Abstract: According to one implementation, a propulsion system includes a rotor, a motor and an anti-icing mechanism. The rotor has blades. The motor rotates the rotor. The anti-icing mechanism deices the blades using heat generated by driving of the motor. Further, according to one implementation, an aircraft includes the above-mentioned propulsion system. Further, according to one implementation, an anti-icing method of a rotor having blades includes deicing the blades using heat generated by driving of a motor for rotating the rotor.

Abstract: An aircraft controlled by compressed air according to an embodiment of the present invention comprises: a fuselage (10) having main wings (20) on both sides thereof; a first nozzle (12) mounted to the roof of the fuselage (10); second nozzles (22) mounted on the top surfaces of the main wings (20); a first tank (31) disposed in the fuselage (10) or the main wings (20) and storing compressed air; and a main control valve (40) for controlling the compressed air so that the compressed air is provided to the first nozzle (12) or the second nozzles (22).

Abstract: A vertical takeoff and landing aircraft using a hybrid electric propulsion system and a control method therefor according to an embodiment of the present invention: performs control such that, during vertical takeoff and landing of an aircraft (1), a generator (20), a power management device (4), and a battery management system (60) simultaneously provide power to a motor (80); and performs control such that, during a cruise flight or transition flight of the aircraft (1), the thrust of a second propeller (82) is increased and a battery (62) of the battery management system (60) is charged with redundant power generated by the generator (20).

Abstract: An example method for launching a high-altitude balloon includes securing a launch collar around a balloon envelope to form a choke point separating an upper portion of the balloon envelope from a lower portion of the balloon envelope. The balloon envelope is structurally secured to a launch platform via a tether that is coupled to the launch collar. The launch collar is configured such that release of the launch collar from the choke point releases the balloon envelope from the launch platform.

Abstract: An aircraft includes a fuselage, a pylon, a wing positioned between the fuselage and the pylon, and a plurality of drive shafts located inside the wing and adapted to drive a rotor associated with the pylon.

Abstract: An unmanned aerial vehicle according to the present invention may comprise: a rotor-blade for providing thrust according to generation of main stream; and a safety guard disposed to surround the rotor-blade. The safety guard may comprise: a guide member which is disposed coaxially with the rotor-blade while having a gap between the guard member and the end of the rotor-blade, so as to stabilize, when the rotor-blade rotates, a flow field suctioned by a negative pressure, and stably boost a discharge flow when the pressure is changed to a positive pressure; and a diffuser which is disposed coaxially with and radially spaced apart from the guide member, and generates a secondary flow toward the main stream to increase a flow rate.

Abstract: Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.

Abstract: An anti-torque rotor includes a mast rotatable about a first axis; a plurality of blades; an element slidable along the first axis, rotating integrally with the mast and operatively connected to the blades. The rotor also has a slidable control rod; a first bearing with a rotatable first ring, a second ring radially internal to the first ring and a plurality of first rolling bodies; a third ring slidable along the first axis and angularly fixed with respect to the first axis; and a locking element arranged in a first configuration, in which it prevents the relative rotation of the second and third rings and is movable from the first configuration to at least one emergency configuration, in which it renders the second ring free to rotate with respect to the third ring, when the first bearing is in a failure condition.

Abstract: In order to provide a track drive device for an aircraft that has zero backlash, a large gear reduction, the ability to self-lock, and a better load transfer and reduced wear, the track drive device drives a track member through a drive device that has at least one drive unit that is arranged adjacent to the track member. Each drive unit comprises a plurality of engaging members that are driven by a cam shaft or a cam gear such that the engaging members are sequentially shifted in a wave-like pattern which results in the track member being moved in a linear manner relative to the drive device along a longitudinal direction.

Abstract: A spoiler actuation apparatus for moving an aircraft spoiler. The spoiler is moveable between a stowed configuration and a deployed configuration. The spoiler actuation apparatus includes a guide member, a rack mounted on the guide member and slideable along a longitudinal axis of the guide member, and a gear coupled to the rack, the gear arranged to move the spoiler in response to sliding of the rack. The rack is held at a first position when the spoiler is in the stowed configuration. An actuator moves the rack from the first position to a second position along the longitudinal axis. When the rack is at the second position, the rack is operable to accelerate relative to the guide member away from the second position by an aerodynamic force acting on the spoiler.

Abstract: Devices and methods for activating a flight-enable beacon configured to provide a light beacon or data signal comprising capability to establish and maintain a fixed set of coordinates. The flight-enabled beacon is configured with a processor, memory, motor, gimbal or swashplate and light emitting source and can be configured to attain and maintain a target altitude and emit a light over a fixed period of time. The flight-enabled beacon is configured to be light and with small form factor for easy portable transport in cases of emergency or to provide a signal easily locatable by parties located a distance from the activated light-enabled beacon.

Abstract: A drive augmenter provide supplemental drive power to the wheel of a landing gear with a drive system. The landing gear has a wheel rotatably mounted to an axle, and the drive system selectively provides a driving force to rotate the wheel. The drive augmenter includes a piston slidably disposed with a cylinder, and selective pressurization of the cylinder drives reciprocating translation of the piston within the cylinder. A crank is coupled to the piston by a rod and is also coupled to a crankshaft. The crank is configured to convert translation of the piston into rotation of the crankshaft. The drive augmenter further includes a drive shaft coupled to the wheel and a clutch configured to selectively transfer rotation of the crankshaft to the drive shaft.

Abstract: Fuselage barrel assemblies and methods of assembling fuselage barrel assemblies are disclosed herein. The fuselage barrel assemblies include a first barrel section and a second barrel section, which is interfaced with the first barrel section to define a barrel joint between the first barrel section and the second barrel section. The fuselage barrel assemblies also include a split longeron, which extends across the barrel joint and is attached to both the first barrel section and the second barrel section. The split longeron includes a first longeron section, which is attached to the first barrel section, and a second longeron section, which is attached to the second barrel section. The split longeron also includes a longeron joint that attaches the first longeron section to the second longeron section. The methods include methods of assembling the fuselage barrel assemblies.

Abstract: A spacecraft attitude control module (1) according to the invention is compact and easy to assemble with additional modules to form an operative attitude control system. The module comprises a robust rectangular, preferably cubic support frame with an attitude control assembly fitted within the confines of the support frame, the assembly including a reference structure comprising a platform, a flywheel support structure (15, 18, 19, 26) and a flywheel (25). The flywheel support structure may be fixed to the platform (10) or it may be a gimbal structure that is rotatable relative to the platform. In the first case the module is a reaction wheel module. In the second case the module is a single gimbal control moment gyroscope module. A preferred embodiment includes a slanted position of the platform (10) relative to the ground plane (100) of the support frame.

Abstract: A wing (5) for an aircraft (1) including a fixed wing (7), a high-lift device (15) and a hold-down arrangement (27) between two supports (23, 25) and having a first hold-down element (29) attached to the high-lift device (15) and a second hold-down element (31) attached to the fixed wing (7). The first hold-down element (29) contacts the second hold-down element (31) when the high-lift device (15) is in a retracted position to prevent a trailing edge (22) of the high-lift device (15) from detaching from an upper surface (19) of the fixed wing (7). One of the hold-down elements (29, 31) is a load-limited hold-down element (32) which is destroyed when loads transmitted through the hold down elements (29, 31) exceed a threshold. Once destroyed, the trailing edge (22) of the high-lift device (15) is not prevented from detaching from the upper surface (19).

Abstract: A drain mast for an aircraft for discharge of water from the aircraft interior with a line which extends in a line direction from a connector end to a discharge end. The connector end can connect to another line in the interior of the aircraft, through which further line water flows into the drain mast. The discharge end can discharge water into a surrounding area of the aircraft. The line includes a plastic, into which a conductive material is embedded, by which the line can be heated electrically, by a heating current being conducted through the conductive material. A proportion of the embedded conductive material in the line increases in the line direction per length unit from the connector end of the line towards the discharge end such that the heating power which is introduced into the line per length unit increases from the connector end towards the discharge end.

Abstract: A disc-type vertical take-off and landing aircraft includes the following. A skirt widens toward the bottom. A disc-shaped rotor is positioned on a lower side of the skirt and rotates with relation to the skirt. A plurality of blades are provided standing on an upper surface of the rotor and are positioned radially from a center of the rotor. A cutout is formed in each of the plurality of blades. When the rotor rotates, centrifugal force causes an airflow along the blade rotating with the rotor, the airflow swirls in a spiral by a flow of air flowing over the cutout of the blade in a direction substantially orthogonal to the blade, the airflow flows in a radial direction of the rotor along the blade while swirling in the spiral, and the airflow ejected downward by the skirt causes ascending.

Abstract: A rotor for a hover-capable aircraft includes an attenuating device to attenuate the transmission of vibrations from a mast to the aircraft. The attenuating device includes a first mass free to oscillate parallel to a hub rotation axis with respect to a casing of the attenuating device and elastically connected to the casing. The attenuating device further includes a second mass free to oscillate parallel to the hub rotation axis, connection means adapted to make the first and second masses integrally movable along the hub rotation axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.

Abstract: The present invention relates to a multi-modal vehicle operable in a first mode as a fixed wing aircraft and reconfigurable to be operable in a second mode as a ground vehicle. The vehicle comprises first and second ends configured to operate in a first direction, with the first end leading the second end, in the first mode and in a second direction, with the second end leading the first end, in normal operation in the second mode.

Abstract: A storage compartment arrangement for a vehicle cabin having a storage compartment, housing, closable storage compartment opening, lower compartment section in the housing, and upper compartment section in the housing. The storage compartment opening extends over the structural heights of both compartment sections. Items of luggage can be placed onto a lower horizontal pivoting edge and pushed into the lower compartment section. An upper horizontal pivoting edge is provided onto which items of luggage can be placed and can be pushed into the upper compartment section. The storage compartment opening has an upper opening edge facing an upper side of the upper compartment section and is adjoined by an auxiliary surface extending over the upper compartment section, is at an angle in a range of 10° to 50° to the separating plane, and, as the distance from the upper delimitation increases, encloses an increasing distance from the separating plane.