A generic landing gear dynamics model for LaSRS++

2000 ◽  
Author(s):  
W. Ragsdale
Keyword(s):  
Landing Gear ◽  
Dynamics Model ◽  
Gear Dynamics

scholarly journals Uncertainty and Sensitivity Analysis of Bifurcation Loci Characterizing Nonlinear Landing-Gear Dynamics

2018 ◽  
Vol 55 (1) ◽  
pp. 162-172 ◽  
Author(s):  
I. Tartaruga ◽  
J. E. Cooper ◽  
M. H. Lowenberg ◽  
P. Sartor ◽  
Y. Lemmens
Keyword(s):  
Sensitivity Analysis ◽  
Landing Gear ◽  
Gear Dynamics ◽  
Uncertainty And Sensitivity Analysis

scholarly journals Lubrication analysis and sub-surface stress field of an automotive differential hypoid gear pair under dynamic loading

2015 ◽  
Vol 230 (7-8) ◽  
pp. 1183-1197 ◽  
Author(s):  
Leonidas Paouris ◽  
Stephanos Theodossiades ◽  
Miguel De la Cruz ◽  
Homer Rahnejat ◽  
Adam Kidson ◽  
...  
Keyword(s):  
Stress Distribution ◽  
Stress Field ◽  
Film Thickness ◽  
Surface Stress ◽  
Lubricant Film ◽  
Gear Pair ◽  
Hypoid Gear ◽  
Lubricant Film Thickness ◽  
Dynamics Model ◽  
Gear Dynamics

Film thickness and sub-surface stress distribution in a highly loaded automotive differential hypoid gear pair are examined. A 4-Degree of Freedom torsional gear dynamics model, taking into account the torsional stiffness of the pinion and the gear shafts, is used in order to evaluate the contact load, the surface velocities and the contact radii of curvature of the mating teeth during a full meshing cycle. The torsional gear dynamics model takes into account both the geometric non-linearities of the system (backlash non-linearity) as well as the time varying properties (contact radii, meshing stiffness) and the internal excitations caused by geometrical imperfections of the teeth pair (static transmission error). The input torque used for the study of the film thickness and the sub-surface stress distribution corresponds to the region after the main resonance, where no teeth separation occurs. The contact conditions predicted by the gear dynamics are used as the input for the elastohydrodynamic elliptical point contact analysis. The lubricant film thickness, the corresponding pressure and surface traction distributions are obtained quasi-statically using the output load of the dynamic gear pair model. The variation of the induced sub-surface stress field is determined throughout a meshing cycle. Based on the sub-surface reversing orthogonal shear stresses, marginal differences occur when the viscous shear on the conjunctional surfaces are taken into account, which are mainly influenced by the applied pressure distribution. The numerical prediction of lubricant film thickness agrees reasonably well with that predicted using the well-established extrapolated oil film thickness formulae reported in the literature.

Topics in landing gear dynamics research at NASA Langley

1988 ◽  
Vol 25 (1) ◽  
pp. 84-93
Author(s):  
Harvey G. McComb ◽  
John A. Tanner
Keyword(s):  
Landing Gear ◽  
Gear Dynamics

scholarly journals Overview of Landing Gear Dynamics

2001 ◽  
Vol 38 (1) ◽  
pp. 130-137 ◽  
Author(s):  
Jocelyn Pritchard
Keyword(s):  
Landing Gear ◽  
Gear Dynamics

scholarly journals Analysis of Carrier-Based Aircraft Catapult Launching Based on Variable Topology Dynamics

2021 ◽  
Vol 11 (19) ◽  
pp. 9037
Author(s):  
Hu Chen ◽  
Xingbo Fang ◽  
Hong Nie
Keyword(s):  
Dynamic Model ◽  
Pitch Angle ◽  
Solution Method ◽  
Multibody System ◽  
Landing Gear ◽  
Dynamics Model ◽  
Topological Relationships ◽  
Variable Topology ◽  
Free Running ◽  
The Moment

The catapult process of a carrier-based aircraft includes multiple links such as catapult tensioning, separation of the holding rod, dragging and running, separation of the catapult and drag shuttle, and free running. The connection relationships between the front landing gear of the carrier-based aircraft and other related components in each link are different, therefore, it is necessary to adjust the topological relationships of the dynamic model in real time, when solving the catapult dynamics of a carrier-based aircraft. In this paper, a dynamic model of the multibody system of the catapult take-off is established, and a variable topology solution is carried out for the dynamic model by adjusting dynamic augmentation equations; in addition, a dynamic analysis of a carrier-based aircraft catapult and take-off process is carried out. A catapult dynamics model and variable topology solution method were established, which solved the changes at the moment of the restraining rod separation, catapult rod separation, and catapult tackle during the aircraft catapult take-off. After the restraining rod was separated from the front landing gear, the catapult force was transmitted to the rear strut, which instantly increased the load of the rear strut by 238.5 kN. In addition, after the carrier-based aircraft reached the end of the catapult’s stroke, the catapult rod was separated from the catapult tow shuttle then unloaded, and the load of the rear strut was reduced from 486.2 kN to −20.3 kN. Under the protruding effect of the nose gear, the pitch angle of the carrier-based aircraft increased rapidly from −0.93° and reached 0.54° when the carrier-based aircraft rushed out of the deck.

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