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 assembly for a model helicopter

Abstract: A landing gear assembly is provided for use on a model helicopter. The landing gear assembly includes a landing gear strut having a leg portion and a foot portion connected to the leg portion to define an included right angle therebetween. The assembly also includes a landing gear skid formed to include a landing gear strut attachment area provided with an L-shaped slot arranged to receive and trap the foot portion of the landing gear strut therein.

Amphibious large aircraft without airstairs

Abstract: An amphibious large aircraft without airstairs is provided. The fuselage (7) of the amphibious large aircraft is flat, and the shape of its bottom is rectangular. The longitudinal cross-section of the fuselage has a shape of the cross-section of a win, so the lift can be generated by the fuselage during flight, and the flight efficiency is increased by 30-40%. The fuselage has only one floor, wherein the passenger cabin (6) is set in the front of the fuselage, and the cargo hold (21) is mounted above the rear. The wings (8) are suspended towards two sides from upper side of the fuselage. A jet engine (30) is mounted above the rear of the fuselage and adjacent to the tail wing. Because landing gears (4, 9) can be lifted vertically and the landing gear wells (3, 10) mounted in the fuselage are provided with fore-and-aft sliding doors (32, 33), the fuselage can stop close to the ground. It is no need for the passenger to go on and off the aircraft via the airstairs and escape from the aircraft via the inflator slide in en emergency. It can be more convenient for the cargo to enter or exit the aircraft when the aircraft is used as a freight aircraft. Because the fuselage is flat, the gliding capability and the ground effect of the aircraft are better, and the aircraft can takeoff, land and cruise on the wide water. The full-length, wingspan and height of the aircraft are all reduced by 25-30% compared with the current aircraft of the same scale, thus the floor space and the investment of the manufacturer, the maintenance factory, the garage and the aerodrome are all reduced.

Design of a five-phase permanent-magnet motor for the electric steering of an aircraft nose landing gear

Abstract: Recently, there has been a growing interest in reducing the number or replacing the hydraulic/pneumatic actuators utilised on aircraft with electric actuators coupled to mechanical gears, which would improve the reliability and performance. This is involved in the concept of more electric aircraft. The electrification of actuators would affect the primary and secondary flight controls, as well as the movement of flight surfaces, retraction of the landing gear, and steering of the nose landing gear, which is also considered in this study. This study considers the design of a multiphase permanent-magnet (PM) motor to be utilised for the electric steering of a commercial aircraft nose landing gear. This multiphase motor would make it possible to achieve a highly reliable actuator and, coupled with a harmonic drive, avoid the use of a multi-motor configuration. Moreover, a multiphase motor would increase the power density and efficiency of the actuator, through improving the torque ripple. The performance variation due to temperature swings is considered, and a design procedure for the PM motor is described using the worse operation case for the electric actuator. The adequate performance of the designed motor and actuator is demonstrated by means of a finite element analysis.

Landing gear for unmanned aerial vehicle

Abstract: The utility model discloses a landing gear for an unmanned aerial vehicle The landing gear comprises a landing gear base, a top surface and a support wall The base is connected with the top surface through the support wall, and is provided with a battery inlet hole Battery plugs are arranged on the base on the two sides of the battery inlet hole A battery compression plate is arranged on the support wall Balls are arranged on vertex angles of the battery compression plate Ball grooves are formed in the support wall Springs are arranged between the battery compression plate and the top surface According to the landing gear for a miniature multi-rotor unmanned aerial vehicle, stable landing in a complex environment, the blind plugging of a battery and combination with a landing gear fixing device of a battery replacement platform are realized