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: 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: 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: 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.

Abstract: A drive unit includes an actuator from which an output rod protrudes at one end of a cylinder and being coupled to a flap of an aircraft, an attachment disposed on the other side of the cylinder, a reaction link coupled to the flap at one end and to the attachment at the other end, and a connection-disconnection section allowing the cylinder and the attachment to be coupled to and separated from each other.

Abstract: A system and a method for evaluating performance of a porous skin of an aircraft including the porous skin, and a boundary layer control system. The performance evaluation system includes a first sensor providing data related to the performance of the porous skin. The performance evaluation system is further configured to clean the porous skin based on the performance of the porous skin determined using the data received from the first sensor in order to ensure that the porous skin operates at its maximum capability.

Abstract: A remote controlled lighter-than-air drone assembly that is capable of prolonged flight. The drone assembly utilizes a balloon structure. Separately, a reservoir is provided for holding a smaller second volume of gas. A propulsion system and a control unit are carried by the balloon structure. The control unit selectively transfers the gas from the reservoir to the balloon structure, and selectively vents the gas as needed. A receiver is used to receive command signals from an external source. The command signals are utilized to operate the propulsion system. An electronics suite is provided that can be altered depending upon duties. The electronics suite is used to scan or otherwise monitor an area below the drone assembly. In flight, the balloon structure is translucent and internally illuminated. A projector can be provided for projecting images onto the interior of the balloon structure.

Abstract: An aircraft wingbox assembly is disclosed having a wingbox with an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox. The ribs divide the wingbox into bays. A fuel tank is in a first one of the bays. One of the spars includes a spar hole which is configured to enable the fuel tank to be removed from the first one of the bays through the spar hole.

Abstract: Aircraft landing gears include at least one wheel, an electric taxiing system including an electric taxiing motor, brakes capable of slowing down or stopping the rotation of the wheel, and a cooling system for cooling the electric taxiing motor and the brakes. The cooling system includes ventilation means capable of mixing a first air flow originating from the brakes and a second air flow originating from outside the landing gear and of ventilating the electric taxiing motor with a mixture of the two air flows.

Abstract: A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

Abstract: An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

Abstract: Various implementations described herein are directed to an aircraft. The aircraft includes an airframe; and a windshield system having a transparent canopy coupled to the airframe and a transparent inner panel having a portion thereof disposed within the transparent canopy and coupled to the airframe and to at least a processor.

Abstract: In the field of multi-rotor rotary-wing aircraft a propulsion system for such an aircraft includes a reconfigurable electric network for supplying the electric motors driving the rotors. The system includes: a supply source, a supply bus connected to the supply source, at least four drive units each including an electric motor and its control circuit, and an electrical ring network including: an electrical line which is interrupted at each drive unit and whose ends are connected to the supply bus, and, for each drive unit, a first switch and a second switch that are connected between the control circuit and the electrical line, on either side of the interruption.

Abstract: Described herein are aircraft, comprising rear spar integration assemblies, and methods of manufacturing these aircraft. Specifically, an aircraft comprises a keel beam and a center wing box, comprising a rear spar. The rear spar is attached to the keel beam using a rear spar integration assembly. The assembly comprises a rear spar stiffener, attached to the rear spar, and having a stiffener load axis. The assembly also comprises and a keel beam fitting, attached to the keel beam, and having a fitting load axis. The rear spar stiffener is also attached to the keel beam fitting, e.g., using splice plates. More specifically, the fitting load axis is offset relative to the stiffener load axis along the primary axis of the aircraft. This offset is designed to compensate for a bending moment at the keel beam-rear spar interface, which allows reducing the size and/or the number of fasteners needed.