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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11 May 2009
50 citations
10 May 2004
50 citations
Patent•
29 Jul 1985
TL;DR: In this article, a drive motor system is coupled to the landing gear wheels of an air craft via a free wheeling clutch assembly, which is used to accelerate the aircraft to a landing position.
Abstract: A drive motor system is coupled to the landing gear wheels of an air craft via a free wheeling clutch assembly. The drive motor system is energized when the landing gear is extended preparatory for landing either manually or automatically. The drive motor system is controlled to rotate the wheels to have the linear velocity of the periphery of a wheel the same as the ground speed of the aircraft at touchdown. A touchdown sensor stops the drive motor system at touchdown causing the clutch assembly to disengage the wheels when the rpm of the wheel is greater than the drive system rpm. An automatic control system is described.
50 citations
04 Jun 2012
TL;DR: In this paper, a numerical procedure for the prediction of aircraft noise certi cation metrics starting from the aircraft trajectory is described, which is applied to the nose landing gear of a Gulfstream business jet.
Abstract: This paper describes a numerical procedure for the prediction of aircraft noise certi cation metrics starting from the aircraft trajectory. The procedure is applied to the nose landing gear of a Gulfstream business jet. The numerical core of the procedure is a hybrid aeroacoustic method based on a lattice Boltzmann ow simulation and a Ffowcs-Williams & Hawkings noise propagation computation. The hybrid method is initially validated by computing the noise generated by a geometrically simpli ed model of the same landing gear installed on a at plate and comparing wall pressure and fareld noise spectra with wind-tunnel measurements. The same numerical method and a similar discretized model are then employed to compute the unsteady ow eld past the real landing gear deployed under the aircraft. The upstream ow conditions are the same occurring during a ight along a
ominally" constant descent trajectory at the nearest point to the ground microphone. Comparisons between the predicted noise levels and the measured ones during a ight test, with only the nose landing gear deployed and other airframe and engine sources kept at their admissible minimum, are in good agreement.
49 citations
01 Jul 2010
TL;DR: An optimal combination of tested gear modifications led to a further noise reduction of up to 8 dB(A) in terms of overall A-weighted noise levels relative to the original advanced gear configuration.
Abstract: Landing gear related airframe noise is one of the dominant aircraft noise components at approach, so continued research efforts to reduce landing gear noise are essential. This paper describes further development of an advanced low noise main landing gear that was previously designed and tested in the European SILENCER project. The work was carried out under the current European co-financed TIMPAN project (Technologies to IMProve Airframe Noise) using a 1/4 scaled landing gear model that was tested in the German-Dutch Wind Tunnel. A variety of gear configurations were tested including a new side-stay design and various modifications to the bogie inclination, wheel spacing, bogie fairings with different flow transparency, leg-door configurations and brake fairings. The farfield noise data from the tests are compared with results from a landing gear noise prediction model, transposed to full scale flight conditions and compared with the full scale test data obtained for the original SILENCER advanced A340 s...
49 citations