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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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Proceedings ArticleDOI
21 May 2007
TL;DR: In this article, the same landing gear model was previously tested in the original hard-walled configuration of the VT tunnel with the same phased array mounted on the wall of the test section, i.e. near-field position.
Abstract: Experiments were conducted on a 26%-scale high fidelity Boeing 777 main landing gear in the Virginia Tech (VT) Stability Wind Tunnel. This wind-tunnel was recently upgraded to a semi-anechoic facility, which allowed aeroacoustic measurements to be carried out in the far-field and in an environment with significantly less reflections. The model was a very faithful replica of the full-scale landing gear, designed to address the issues associated with low-fidelity models. A 63-element microphone phased array was used to locate the noise source components of the landing gear on the flyover path, both in the near- and far-field. The same landing gear model was previously tested in the original hard-walled configuration of the VT tunnel with the same phased array mounted on the wall of the test section, i.e. near-field position. The new anechoic configuration of the VT wind tunnel offered a unique opportunity to directly compare, using the same gear model and phased array instrumentation, data collected in hard-walled and semi-anechoic test sections. Through these tests some of the limitations associated with hard-walled wind tunnels were discussed. The tests also allowed the noise source components of the landing gear on the flyover path to be identified. It was shown that noise from the landing gear on the flyover path cannot be characterized by only taking phased array measurement straight under the gear.

12 citations

Patent
07 Jun 2007
TL;DR: In this paper, a landing gear with at least two legs capable of retracting into the fuselage via hatches is described. And the landing gear is dual-function, using wheels or skis suspended on legs.
Abstract: A motorised airplane includes a landing gear (17) with at least two legs (21) capable of retracting into the fuselage (11) via hatches (28). A pair of hydrofoils (16) is fitted to the base of the fuselage (11) in conformance with the ailerons used for lift and hydrodynamic stability, directed towards the base like a reverse V shape. The legs (21) of the landing gear (17) are each articulated around the pivot axes (20), fitted onto the hydrofoils (16). The landing gear (17) is dual-function, using wheels (18) or skis (19) suspended on legs (21). Applications: airplane for landing on water, ground and snow.

12 citations

Proceedings ArticleDOI
16 May 2016
TL;DR: In this article, the authors describe the rescheduling of the European Rosetta mission to allow a maximum scientific output, despite the limitations due to unknown communication windows, unknown orientation with respect to the comet surface, the associated risks of any mechanisms activation, the lack of sufficient solar power and limited battery lifetime, is described and elaborated.
Abstract: Philae’s landing on comet 67P/Churyumov–Gerasimenko on 12 November 2014 was one of the main milestones of the European Rosetta mission. The nature of Philae’s mission, to land, operate and survive on comet 67P, required a high degree in autonomy of the on-board software and of the operations scheduling and execution concept. Philae’s baseline operations timeline consisted of predefined and validated blocks of instrument deployments and scientific measurements. These were supported by subsystem activities such as rotation and lifting of the main body relative to the landing gear to allow for specific instrument deployment or in order to cope with the unknown attitude after landing. The nominal descent was followed by an unforeseen rebound at touchdown, lifting Philae again from the comet surface to enter a two-hour phase of uncontrolled flight over the comet surface. Philae’s unknown final landing site, unfavorable attitude with respect to the local surface, bad illumination and lack of anchoring required a complete rescheduling of the baseline timeline. The autonomy offered by the system and the predefined contingency operations were exploited by the operations team to maximize output despite this undesirable state. Implementation of the rescheduling to allow a maximum scientific output, despite the limitations due to unknown communication windows, unknown orientation with respect to the comet surface, the associated risks of any mechanisms activation, the lack of sufficient solar power and limited battery lifetime, is described and elaborated.

12 citations

Patent
03 Mar 1947
TL;DR: In this article, the principal object of the landing gear improvements was to improve the facility of the airplane for making landings across the wind, and a more particular object was to provide...
Abstract: This invention relates generally to airplane under carriages or landing gear and has for its principal object to provide improvements in the landing gear for improving the facility of the airplane for making landings across the wind. A more particular object of the present invention is to provide...

12 citations

Patent
Hong Nie, Yin Yin, Xiaohui Wei, Rui Fan, Bin Mi 
20 Apr 2011
TL;DR: In this paper, an airplane landing gear with a deflected airplane wheel retraction jack is described, which consists of a landing gear main leg outer cylinder (3), a buffer piston rod (15), an upper torque arm (16), a lower torque arm, a hub (13), and a tyre (14).
Abstract: The invention discloses an airplane landing gear with a deflected airplane wheel retraction jack, belonging to the technical field of airplane landing gears. The airplane landing gear with a deflected airplane wheel retraction jack mainly comprises the integral structure of a landing gear main leg, which is composed of a landing gear main leg outer cylinder (3), a buffer piston rod (15), an upper torque arm (16), a lower torque arm (17), a hub (13) and a tyre (14). The airplane landing gear also comprises the retraction rod system of the landing gear, which is composed of an upper locking stay bar (9), a lower locking stay bar (10), an upper side stay bar (7), a lower side stay bar (8), a lug (6), a first lantern ring (4) and a second lantern ring (5); and a retraction actuator cylinder (S) and an unlocking actuator cylinder (J) form the retraction power plant of the landing gear. The invention realizes the oblique and front retraction mode of the landing gear; meanwhile, the retraction mechanism also realizes the mode that the tyre rotates around the axis of the buffer outer cylinder, and thus the tyre rotates to the horizontal position when the landing gear is retracted in an airfoil, thereby solving the problem of large occupied space of the lading gear tyre.

12 citations


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