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Landing gear

About: Landing gear is a research topic. Over the lifetime, 3403 publications have been published within this topic receiving 25370 citations. The topic is also known as: landing gear & gear.


Papers
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Patent
23 Jun 1975
TL;DR: An articulated, retractible landing gear for helicopters and the like includes a three member drag brace assembly having a retraction brace pivotally connected to the helicopter fuselage at its inboard end and to an upper drag brace at its outboard end as discussed by the authors.
Abstract: An articulated, retractible landing gear for helicopters and the like includes a three member drag brace assembly having a retraction brace pivotally connected to the helicopter fuselage at its inboard end and to an upper drag brace at its outboard end, with the latter pivotal connection being along the articulation axis of the landing gear, the upper brace being pivotally connected at its other end to a lower brace which in turn is connected to the oleo strut of the landing gear by a universal joint, the pivotal connection between the upper and lower braces in the extended position of the landing gear being on an axis normal to both the drag brace center line and the articulation axis.

17 citations

Patent
18 Jul 1942
TL;DR: In the conventional type of airplane of current design retractable landing gears of various designs are commonly employed and are well known In some of the airplanes, principally amphibions, the landing gear is adapted as discussed by the authors.
Abstract: The present invention relates to retractable landing gears for airplanes In the conventional type of airplane of current design retractable landing gears of various designs are commonly employed and are well known In some of the airplanes, principally amphibions, the landing gear is adapted

17 citations

Patent
08 Aug 1939
TL;DR: In this paper, the authors proposed a landing gear for aircraft of the flying boat kind, i.e., one having a buoyant hull or fuselage, which can be used as an amphibian, being capable of landing on land.
Abstract: This invention relates to alighting gear for aircraft and is particularly concerned with aircraft of the flying boat kind, i. e., one having a buoyant hull or fuselage. The invention seeks to provide landing gear so that the aircraft may be used as an amphibian, being capable of landing on...

17 citations

Patent
Paul De Ruffray1, Rodolphe Morel1
14 Nov 2006
TL;DR: A reduced-volume casing for a landing gear including a chassis for fixing and taking up loads, to which the landing gear is exposed and an envelope-type structure arranged on the chassis for taking up pressurization forces is described in this paper.
Abstract: A reduced-volume casing for a landing gear including a chassis for fixing and taking up loads, to which the landing gear is exposed and an envelope-type structure arranged on the chassis for taking up pressurization forces. The chassis can include, in particular, a frame which is even to the output opening of the landing gear and is provided with beams used for receiving means for maintaining the fastening bearings of the gear and also including polygons which are used for receiving the fastening bearings of the gear manoeuvring strut and are fixed to the beams, wherein the beams and polygons form a lattice structure.

16 citations

Journal ArticleDOI
TL;DR: In this paper, a model of a three-dimensional dual-sidestay landing gear mechanism is presented and employed in an investigation of the sensitivity of the downlocking mechanism to attachment point deflections.
Abstract: A model of a three-dimensional dual-sidestay landing gear mechanism is presented and employed in an investigation of the sensitivity of the downlocking mechanism to attachment point deflections. A motivation for this study is the desire to understand the underlying nonlinear behavior, which may prevent a dual-sidestay landing gear from downlocking under certain conditions. The model formulates the mechanism as a set of steady-state constraint equations. Solutions to these equations are then continued numerically in state and parameter space, providing all state parameter dependencies within the model from a single computation. The capability of this analysis approach is demonstrated with an investigation into the effects of the aft sidestay angle on retraction actuator loads. It was found that the retraction loads are not significantly affected by the sidestay plane angle, but the landing gear’s ability to be retracted fully is impeded at certain sidestay plane angles. This result is attributed to the lan...

16 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202353
2022135
2021101
2020116
2019199
2018190