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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.


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Patent
30 Sep 2014
TL;DR: In this article, the Center of Gravity of an aircraft is determined from the combined measured main landing gear pressures in relation to a nose landing gear strut pressure measurements, or combined main legged axle deflection sensor in relation with a nose legged sensor, without any determination of the aircraft weight.
Abstract: A method which determines aircraft Center of Gravity independent of measuring the aircraft weight. The method is used in monitoring, measuring and computing the Center of Gravity of an aircraft utilizing pressurized, telescopic landing gear struts with axles. Pressure sensors are mounted in relation to each of the landing gear struts to monitor, measure and record aircraft landing gear strut loads by way of pressure. Axle deflection sensors are mounted in relation to each of the landing gear axles to monitor, measure and record aircraft landing gear axle loads by way of deflection. Nose landing gear strut pressure and corresponding values from axle deflection sensors may be adjusted in correlation to the reduced size of the nose landing gear, as compared to the size of the main landing gear, allowing aircraft Center of Gravity to be determined from the combined measured main landing gear pressures in relation to a nose landing gear strut pressure measurements, or combined main landing gear axle deflection sensor in relation to a nose landing gear axle deflection sensor; without any determination of the aircraft weight.

11 citations

Patent
05 Jun 1980
TL;DR: A landing gear for ultralight aircraft includes a main landing gear assembly disposed in a position relative to the longitudinal axis of the aircraft to permit either tail wheel type landing or tricycle landing operations as mentioned in this paper.
Abstract: A landing gear for ultralight aircraft includes a main landing gear assembly disposed in a position relative to the longitudinal axis of the aircraft to permit either tail wheel type landing or tricycle landing operations with the assembly including an arched axle wherein the arch provides a spring for the landing gear as well as provides clearance to enable foot launching of the aircraft. A nose wheel strut assembly is linked to and extends forward of the main wheel landing gear assembly and includes a resilient tension link member.

11 citations

Patent
11 Feb 1992
TL;DR: In this article, an elastic leg consisting of a damping chamber and of a sliding rod equipped with a stub axle, as well as an operating jack was used for a helicopter to retractable landing gear.
Abstract: The invention relates to a retractable landing gear, especially for a helicopter, including an elastic leg consisting of a damping chamber and of a sliding rod equipped with a stub axle, as well as an operating jack. In accordance with the invention, an additional energy-absorption device (150), with force threshold, is built into the operating jack (108), in such a way that the said jack applies a predetermined torque tending to keep the leg of the gear in a substantially vertical position, while allowing the retraction of the said gear with a controlled force in the event of an emergency landing; moreover, the stub axle (106) is offset with respect to the axis of the elastic leg in such a way that a vertical force exerted on the gear leg (101) generates a torque tending to retract the said gear, the latter torque, however, remaining less than the said predetermined holding torque in the normal landing situation.

11 citations

Proceedings ArticleDOI
16 Jun 2014
TL;DR: In this article, a high-fidelity 18% scale Gulfstream aircraft model in landing configuration with the main landing gear deployed was used to measure instantaneous velocities in the immediate vicinity of the landing gear and its wake and near the inboard tip of the flap.
Abstract: Off-surface flow measurements of a high-fidelity 18% scale Gulfstream aircraft model in landing configuration with the main landing gear deployed are presented. Particle Image Velocimetry (PIV) and Laser Velocimetry (LV) were used to measure instantaneous velocities in the immediate vicinity of the main landing gear and its wake and near the inboard tip of the flap. These measurements were made during the third entry of a series of tests conducted in the NASA Langley Research Center (LaRC) 14- by 22-Foot Subsonic Tunnel (14 x 22) to obtain a comprehensive set of aeroacoustic measurements consisting of both aerodynamic and acoustic data. The majority of the off-body measurements were obtained at a freestream Mach number of 0.2, angle of attack of 3 degrees, and flap deflection angle of 39 degrees with the landing gear on. A limited amount of data was acquired with the landing gear off. LV was used to measure the velocity field in two planes upstream of the landing gear and to measure two velocity profiles in the landing gear wake. Stereo and 2-D PIV were used to measure the velocity field over a region extending from upstream of the landing gear to downstream of the flap trailing edge. Using a special traverse system installed under the tunnel floor, the velocity field was measured at 92 locations to obtain a comprehensive picture of the pertinent flow features and characteristics. The results clearly show distinct structures in the wake that can be associated with specific components on the landing gear and give insight into how the wake is entrained by the vortex at the inboard tip of the flap.

11 citations

Patent
29 Mar 2011
TL;DR: In this paper, a wheel design for an aircraft landing gear wheel that is configured to maximize the space available within the wheel well to support a motor driver assembly that drives the aircraft wheel when the aircraft is on the ground is presented.
Abstract: A wheel design is provided for an aircraft landing gear wheel that is configured to maximize the space available within a landing gear wheel well to support a motor driver assembly that drives the aircraft wheel when the aircraft is on the ground. The wheel includes inboard and outboard support walls that are spaced apart a selected distance along the wheel axle so that the motor driver assembly components are substantially completely contained within the wheel space defined by the support walls. The preferred motor driver assembly includes an electric motor and a gear and clutch assembly operatively connected to the wheel to drive the wheel and move the aircraft on the ground. The wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle.

11 citations


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