Abstract: An assembly comprising a first part and a second part, the assembly comprising a disconnectable coupling system provided with a mechanical fuse for securing the first part and the second part according to an axis of movement up to a breaking threshold. The assembly comprises at least one single-use friction brake interposed between the first part and the second part, the friction brake braking a movement of the first part with respect to the second part after the mechanical fuse has broken.

Abstract: An ejection method (100) for ejecting at least one payload such as a satellite. The ejection method includes a step (108) of ejecting the payload from a spacecraft that is driven by a continuous propulsion force when the satellite is ejected.

Abstract: A flow body for an aircraft with an integrated de-icing system. The flow body includes a front skin, an internal structural component, a lever having first and second ends, with an attachment point in-between, and an actuator. The actuator is spaced inside the front skin. The lever extends from the actuator to a front skin inner surface, the first end coupling with the front skin, and the second end coupling with the actuator. The attachment point is swivably supported on the internal structural component. The attachment joint is closer to the first end than the second end. The lever and the actuator apply an impulsive force in a transverse direction to the lever, such that the lever rotates around the attachment point, and such the first end urges the front skin to locally elastically deform for removing ice accretion from an outer side of the front skin.

Abstract: A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.

Abstract: Methods and systems for efficiently loading cargo transports, such as cargo aircraft, are described. The methods and systems rely upon payload profiles for various payloads where the payloads include repeatable payloads that have the same characteristics. Based on the payload profile, the payload is positioned at a designated location in an interior cargo bay of the cargo transport. The designated location is denoted by one or more pre-formed markings in the interior cargo bay that establish where a payload having the respective payload profile should be positioned in the bay. The payload can then be secured in the bay. Because the designated location accounts for centers of gravity, the payload can be loaded and secured in the bay without having to run various calculations each time a payload is loaded. Systems and methods related to how the payloads are packaged in an efficient, expeditious manner are also provided.

Abstract: Systems, devices, and methods for stopping the rotation of propellers used in unmanned aerial vehicles (UAV) such as drones are disclosed. The propellers are stopped in response to detecting when beams of light adjacent the propellers are blocked.

Abstract: A paradrone includes a canopy having a parafoil, a transverse canopy frame coupled to the parafoil to support the parafoil, a longitudinal canopy frame that is coupled to the parafoil while having a bent structure such that the parafoil generates a lift, and at least one parafoil connecting portion for connecting at least one canopy frame among the transverse canopy frame and the longitudinal canopy frame to the parafoil. The paradrone also includes a servomotor portion having a servomotor body and a servomotor arm for coupling and fixing intersecting parts of the transverse canopy frame and the longitudinal canopy frame. The servomotor arm is connected to a servomotor body and rotated in a predetermined direction by driving of the servomotor body to change the angle between the travelling direction of the paradrone fuselage and the transverse and longitudinal canopy frames, thereby changing the angle of attack.

Abstract: 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.

Abstract: The present invention relates to the field of heavier-than-air aircraft, such as airplanes and unmanned aerial vehicles (UAV) and, in particular, to emergency rescue systems. The technical objective is accomplished by providing an aircraft, such as a drone, including a powerplant, a parachute, and a body. In particular, the parachute has a fixed shape, it is permanently in an opened state and is connected to the body by rigid braces, while the aircraft center of gravity is located below the aircraft aerodynamic center.

Abstract: A passenger seat assembly includes a riser attached to an upper surface of a floor of the vehicle, a seat attached to an upper surface of the riser, and at least one shell portion attached to the upper surface of the riser. The riser includes at least one door for accessing an interior volume of the riser. At least a portion of the interior volume of the riser is a luggage storage volume.

Abstract: Systems and methods to cut a closing loop to deploy a parachute. The system includes a cutter with a body with a cutter opening that extends through the body and a blade that is movable across the cutter opening. Processing circuitry is configured to signal the cutter to move the blade across the cutter opening. A mount includes a base, a retainer with a channel sized to receive the cutter, and a mount opening that extends through the mount and across the channel. The cutter is configured to fit within the channel with the cutter opening aligned with the mount opening to form a through-opening such that the closing loop extends through the cutter and the mount.

Abstract: A vehicle comprising a morphing wing and a body is disclosed. The aircraft is configured to transform from a first configuration into a second configuration for ascent or descent of the aircraft. The drag force and lift force on the aircraft in the second configuration are less than in the first configuration. Transforming from the first to the second configuration comprises: contracting the wing within a geometric plane defined by the wing, and rotating the outer edge of the wing downwards, out of the geometric plane.

Abstract: A yaw alleviation device for an aircraft containing rotatable wing roots attached to wings. The device includes a spring configured to operatively connect to a wing; and a buckling member to operatively connect to the wing. The spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause rotation of one or both wings in rotationally opposite directions. The buckling member may be positioned parallel and at an offset distance to the spring.

Abstract: The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members. By utilizing a larger rotor blade area (and/or larger rotor disc area) and adjusting the blade pitch and RPM, the rotors can augment the lift generated by the aerodynamic profile of the aircraft in the forward flight mode in addition to providing forward thrust. Variants generating lift with the rotors can reduce or eliminate additional control surfaces (e.g., wing flaps, ailerons, ruddervators, elevators, rudder, etc.) on the aircraft since the thrust and motor torque is controllable (thereby indirectly controlling lift) at each rotor, thereby enabling pitch, yaw, and/or roll control during forward flight.

Abstract: A balloon system including a balloon, and optionally including a payload and/or a safety module. A balloon, preferably including a balloon envelope and one or more passive vents, and optionally including one or more active valves. A method of balloon system operation, preferably including maintaining a zero-pressure balloon condition and sealing balloon vents, and optionally including ascending, descending, and/or otherwise operating the balloon system in flight.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: An in-flight refueling assembly for an aircraft to be refueled by a fuel dispensing aircraft includes a refueling probe extending from the aircraft and having an electromagnet with an energized condition and a non-energized condition. A refueling probe receptacle is connected to the fuel dispensing aircraft. A superconductor is connected to the receptacle such that the refueling probe becomes aligned with the receptacle when the electromagnet is placed in the energized condition.

Abstract: In an embodiment, an aircraft includes an airframe and a first propulsion assembly coupled to the airframe. The first propulsion assembly includes a first rotor hub and a first plurality of rotor blades non-uniformly spaced about the first rotor hub and operable to rotate in a rotor plane with the first rotor hub. The aircraft also includes a second propulsion assembly coupled to the airframe. The second propulsion assembly includes a second rotor hub and a second plurality of rotor blades non-uniformly spaced about the second rotor hub and operable to rotate in a rotor plane with the second rotor hub.

Abstract: An unmanned vehicle having a launch configuration and one or more operational configurations. In the launch configuration, one or more engines resides within an engine bay. The unmanned vehicle is generally shaped like a projectile and can be launch from any tube-shaped deployment system using an initial propulsor. The engine bay can be opened, and the engines can be moved into a generally external position with respect to the engine bay for operation of said engines. In some embodiments, the one or more engines can pivot to direct thrust in multiple directions. In some embodiments, the unmanned vehicle includes flight control surfaces to further improve the flight characteristics of the vehicle.

Abstract: Provided is an aerial vehicle having a structure in which a rotating body has been excluded from a portion that can be touched by a user during flight. An aerial vehicle includes: a balloon unit; a control unit provided at the bottom of the balloon unit; and a plurality of micro-mechanisms (micro blowers), each of which blows out air. The micro blowers have a structure in which a vibrating member is vibrated in a space in communication with a plurality of openings, thereby blowing out, through a second opening, the air that has flowed into the space through a first opening. The control unit controls the micro blowers to change the position or the attitude of the aerial vehicle.