynamic Derivative, Dynamic Maneuvers, Flight Load

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

* - Corresponding Author

References

[1] Jan R. Wright, and Jonathan E. Cooper, Introduction to Aircraft Aeroelasticity and Loads, John Wiley & Sons, Ltd, 2007, 266-269, 279-280.

Google Scholar

[2] Aircraft Design Manual, the 9th Volume: Loads Strength and Stiffness, Bei Jing: Aviation Industry Publishing House, 2001, 28-30.

Google Scholar

[3] Lomax, T.L. Structure Loads Analysis for Commercial Transport Aircraft: Theory and practice, AIAA Education Series, (1996).

Google Scholar

[4] Andreas Schutte, Gunnar Einarsson. Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics, and Structure Mechanics Coupling, Journal of Aircraft, Vol. 46, No. 1, (2009).

DOI: 10.2514/1.31182

Google Scholar

[5] Li Xile, Yang Yong, Numerical Simulation of the Free Rolling Motion of a Delta Wing Configuration with Aileron Deflection, Acta Aeronautica et Astronautica Sinica, Vol. 33, No. 3, (2012).

Google Scholar

[6] Gray, W. L, and Schenk, K.M., A method for Calculating the Subsonic Steady-State Loading on an Airplane Wing of Arbitrary Plan Form and Stiffness, NACA TN 3030, Dec. (1953).

Google Scholar

[7] Albino, E. and Rodden, W.P. "A doublet-lattice Method for Calculating lift distribution on oscillating surfaces in subsonic flows. AIAA Journal, 7(2).

DOI: 10.2514/3.5086

Google Scholar