Topic
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 published on a yearly basis
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04 Jan 2016
TL;DR: AFLoNext as mentioned in this paper is a project of four years duration, funded by the European Commission within the Seventh Framework Programme, with the main objectives of proving and maturing highly promising flow features.
Abstract: AFLoNext is a project of four years duration, funded by the European Commission within the Seventh Framework Programme. The project’s main objectives are proving and maturing highly promising flow ...
9 citations
15 Dec 2010
TL;DR: In this article, the authors developed noise prediction models and add-on noise reduction fairings to protect complex gear structures from high-speed inflow, providing the only limited noise reduction potential.
Abstract: Noise originating from flow around aircraft landing gears is one of the major components of aircraft noise in the approach phase. Owing to the complex structure of landing gears, they represent a cluster of aerodynamic noise sources that are difficult to deal with for the purpose of noise reduction. Moreover, a variety of safety and operational constraints must be considered. Landing gear noise intensity increases proportionally to the 6th power of flow velocity while the sound frequencies increase linearly with the velocity. Through wind tunnel tests on full-scale gears, typical noise characteristics (spectrum and directivity) and the noisiest gear components can be identified. On the basis of this knowledge, both noise prediction models and add-on noise reduction fairings can be developed. Such fairings, to protect complex gear structures from high-speed inflow, provide the only limited noise reduction potential. Much higher noise benefits can be achieved for new landing gears of future aircraft, when aeroacoustic constraints are introduced as an additional design criterion, thus enabling a low-noise design of both the overall gear architecture and of individual gear components. On top of that, both passive and active flow control means can be applied locally to gear components for further noise reduction.
Keywords:
airframe noise;
landing gear noise;
add-on gear fairings;
low-noise gear design;
flow control
9 citations
Patent•
22 Dec 2003
TL;DR: In this article, an aircraft that uses a shape memory alloy to extend or retract landing gear is described. But the shape memory is not included in the design of the aircraft, and it is not shown how to use it in a fixed position.
Abstract: Aircraft that use a shape memory alloy to extend or retract landing gear are provided. The present invention includes aircraft that contain a first retractable landing gear and a first shape memory alloy. The first retractable landing gear in the aircraft may be moveable from a first position to a second position while the first shape memory alloy may be changeable from a first configuration to a second configuration, the first shape memory alloy being in physical communication with the first retractable landing gear. Aircraft in accord with the present invention may also include a lock positioned to secure the first retractable landing gear in a retracted position and/or a second retractable landing gear coupled to the aircraft. This second retractable landing gear may also be moveable from a first position to a second position.
9 citations
Patent•
21 Dec 2011TL;DR: A landing gear vibration absorber of a helicopter with a landing gear comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids to a helicopter's fuselage is described in this paper.
Abstract: The invention is related to a landing gear vibration absorber (1) of a helicopter (2) with a landing gear (3) comprising a pair of skids (4, 5) and at least one cross tube (6, 7) for mounting the skids (4, 5) to a helicopter's fuselage (8). At least one spring-mass system (10, 20, 24) is mounted to the landing gear (3). Said at least one spring-mass system (10, 20, 24) is tuned to the helicopter's main excitation frequency and said at least one spring-mass system (10, 20, 24) being located at or near at least one antinode of the landing gear (3). The invention is related as well to a method of operating a landing gear vibration absorber (1) of a helicopter (2).
9 citations
02 Jun 2014
TL;DR: An ASM model is presented for the case study given as a challenge for the ABZ’14 conference, which specifies the digital part of a landing gear system for aircraft, to make the formal model well understandable for humans.
Abstract: We present an ASM model for the case study given as a challenge for the ABZ’14 conference, which specifies the digital part of a landing gear system for aircraft. We strove to make the formal model well understandable for humans. We note inconsistencies, ambiguities and gaps in the case study and summarise our experiences during modelling and the proof of safety properties.
9 citations