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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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Proceedings ArticleDOI
21 May 2007
TL;DR: In this article, a Toboggan-shaped main landing gear noise reduction fairing was designed for full-scale flight evaluation on a B777-300ER aircraft in the QTD 2 program.
Abstract: The advances in aircraft engine noise reduction and the increasing demand for quieter aircraft has led noise research to focus more attention on airframe noise. Landing gears and high lift systems have been known to significantly contribute to the total aircraft noise at approach idle conditions, especially in cases where high by-pass ratio engines are used, when noise from the engines is low enough that it could be considered comparable or lower than the noise from the airframe. Landing gears in service on today’s aircraft were not designed with noise impact in mind and contain a myriad of possible noise generating features. Today’s landing gear designer is challenged to consider noise among many other factors when designing efficient aircraft landing gear systems. It is a challenge further complicated if noise reduction solutions are required for retro-fit applications. Much of the experimental noise research conducted on landing system noise has centered around the understanding of noise generating mechanisms and evaluation of noise reduction concepts in model-scale environments such as wind tunnel tests. These experiments have provided valuable insight into landing gear noise sources. However, little effort has been made to integrate noise reduction research with full-scale landing gear design and evaluate noise reduction potential in a full-scale flight environment. The work conducted under the Quiet Technology Demonstrator 2 (QTD2) program marks a first step in the successful integration of noise research with landing gear design with the focus being to design, implement and evaluate noise reduction solutions in a full-scale flight environment. This paper discusses the design and analysis of a ‘toboggan’ shaped main landing gear noise reduction fairing for full-scale flight evaluation on a B777-300ER aircraft in the QTD 2 program. The fairing was selected for flight evaluation after a series of model-scale wind tunnel acoustic experiments were conducted in conjunction with full-scale feasibility studies. The fairing design addressed issues such as gear kinematics and stowing, brake cooling, ground operations and noise reduction potential. The design was supported by static stress analysis and flutter analysis to ensure that the fairing was flight worthy.

13 citations

Proceedings ArticleDOI
01 Oct 2017
TL;DR: In this paper, a mathematical model of an articulated robotic landing gear that adapts to uneven ground conditions is considered, consisting of a planar landing gear composed of two legs connected by a base and a skid at each end.
Abstract: This paper proposes a method to investigate into helicopter landing on uneven terrain by means of using a scaled articulated robotic landing gear. A mathematical model of an articulated robotic landing gear that adapts to uneven ground conditions is considered. The model consists of a planar landing gear composed of two legs connected by a base and a skid at each end. Each skid has two degrees of freedom with PID joint controllers to provide stability while landing. A combination of Lagrange and Newton-Euler techniques is used to model the system dynamics. This work also includes a model of the ground interaction, a thrust controller and a level controller to maintain stability while landing. Experimental results with a laboratory-build scaled prototype are included and compared with the simulations.

13 citations

Proceedings ArticleDOI
08 Jan 2007
TL;DR: In this paper, the use of belly-flaps to enhance the lift and pitching moment during takeoff and landing of a blended-wing-body (BWB) was proposed.
Abstract: Since the beginning of flight with the Wright brothers, the shape of an airplane hasn’t really changed. An airplane has always been a fuselage with wings, a tail, engines and a landing gear. A couple of people, like the Horton brothers or Northrop, tried in the mid 30’s to completely change the airplane configuration with an innovative design of a tailless allwing airplane. However that concept was not consummated until the late 80’s when the B-2, the only flying wing to enter production to date, illustrated its benefits. Since then the airplane industry has attempted to adopt this design for future passenger airplanes because of its increased efficiency over a conventional tailed airplane. But there are some major challenges that must be resolved before one will see a Blended-Wing-Body (BWB) takeoff at a major International airport. One of the issues is its difficulty to rotate due to the missing tail. This paper presents a possible solution, namely the use of belly-flaps to enhance the lift and pitching moment during takeoff and landing. Wind tunnel tests on a generic BWBmodel have shown an increase up to 35% of the lift-off CL and an increase of 10% in pitching moment using belly-flaps mounted on the underside of the model.

13 citations

Patent
14 Oct 2011
TL;DR: In this paper, a system and method for monitoring loads applied to aircraft landing gear structure is presented, which includes the step of interrogating at least one sensor positioned proximate the landing gear by way of data acquisition circuitry to yield strain data.
Abstract: A system and method for monitoring loads applied to aircraft landing gear structure. The method includes the step of interrogating at least one sensor positioned proximate the landing gear structure by way of data acquisition circuitry to yield strain data. The method further includes the step of instructing the data acquisition circuitry with respect to a sampling rate and data resolution for interrogation.

13 citations

Patent
James Morris1, Antonio Colosimo1
21 Jul 2014
TL;DR: In this paper, a method for controlling the speed of an aircraft during an autonomous pushback manoeuvre without a pushback tractor is described, where the aircraft's speed is controlled by applying a torque to at least one landing gear wheel of the aircraft.
Abstract: The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.

13 citations


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