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.

A new concept for UAV landing gear shock vibration control using pre-straining spring momentum exchange impact damper:

Abstract: This study proposes a new method for reducing the shock vibration response of an Unmanned Aerial Vehicle (UAV) during the landing process by means of the momentum exchange principle (MEID). The per...

Development of prototype electro-hydrostatic actuator for landing gear extension and retraction system

Abstract: More Electric Aircraft (MEA) or All Electric Aircraft (AEA) is intensively researched and developed all over the world to reduce total Aircraft power consumption, and thus total operation cost. In MEA or AEA development, Aerospace Research and Technologies activity are focusing the area of Electrical Power system, Flight control, Engine system, Environmental Control System and Landing Gear System.[1] We are focusing the Landing Gear Actuation System and as our 1st step we have developed prototype ELECTRO-HYDROSTATIC ACTUATOR (EHA) for Landing Gear Extension and Retraction System (LGERS) application. The prototype EHA was designed and tested to evaluate the performance, weight and reliability to apply the future Aircraft application. From our prototype model development, we have clarified the technical issues to be improved or considered in the future MEA or AEA application.

Aerodynamic Measurements of a Gulfstream Aircraft Model With and Without Noise Reduction Concepts

Abstract: Steady and unsteady aerodynamic measurements of a high-fidelity, semi-span 18% scale Gulfstream aircraft model are presented. The aerodynamic data were collected concurrently with acoustic measurements as part of a larger aeroacoustic study targeting airframe noise associated with main landing gear/flap components, gear-flap interaction noise, and the viability of related noise mitigation technologies. The aeroacoustic tests were conducted in the NASA Langley Research Center 14- by 22-Foot Subsonic Wind Tunnel with the facility in the acoustically treated open-wall (jet) mode. Most of the measurements were obtained with the model in landing configuration with the flap deflected at 39o and the main landing gear on and off. Data were acquired at Mach numbers of 0.16, 0.20, and 0.24. Global forces (lift and drag) and extensive steady and unsteady surface pressure measurements were obtained. Comparison of the present results with those acquired during a previous test shows a significant reduction in the lift experienced by the model. The underlying cause was traced to the likely presence of a much thicker boundary layer on the tunnel floor, which was acoustically treated for the present test. The steady and unsteady pressure fields on the flap, particularly in the regions of predominant noise sources such as the inboard and outboard tips, remained unaffected. It is shown that the changes in lift and drag coefficients for model configurations fitted with gear/flap noise abatement technologies fall within the repeatability of the baseline configuration. Therefore, the noise abatement technologies evaluated in this experiment have no detrimental impact on the aerodynamic performance of the aircraft model.

Jumbo aircraft, in particular of high-wing monoplane design

Abstract: This invention relates to an improvement in a jumbo aircraft, in particular of high-wing monoplane design, with a fuselage and a retractable and steerable main landing gear and a device for high lift generation, the improvement comprising (a) a plurality of rows of landing gear units mounted along the aircraft fuselage and spread across a range extending predominantly in the longitudinal aircraft direction, the units forming the main landing gear, (b) the landing gear units being of the same design and identical dimensions, and (c) a device for switching-on the lift generating device at predetermined lift conditions together with setting and maintaining a longitudinal attitude of the aircraft or of its landing gear parallel to the taxiway and runway, whereby the take-off phase or the landing phase is performed using the method of direct lift control.

CFD/CAA Analysis of the LAGOON Landing Gear Configuration

Abstract: The unsteady flow field about the ONERA/Airbus LAGOON two-wheel landing gear configuration and the associated aerodynamic noise generation are computed using a hybrid approach in which the flow field is provided by a Lattice-Boltzmann simulation, and the noise radiation is computed using the Ffowcs-Williams & Hawkings analogy. A detailed validation study is carried out, following the guidelines of the second workshop on benchmark problems for airframe noise computations, and deploying the complete experimental database for detailed comparisons. The effect of grid resolution on both nearand far-field results is investigated, showing the physical consistency of the numerical model. In addition, an assessment of the numerical prediction is carried out by computing the maximum perceived noise level along a nominal approach trajectory. Finally, an unsteady flow mechanism, never reported so far, involving the onset of cavity modes in the two facing rim cavities is analyzed in detail and correlated with the generation of tonal noise components.