Abstract: An aircraft-floor element comprising a first cladding element configure to be swung from a first position to a second position. In the first position, the first cladding element is arranged parallel to a main plane of the aircraft-floor element and on a side of the aircraft-floor element which is directed towards a passenger cabin. In the second position, the first cladding is arranged at an angle to the main plane of the aircraft-floor element, wherein it forms a cladding for a cargo space. An aircraft zone having an aircraft-floor element and an aircraft having such an aircraft zone are also disclosed.

Abstract: An aircraft landing gear assembly is disclosed including a landing gear bracket, a fore lever receiving a fore aircraft wheel, an aft lever receiving a rear aircraft wheel, the fore and aft levers being independently moveable, wherein the bracket further comprises a fore lever stop to prevent downwards movement of the fore lever past a lowest rotational position with respect to the bracket at a first angle ?1 forward from the notional bracket axis, and a rear lever stop to prevent downwards movement of the rear lever past a lowest rotational position at a second angle ?2 behind from the notional bracket axis, wherein the first angle is greater than the second angle. An aircraft and a method of landing an aircraft are also disclosed.

Abstract: A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.

Abstract: The disclosure generally pertains to a vertical take-off and landing (VTOL) aircraft comprising a fuselage and at least one fixed wing. The aircraft may include at least two powered rotors located generally along a longitudinal axis of the fuselage. The rotor units may be coupled to the fuselage via a rotating chassis, which allows the rotors to provide directed thrust by movement of the rotor units about at least one axis. The VTOL aircraft may include instructions to perform a degraded rotor landing protocol. The degraded rotor landing protocol may include adjusting a power to an operable rotor unit to control a rate of descent and/or slow a rate of acceleration toward a landing surface. The VTOL aircraft may be configured to impact the landing surface from a substantially vertical configuration, and adjust a thrust vector to cause the aircraft to come to rest in a generally upright configuration.

Abstract: An air mobility may include a wing portion extending from a fuselage of the air mobility; a folded portion provided at an edge portion of the wing portion, configured to extend from the wing portion to form a part of the wing portion during unfolding of the folded portion, and configured to move to overlap with the wing portion during folding of the folded portion, so that an area of air resistance in a vertical direction of the wing portion is reduced; an actuator connected to the folded portion and configured to provide power to the folded portion, so that the folded portion is unfolded or folded to the wing portion; and a controller connected to the actuator and configured to control the actuator, so that the folded portion is folded during vertical takeoff or landing of the fuselage, and configured to control the actuator to unfold the folded portion during cruising of the fuselage.

Abstract: Distributed trailing edge actuation systems and methods for aircraft are described herein. An example aircraft includes a wing, a flap coupled to the wing, the flap movable between a stowed position and a deployed position, and a distributed trailing edge (DTE) actuation system including a flap actuator coupled to the wing to move the flap. The flap actuator includes an integrated hydraulic powered actuator and electric powered actuator. The flap actuator is operable in a hydraulic powered mode in which the hydraulic powered actuator is activated to move the flap, an electric powered mode in which the electric powered actuator is activated to move the flap, and a hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap.

Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.

Abstract: An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.

Abstract: An aircraft includes a fuselage that provides an aircraft passenger cell and a plastically deformable protective body secured on the fuselage. The plastically deformable protective body can be secured on the bottom of the fuselage and/or laterally on the fuselage. The plastically deformable protective body can be secured releasably on the fuselage, for example, via a screw connection.

Abstract: Stud-propelling mechanisms for securing a launch vehicle to a landing platform, and associated systems and methods, are disclosed. A representative system includes a fastening mechanism carried by a landing support element of a portion of a launch vehicle, the mechanism configured to fasten the landing support element to the landing surface when the launch vehicle portion is on the landing surface. The fastening mechanism can include a barrel structure for propelling a stud and an interference portion positioned to receive the stud upon activation of an energetic material that propels the stud. The stud can bind in the interference portion and in the landing surface to fasten the landing support element to the landing surface. A representative method includes automatically fastening a portion of a launch vehicle to a landing surface using a stud carried by the portion of the launch vehicle.

Abstract: A missile comprises a generally cylindrical body having a distal end and a proximal end; a nosecone having a pointed distal end and a proximal end, wherein the proximal ends of the body and nosecone are oriented toward each other; a forward angled section rotatably attached to the proximal end of the nosecone at its forward edge, the opposite end of the forward angled section having an angled edge perpendicular to the longitudinal axis except for the angle defined by the edge; a rear angled section rotatably attached to the proximal end of the body at its rear edge, the opposite end of the forward angled section having an angled edge matching the angled edge of the forward angled section, the angled edges of the forward angled section and the rear angled section being rotatably attached.

Abstract: An aircraft propulsion assembly includes a first engine and a second engine that are adjacent and a nacelle in which the engines are installed. The nacelle includes a common air inlet lip for the first engine and the second engine, the air flow being divided between the first engine and the second engine by a median lip which extends, at least partly, set back from said common air inlet lip. The common are inlet lip includes, directly in line with the median lip, a bottom lobe and a top lobe extending forward of the nacelle. Such a configuration makes it possible to be able to provide a high aerodynamic form between the fairings of the engines, without the risk of generating overspeeds in the air flow.

Abstract: A propulsion system for an aircraft, including at least one rotor and a nacelle cowling extending around the at least one rotor, said nacelle cowling being sectored and including at least one sector, which is fixed and sectors which are retractable in the peripheral direction relative to an axis of rotation of the rotor. The retractable sectors include at least a first series of sectors which are telescopically retractable in or on at least one fixed sector and at least a second series of sectors which are telescopically retractable in or on at least one fixed sector, the at least one fixed sector having an angular extent around the axis which is less than or equal to 90°.

Abstract: An unmanned aerial vehicle (UAV) module includes a UAV having foldable wings coupled to a body of the UAV, a UAV case having length and width dimensions that is constructed and arranged to operate in (i) a closed configuration that stores and protects the UAV while the UAV module is transported within the UAV case between locations with the foldable wings in a folded configuration, and (ii) an opened configuration that provides a base from which the UAV launches vertically from within the UAV case while the foldable wings of the UAV remain in the folded configuration. The UAV is constructed and arranged to automatically unfold the foldable wings outwards from the body of the UAV to form a fixed wing that extends beyond the length and width dimensions of the UAV case for fixed wing horizontal flight after the UAV is airborne.

Abstract: Duct stringers for aircraft wing boxes. The duct stringer comprises a base, a pair of sidewalls projecting from the base in a spaced-apart relationship, and a cap wall that extends between and interconnects the pair of sidewalls, with the cap wall being positioned spaced apart from the base by the pair of sidewalls. The duct stringer further comprises an ovaloid vent formed in the cap wall. The ovaloid vent comprises a perimeter that circumscribes an aperture and that defines a closed shape. The perimeter comprises a pair of curved end regions opposed to one another and that each arc at least substantially through 180 degrees. Each curved end region comprises a non-uniform radius of curvature.

Abstract: A system of an electric aircraft with pitch control using an elevator is presented. In some embodiments, the electric aircraft may include an elevator configured to deflect. In some embodiments, the electric aircraft may further include a lift lever configured to generate a lift command upon activation by a pilot. In some embodiments, the electric aircraft may further include a flight controller communicatively connected with the lift lever and the elevator, wherein the flight controller is configured to receive the lift command from the lift lever and adjust the elevator as a function of the lift command.

Abstract: An actuator system for controlling movement of a plurality of panels. The system includes two lifting mechanisms connected to each panel at two separate locations on the panel, and, for each panel: an actuator in engagement with a first of the lifting mechanisms to drive the lifting mechanism to move the panel, and a torque tube having a first end in engagement with the actuator so as to be rotated by the actuator as the actuator drives the lifting mechanism, the torque tube having a second end in engagement with the other of the two lifting mechanisms to drive the lifting mechanism due to rotation of the torque tube.

Abstract: The cross-sectional shape of a support member is an airfoil shape in which a first end portion including a first end is curved and which tapers toward a second end. The support member is arranged such that the tapering direction of the airfoil shape is downward, and the tapering direction of the support member is determined in advance according to the moving direction of a blade passing directly above the support member during rotation of a takeoff and landing rotor.

Abstract: A rescue basket having the capacity to safely hold two full-sized individuals increases the efficiency and effectiveness of helicopter water rescue and recovery operations. The rescue basket includes an open end, which affords an additional option for loading passengers, along with a door mechanism that can at least partially close off the open end for passenger safety. The rescue basket includes a flotation system that maintains the basket at a desired flotation level when completely immersed in water, along with sufficient reserve buoyancy to safely maintain the passengers above water when loaded. Methods of performing a water rescue utilizing the present rescue basket on board of a helicopter are also provided.

Abstract: A hybrid air mobility system is capable of flying a long distance through effective operation of an engine and batteries. The hybrid air mobility system includes a fuselage configured to supply power to a propeller and electric equipment, the fuselage being provided with a duct including an inlet and an outlet so as to circulate air to the engine and the electric equipment; a deflector rotatably installed at the outlet of the duct so as to convert a discharge direction of exhaust gas generated by the engine and cooling air after cooling the electric equipment; and a controller configured to determine whether or not the engine is driven and to control a rotated position of the deflector depending on an amount of driving of the engine so as to selectively adjust movement of the exhaust gas and the cooling air towards the propeller.