A strut assembly for an aircraft landing gear structure according to the present disclosure is transitioned between an extended configuration, corresponding to the aircraft being off the ground, and a retracted configuration, in which the strut assembly is shortened along its longitudinal axis with respect to the extended configuration, for stowage during flight. The strut assembly includes an upper bulkhead supported by an upper tubular housing, and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing. To transition the strut assembly to the retracted configuration, translation of the upper bulkhead with respect to the upper tubular housing mechanically causes translation of the lower tubular housing to a retracted position, such that the overall length of the strut assembly is reduced. In some examples, the strut assembly is an oleo strut assembly.

An aircraft nose gear-mounted flight control device promotes aircraft stability during low-speed phases of flight, including take-offs and landings. The flight control device is an operable airfoil secured to an aircraft nose gear, either to a vertical support strut or to a wheel axle thereof. The airfoil is deployed when the nose gear is deployed, and is retracted when the nose gear is retracted. Upon deployment, the airfoil is effective to at least provide aircraft pitch control. In some configurations, the airfoil deploys as two separate but mirror-imaged left and right airfoil components that move in concert to provide pitch control. In other configurations, the airfoil components move at relatively different angular rates and amounts to provide both pitch and roll control. The entire airfoil may be pivotal for pitch control, or may instead be fixed, but have moveable flaps or flap-like portions that provide pitch control.

A spaceplane suitable for aeronautical flight comprising a body and a wing defining a lower airfoil surface in addition to attitude control means that comprise one or a plurality of shutters disposed under the lower airfoil surface of same and maneuverable between a stowed position and an inclined extended position for aerodynamic braking during the transition from a phase of space flight to a phase of aeronautical flight of the aircraft.

A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

The present disclosure provides a system for opening and closing, in a substantially longitudinal direction, at least one hatch of a landing gear bay of an aircraft. In particular, the system includes: a proximal guide rod and a distal guide rod, each having a first end pivotably attachable to the hatch, and a second end pivotably attachable to a stationary inner structure of the gear bay, and arranged such as to form a deformable parallelogram hinge; and at least one drive rod having a first end that is pivotably attachable to the hatch, and a second end that is pivotably attachable to a landing gear leg.

The present disclosure provides a system for opening and closing, in a substantially longitudinal direction, at least one hatch of a landing gear bay of an aircraft. In particular, the system includes: a proximal guide rod and a distal guide rod, each having a first end pivotably attachable to the hatch, and a second end pivotably attachable to a stationary inner structure of the gear bay, and arranged such as to form a deformable parallelogram hinge; and at least one drive rod having a first end that is pivotably attachable to the hatch, and a second end that is pivotably attachable to a landing gear leg.

A fence 30A is installed on an inner surface 21a of a door 20A on the side which faces a landing gear bay 15, the fence 30A rising inwardly of the airframe from the inner surface 21a. When the door 20A opens outwardly of an airframe due to a pressure difference between the side of an outer surface 21c of the door 20A and the side of an inner surface 21a facing inner part of the landing gear bay 15 during a flight of an aircraft 10, the fence 30A closes a gap between the door 20A and an opening 15a of the landing gear bay 15, and thereby prevents air from flowing into the landing gear bay 15 through the gap.

A fence 30A is installed on an inner surface 21a of a door 20A on the side which faces a landing gear bay 15, the fence 30A rising inwardly of the airframe from the inner surface 21a. When the door 20A opens outwardly of an airframe due to a pressure difference between the side of an outer surface 21c of the door 20A and the side of an inner surface 21a facing inner part of the landing gear bay 15 during a flight of an aircraft 10, the fence 30A closes a gap between the door 20A and an opening 15a of the landing gear bay 15, and thereby prevents air from flowing into the landing gear bay 15 through the gap.

Provided is a tailstock type vertical take-off and landing unmanned aerial vehicle and a control method thereof. The unmanned aerial vehicle is mainly composed of a fuselage, wings, ailerons, empennages, an elevator, a rudder, an engine, an attitude adjustment nozzle, a landing gear, and the like. The wings are symmetrically arranged on both sides of the middle of the fuselage; the ailerons are hinged to the trailing edges of the wings on the both sides; the empennages are located at the tail of the fuselage, and a form of vertical empennages+horizontal empennages or V-shaped empennages can be used; the elevator and rudder are hinged to the trailing edges of the empennages; the engine is arranged at the tail of the fuselage for producing main thrust.