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.

Method and apparatus to increase aircraft maximum landing weight limitation

Abstract: A method and apparatus for establishing a justification basis to Aircraft Regulatory Authorities, to allow for a reduction in aircraft sink-speed assumptions. To further allow the aircraft to operate an increased maximum landing weight limitation. A system for use in measuring aircraft vertical velocity at initial contact with the ground, experienced while aircraft are executing either normal or hard landing events. Pressure sensors are attached to the working pressure within the landing gear strut, so to monitor in-flight landing gear strut pre-charge pressure, until such time as the pre-charge pressure suddenly increases, to detect the aircraft has come into initial contact with the ground. Rotation sensors are attached to the hinged elements of the landing gear strut, so to monitor in-flight landing gear strut extension, until such time as the strut extension suddenly decreases, to detect the aircraft has come into initial contact with the ground.

Aircraft landing gear load sensor

Abstract: An aircraft landing gear comprising a fibre optic load sensor for monitoring load in a component of the landing gear, such as an axle. The fibre optic cable is mounted on an inner surface of the component of the landing gear. Typically the fibre optic load sensor comprises one or more Bragg Grating sensors.

Drop Testing Naval Aircraft and the VSD Landing Gear Dynamic Test Facility

Abstract: This paper describes a laboratory facility developed by Vought Systems Division (VSD) of LTV Aerospace Corp. and techniques used to realistically simulate landings of full scale aircraft under precisely controlled conditions. Capabilities are included to evaluate effects of running over deck obstructions during carrier landings or other types of bumps that might be encountered in rough field operations of aircraft. The project provided VSD with the most accurate method known for dynamic simulation of aircraft landings and safe evaluation of the structural adequacy of airframes and landing gear systems for landing loads. Operational characteristics of the facility are predictable and repeatable. A deck obstruction or bump can be repeatedly passed under the landing gear wheel within */2 in. of any preselected point in the stroke of a landing gear strut at any sink speed or landing velocity to 120 knots. Tests performed in the facility have shown that running over a bump can increase both main gear and nose gear loads significantly and can also result in tires being cut and rims bent at lower sink speeds than previously anticipated. Comparison of data shows the laboratory data to be characteristic of flight test data.

Ground-bound device for take off, landing and taxiing of aircrafts

Abstract: The invention relates to a device in the form of a ground-bound device for take off, landing and taxiing aircraft or flying objects without a landing gear or with a retracted landing gear. Said device consists of three main components, a slide (7), a carriage (9) a ground landing gear device (10) and is characterised by the following characteristics: said ground landing gear device (10) can be detachably connected to a slide system that can be driven in the direction of displacement; said ground landing gear device (10) comprises at least two coupling means that allow intersecting points of the aircraft to be coupled to said ground landing gear device (10); said ground landing gear device (10) can be displaced along the slide system transversal to the direction of displacement of the slide system in order to adapt said ground landing gear device (10) to the position of the aircraft; and said ground landing gear device (10) can be adjusted about the vertical axis at an angle in relation to the direction of displacement of the slide system, in order to adapt the ground landing gear (10) to a yaw angle of the aircraft in relation to the direction of displacement of the slide system.