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.

Aircraft towing vehicle

Abstract: The invention relates to an aircraft towing vehicle, comprising a lifting and a locking device (5) for the nose landing gear of the aircraft being towed, which device has two support elements (9) which reach behind the nose wheels and can be displaced along straight-line guiding rails (15) by means of a linear drive (11) so as to pull the nose wheels of the aircraft onto a lifting platform (7) and to lock it into place thereon. At the end of each guiding rail (15), the invention provides for a guiding pin (29) which, in cooperation with a guiding track (31, 31') embodied in the support element, controls the rotation of said support elements into a release position in which the nose landing gear is able to pass through or, by a reverse movement, the rotation of the support elements into the operating position in which said support elements reach behind the nose landing gear.

Multifunctional electromechanical device for landing gear

Abstract: The invention relates to a multifunctional electromechanical device for aircraft landing gear, comprising at least: a first shaft (10) rotatably mounted onto the aircraft around a rotational axis (R) substantially parallel to a hinge axis (X) of the landing gear on the aircraft; a second telescopic shaft (20) rotatably mounted onto the landing gear while descending along the latter until in proximity with the wheels present on the latter; a transmitting means (19) for transmitting a rotational movement of the first shaft to the second shaft; a transmitting means (21) for transmitting a rotational movement of the second shaft to at least one wheel present on the landing gear; a braking means (30) being specific to one of the shafts in relation to the landing gear if the wheel is not provided with a brake; and a motor means (11, 15) for turning the first shaft.

Wind tunnel experiments on airframe noise sources of transport aircraft

Abstract: Source distributions of airframe noise of a transport aircraft have been measured in the anechoic test section of the German-Dutch Wind Tunnel (DNW) by means of a highly directional microphone. This device - an elliptical acoustic mirrormicrophone system - had been designed for model tests in smaller wind tunnels but could be adapted to the new task. During most of the tests the model was in landing configuration with leading edge slats, flaps and landing gear extended. Some measurements of the sound source distributions were also made, for comparison, with the model in clean configuration (slats, flaps and landing gear retracted). Within the measured source distributions, dominant aerodynamic noise sources could be clearly identified. These are mainly the landing gear and the slats and flaps in extended position. The tests have demonstrated that the acoustic mirror telescope is a practical and reliable device for investigations of airframe noise sources by wind tunnel tests in the DNW.

Shimmy in a nonlinear model of an aircraft nose landing gear with non-zero rake angle

Abstract: This work concentrates on the lateral oscillations in vehicles, also called shimmy, with a particular emphasis on aircraft. A mathematical model of a nose landing gear is discussed with geometric detail that has been mostly neglected in the past research. Stability criteria for the shimmy-free operation of the landing gear are derived using linear stability analysis. Nonlinear analysis is used not only to study the qualitative behaviour of the Hopf bifurcation but also to analyze the system beyond the Hopf bifurcation. The manuscript concludes with suggestions for future research.

Rotorcraft Slope Landings with Articulated Landing Gear

Abstract: Rotorcraft are uniquely suited to operate in remote areas, primarily due to their ability to perform vertical takeoffs and landings. However, the slope of the landing surface can severely limit viable landing areas. Adding robotic articulated landing gear to a rotorcraft increases the number of degrees of freedom that can be used to land on an irregular surface. Instead of relying on the rotor thrust magnitude and direction to land safely, the gear can also be used to conform more closely with the ground, potentially allowing for quicker and safer landings. The current work presents a multi-body simulation tool to simulate the dynamics of a rotorcraft with robotic gear landing on sloped terrain, including overall system motion, loads computation, and stress analysis. Through dynamic simulation and analysis it is shown that a robotic legged landing gear system can substantially expand the slope and type of terrain for landing with a small increase in landing gear system weight.