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.

Design and Fabrication of the Mars Helicopter Rotor, Airframe, and Landing Gear Systems

Abstract: The Mars Helicopter is an autonomous 1.8 kg co-axial, counter-rotating rotorcraft baselined to fly on the Mars 2020 mission to demonstrate aerial mobility on the surface of Mars. In this paper the authors describe the design, development, and fabrication of the rotor system, landing gear system, and auxiliary structures which are being integrated onto the helicopter. The rotor system has a diameter of 1.21 m and consists of the rotor blades and hubs, direct-drive brushless propulsion motors, swashplates and linkages, and servos that actuate the swashplate. The landing gear is comprised of four folding composite landing legs and suspension mechanisms that deploy upon egress from the rover. Several test campaigns were carried out on engineering development models in 2017/2018, and final assembly and testing of the flight model is expected to be complete by early spring 2019.

Retractable landing gear

Abstract: This invention relates to means for retracting the landing gear of areoplanes, or the floats of hydroplanes, the embodiment of which considerably simplifies known constructions by rendering superfluous the usual multiple lifting-control members and the special locking means required when the...

An Adaptive Landing Gear for Extending the Operational Range of Helicopters

Abstract: Conventional skid or wheel based helicopter landing gears severely limit off-field landing possibilities, which are crucial when operating in scenarios such as mountain rescue. In this context, slopes beyond 8° and small obstacles can already pose a substantial hazard. An adaptive landing gear is proposed to overcome these limitations. It consists of four legs with one degree of freedom each. The total weight was minimized to demonstrate economic practicability. This was achieved by an innovative actuation, composed of a parallel arrangement of motor and brake, which relieves the motor from large impact loads during hard landings. The loads are alleviated by a spring-damper system acting in series to the actuation. Each leg is individually force controlled for optimal load distribution on compliant ground and to avoid tipping. The operation of the legs is fully autonomous during the landing phase. A prototype was designed and successfully tested on an unmanned helicopter with a maximum take-off weight of 78 kg. Finally, the implementation of the landing gear concept on aircraft of various scales was discussed.

Characterization of Low Noise Technologies Applied to a Full Scale Fuselage Mounted Nose Landing Gear

Abstract: The negative impact of aircraft noise includes effects on population’s health, land use planning and economic issues such as building restrictions and operating restrictions for airports. Thus, the reduction of noise generated by aircraft at take-off and approach is an essential consideration in the development of new commercial aircraft. Among the different aircraft noise sources, landing gear noise is one of the most significant during approach. This research presents results from the European Clean Sky funded ALLEGRA project, which investigated a full-scale Nose Landing Gear (NLG) model featuring the belly fuselage, bay cavity and hydraulic dressing. Tests were performed for a variety of wind speeds and yaw angles. In this paper, a characterization of the noise generated by the full-scale Nose Landing Gear (NLG) model is presented and the different techniques used for characterizing acoustic sources on the NLG are described. The landing gear noise source is characterized in terms of OASPL, directivity, source spectra, PNL and PNLT. A comparison between the NLG with and without the application of low noise technology is presented.Copyright © 2015 by ASME