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.
Flight loads analysis of a maneuvering transport aircraft
2014-01-01
Advanced Materials Research, ISSN 1022-6680, 2014, Vol. 1016
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
DDC: | 629 |
Flight Loads Analysis of a Maneuvering Transport Aircraft
Trans Tech Publications | 2014
|Flight Loads Analysis of a Maneuvering Transport Aircraft
British Library Conference Proceedings | 2014
|Horizontal Tail Loads in Maneuvering Flight
NTIS | 1950
|Horizontal tail loads in maneuvering flight
Engineering Index Backfile | 1950
|Measurement of maneuvering loads in flight
Engineering Index Backfile | 1945
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