According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy absorbing assembly. The energy absorbing assembly includes first and second portions and a retractable section. The retractable section may be at least partially affixed to the first portion and is configured to enable displacement of the second portion of the stabilizer with respect to the first portion.

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

The present disclosure provides a landing gear assembly for reducing drag on an aircraft. Landing gear assembly may include a proximal joint, a movable leg extending from the proximal joint, and a base attached to a distal end of the leg. The base may be configured to support the electric aircraft on an environmental surface. The landing gear assembly may transition between a deployed landing position and a collapsed flight position when landing and taking off to provide optimal aerodynamics of the aircraft.

An aircraft landing gear assembly having a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.

An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

An aircraft landing gear is disclosed including a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

An aircraft undercarriage includes an upper element for connecting to an aircraft structure and a lower element carrying an axle. The lower element is mounted to be movable in translation relative to the upper element along a longitudinal axis, and a shock absorber is arranged to damp movements in translation of the lower element relative to the upper element.

First and second portions of a spring are connected respectively to the upper element and to the lower element so that during movement in translation of the lower element relative to the upper element, the spring opposes any turning of the lower element relative to the upper element about said longitudinal axis.

An impact absorber device (10) of a fixed landing skid of an aircraft (1) is described. The device comprises a female element (20), a male element (30) and a core (40) arranged between said female element and said male element, wherein said female element comprises a cavity and said male element comprises a support and pressure surface for supporting said core, wherein said core comprises a body with controlled plastic deformation of a metallic material. In embodiments of the invention, the core comprises an extruded body having a honeycomb structure or a body comprising a spirally wound metallic substrate.