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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
Bernard Guering1
10 Jul 2007
TL;DR: In this article, an electrical flight control and ground steering control system for an aircraft that has a main landing gear with a front landing gear is described. But it is not shown how to control the aircraft's attitude relative to the longitudinal axis.
Abstract: Aircraft flight control and ground steering control system This electrical flight control system is intended for an aircraft that has a main landing gear with a front landing gear. It is provided with a handle ( 2 ) that can move around two maneuvering axes ( 4, 6 ) by means of a linkage system ( 8 ), and is movable in rotation around a longitudinal axis substantially perpendicular to the maneuvering axes, means on each of the maneuvering axes for generating a pilot-operated instruction from a movement of the movable handle around one maneuvering axis, and means for generating an instruction in order to act on the orientation of the front landing gear of the aircraft as a function of the angular position of the movable handle ( 2 ) relative to the longitudinal axis.

14 citations

Patent
19 May 1975
TL;DR: In this article, a system for recording aircraft fatigue cycles senses engine starting, engine shutdown, landing gear status, engine reversal and throttle setting and derives therefrom unit and fractional cycles.
Abstract: In an aircraft, a system for recording aircraft fatigue cycles senses engine starting, engine shutdown, landing gear status, engine reversal and throttle setting and derives therefrom unit and fractional cycles. The system includes a first memory responsive to the aforementioned sensors for producing an indication of when the aircraft is in flight and a second memory for producing an indication of when the landing gear are dropped in flight. These memory indications are fed to gates which index the units counter when a takeoff, landing and engine shutdown cycle is completed and which index the fractions counter when a retakeoff without engine shutdown is accomplished. Other gates cause the units counter to be indexed when the engine is restarted in flight. In a multi-engine aircraft, sensors and counters are provided individually for each engine.

14 citations

Proceedings ArticleDOI
09 Sep 2015
TL;DR: In this article, a full-scale nose landing gear (NLG) model featuring the belly fuselage, bay cavity and hydraulic dressing was used for noise reduction in commercial aircraft.
Abstract: The reduction of noise generated by aircraft at take-off and approach is crucial in the design of new commercial aircraft. Landing gear noise is significant contribution to the total noise sources during approach. The noise is generated by the interaction between the non-aerodynamic components of the landing gear and the flow, which leads to turbulence generated noise. This research presents results from the European Clean Sky funded ALLEGRA project. The project investigated a full-scale Nose Landing Gear (NLG) model featuring the belly fuselage, bay cavity and hydraulic dressing. A number of low noise treatments were applied to the NLG model including a ramp door spoiler, a wheel axel wind shield, wheel hub caps and perforated fairings. Over 250 far field sensors were deployed in a number of microphone arrays. Since technologies were tested both in isolation and in combination the additive effects of the technologies can be assessed. This study describes the different techniques used to quantify the contribution of each technology to the global noise reduction. The noise reduction technologies will be assessed as a function of frequency range and through beamforming techniques such as source deletion.Copyright © 2015 by ASME

14 citations

Book ChapterDOI
02 Jun 2014
TL;DR: This paper presents a stepwise formal development of the landing system of an aircraft in Event-B modeling language, and the ProB model checker is used to verify the deadlock freedom and to validate the behaviour requirements by animating the formalized models.
Abstract: This paper presents a stepwise formal development of the landing system of an aircraft. The formal models include the complex behaviour, temporal behaviour and sequence of operations of the landing gear system. The models are formalized in Event-B modeling language, and then the ProB model checker is used to verify the deadlock freedom and to validate the behaviour requirements by animating the formalized models. This case study is considered as a benchmark for techniques and tools dedicated to the verification of behavioural properties of the complex critical systems.

14 citations

Journal ArticleDOI
01 Oct 2018
TL;DR: In this article, uncertain polytopic state space representation is developed by modelling the pneumatic shock absorber dynamics as a mechanical system with non-linear stiffness and damping properties, and a linear matrix inequalities-based robust linear quadratic regulator controller having pole location constraints is designed, since the classical linear quadric regulator control design is dealing with linearized state space models without considering the nonlinearities and uncertainties.
Abstract: This paper deals with the active control of a non-linear active landing gear system equipped with oleo pneumatic shock absorber. Runway induced vibration can cause reduction of pilot’s capability of control the aircraft and results the safety problem before take-off and after landing. Moreover, passenger–crew comfort is adversely affected by vertical vibrations of the fuselage. The active landing gears equipped with oleo pneumatic shock absorber are highly non-linear systems. In this study, uncertain polytopic state space representation is developed by modelling the pneumatic shock absorber dynamics as a mechanical system with non-linear stiffness and damping properties. Then, linear matrix inequalities-based robust linear quadratic regulator controller having pole location constraints is designed, since the classical linear quadratic regulator control design is dealing with linearized state space models without considering the non-linearities and uncertainties. Thereafter, numerical simulation studies ar...

14 citations


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