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.

Landing gear for a tail sitting airplane

Abstract: A tail sitter aircraft of a type that takes off and lands on its tail section with the fuselage pointed vertically upward has landing gears located on its rearward end. Each of the landing gears is mounted on a support axis which is offset from the fuselage axis and which intersects a wheel axle at a 90 degree angle. The landing gears are located on the tail section and spaced around the fuselage axis. Two of the landing gears which are opposite each other will be locked so that they can roll only along a single straight line. The other two landing gears, which are also spaced opposite each other, are locked so that they can roll only on a single straight line. The straight lines are perpendicular to each other.

Two-speed trailer landing gear safety arrangement

Abstract: A two-speed landing gear arrangement for high and low speed operation thereof including a landing gear drive shaft having a high speed detent position and a low speed detent position, a landing gear handle having a handle shaft in longitudinal abutting relation with the landing gear shaft, a coupler housing surrounding and slidably disposed in reciprocable relation on the abutting ends of the handle shaft and the landing gear shaft, the handle shaft having axially spaced drive dogs each mounted by a shear pin and respectively received in an opposed square interlocking recess in the outer end of the housing, said housing at the inner end thereof having a slotted portion with an inner end part in abutting relation with a fixed portion of the landing gear, the outer end of the landing gear shaft having an outer end including a landing gear pin therethrough in lost motion coupleable relation with the slotted portion and further including a slide portion outwardly of the pin cooperative with a reduced bore in the housing, a detent groove on the handle shaft outwardly of the drive dogs and cooperative with a detent means in the outer end of the housing for limiting longitudinal reciprocable movement of the handle shaft with respect to the housing during pulling out of the landing gear crank handle whereby pushing of the handle into the landing gear pushes the landing gear in low gear through the low gear shear pin in the low gear driving dog and pulling out of the landing gear crank handle causes high gear drive of the landing gear through the high gear shear pin in the high gear driving dog.

Aircraft landing gear unlock actuator

Abstract: This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. A lock-stay is connected to the landing gear strut and is movable between locked and unlocked conditions. An unlock actuator is connected to the lock-stay and includes first and second members movable relative to one another. The first member is movable between first and second positions that correspond to the locked and unlocked conditions. A controller is in communication with the unlock actuator and is configured to command the unlock actuator between the first and second positions in response to an input. The second member is permitted to free-drive relative to the first member between the stowed and deployed positions with the lock-stay in the unlocked condition.

Landing gear for a 'silent' aircraft

Abstract: The Silent Aircraft Initiative aims to provide a conceptual design for a large passenger aircraft whose noise would be imperceptible above the background level outside an urban airfield. Landing gear noise presents a significant challenge to such an aircraft. 1/10th scale models have been examined with the aim of establishing a lower noise limit for large aircraft landing gear. Additionally, the landing gear has been included in an integrated design concept for the 'Silent' Aircraft. This work demonstrates the capabilities of the closed-section Markham wind tunnel and the installed phased microphone arrays for aerodynamic and acoustic measurements. Interpretation of acoustic data has been enhanced by use of the CLEAN algorithm to quantify noise levels in a repeatable way and to eliminate side lobes which result from the microphone array geometry. Results suggest that highly simplified landing gears containing only the main struts offer a 12dBA reduction from modern gear noise. Noise treatment of simplified landing gear with fairings offers a further reduction which appears to be limited by noise from the lower parts of the wheels. The importance of fine details and surface discontinuities for low noise design are also underlined.