Abstract: A rotor wing aircraft provided with a propulsion apparatus is disclosed. The aircraft has a rotating mast configured to rotate said rotor wing and the apparatus includes a pole mechanically connectable to the rotating mast of the aircraft. At one of the ends of the pole there is placed an electric turbine, powered by a battery, and configured to rotate the pole around an axis of the rotating mast in such a way that the rotation of the pole can be used to rotate the rotor wing. Preferably the pole is made of carbon fiber.

Abstract: A method of facilitating the piloting of a hybrid rotorcraft that comprises a lift rotor and at least one propulsion rotor together with at least one engine operating in compliance with at least one rating. For at least one rating, onboard calculator determines a first power margin of the power plant that is available for the lift rotor and at least one second power margin that is available for said at least one propulsion rotor. A single indicator displays a line together with a first index pointing to said line to illustrate a current operating point of the lift rotor, and a second index pointing to said line to illustrate a current operating point of said at least one propulsion rotor. For each monitored rating, a first symbol is spaced apart from the first index by a first distance illustrating the first power margin. A second symbol is spaced apart from the second index by a second distance illustrating the second power margin.

Abstract: Provided is a floating type moving apparatus capable of safely moving while floating from the ground. A floating type moving apparatus includes: six or more impellers provided below an operator cab, for blasting, downward in a z direction, air taken in from the air intake space between the impellers and the operator cab; six or more motors for driving the six or more impellers; and an electricity storage unit for supplying power to the six or more motors. The floating type moving apparatus is allowed to float from the ground by the air blasted from some or all of the six or more impellers, and the six or more impellers are arranged on the circumference of a circle with the center passing through an axis parallel to the z direction.

Abstract: The invention specifies key small Unmanned Aerial System (sUAS) features which include the tactical mounting of the sUAS to a firearm for rapid access in tactical situations. The invention claims both the fixturing of a sUAS to a firearm and technologies and methodologies to allow for deployment of the sUAS utilizing a single hand of the operator.

Abstract: A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each each satellite and a distributed portion of the weight of the central hub.

Abstract: A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite and a distributed portion of the weight of the central hub.

Abstract: A portable case for an unmanned aerial vehicle (UAV) and a system including a portable case for UAV and an adapter for coupling the portable case to a vehicle are disclosed. An example system may include an exterior attachment disposed on an exterior of a vehicle, an adapter configured to couple a portable case for an UAV to the exterior attachment, and a moveable cover connected to the vehicle and configured to cover the portable case when the portable case is coupled to the vehicle. An example portable case may comprise a landing pad for the UAV, a bottom portion having the landing pad and configured to connect to the exterior attachment via the adapter, and a removable upper portion configured to be connected to the bottom portion when the bottom portion is disconnected from the at least one exterior attachment.

Abstract: An aerial drone for repairing holes or punctures in a membrane on a roof, wherein the aerial drone includes at least one camera for recording a section of the membrane, a 3D printer adapted to print onto the section of the membrane, wherein the 3D printer is controllable wirelessly from a different altitude and/or the ground.

Abstract: [Problem] To provide an aerial vehicle wherein the flight efficiency can be improved. [Solution] An aerial vehicle according to the present invention relates in particular to a aerial vehicle having a loading section whereon a payload and the like can be loaded. The aerial vehicle is capable of traveling at least forward and backward, is provided with lift generation sections, arm sections for holding the lift generation sections, a loading section disposed on the arm sections and positioned posterior to the center of gravity of the aerial vehicle, and a maintaining means for maintaining the aerial vehicle at least in the horizontal attitude, and the loading section has a first connection part for maintaining a loaded object at least in the horizontal attitude.

Abstract: An unmanned aerial vehicle (UAV) includes a central body, a plurality of arms extending out from the central body and in fluid communication with the central body, and a plurality of propulsion units. The plurality of arms are configured to route fluid away from the central body of the UAV. Each propulsion unit attached to a corresponding arm of the plurality of arms.

Abstract: Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

Abstract: Disclosed is a package delivery mechanism for use by an unmanned aerial vehicle (UAV). The package delivery mechanism includes a gravity activated locking mechanism to lock and unlock a package attached to the UAV based on the weight of the package. When the package is attached to suspension means of the UAV that lowers the package to the ground from the UAV, the locking mechanism automatically engages with the package and keeps the package locked to the suspension means, due to the weight of the package. When the package is lowered and reaches on the ground, the weight of the package is offloaded from the suspension means, which enables the locking mechanism to be disengaged, thereby releasing the package. The package delivery mechanism includes a severing module to sever the suspension means from the UAV.

Abstract: A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device. The drone device is able to be implemented in conjunction with a security system.

Abstract: A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device.

Abstract: A flying surface may comprise a plurality of interconnectable flying vehicles configured for mid-flight reconfiguration of the flying surface. Each flying vehicle may be entirely self-sufficient, including an onboard thrust unit, an onboard controller, an onboard power unit, and connectors configured to engage corresponding connectors of other flying vehicles to form a flying surface. The flying vehicles may additionally be configured for self-control, thereby enabling a distributed control model for a flying surface that does not require significant, centralized processing power and corresponding power storage. The flying surfaces may dynamically reconfigure mid-flight by attaching or detaching flying vehicles so as to enable a wide variety of in-flight maneuvers.

Abstract: Methods and systems are provided for remote egg oiling to control avian pest species population through reduction in nesting success. A fluid application system including an oil reservoir, an oil nozzle, a pressurization source, a camera and a targeting laser is provided for accurately dispensing oil onto a clutch of eggs in a nest that is located in hard-to-reach areas such as cliff faces, rock outcrops and artificial structures. Two aerial embodiments are disclosed.

Abstract: An electronic device in an aspect of the present disclosure is an electronic device which is mounted on a seat that is turnable around a first axis such that the electronic device is turnable around a second axis. The electronic device includes a detector that detects acceleration information, and a controller that determines which of a turn around the first axis and a turn around the second axis is occurring based on a temporal change in the acceleration information detected by the detector.

Abstract: A socket insert includes a lower housing section, which incorporates a current infeed terminal, and an upper housing section, which is connected to the lower housing section, upon one of the sidewalls of which a snap-fit connecting part is arranged. The socket insert further comprises a cover plate, which is integrally connected to the upper housing section, closes the upper housing section to the exterior, and incorporates at least one device terminal which is electrically connected to the current infeed terminal. The cover plate incorporates a peripheral cover plate overhang which projects beyond the side walls of the upper housing section.

Abstract: A rail system for fixing fittings in a cabin of a vehicle includes a first elongate rail body with a fixing side for fixing to a vehicle structure, an opposite support side with a support surface for receiving fittings, and a rail cross-section extending between the fixing side and the support side, and several fixing inserts which can be fixed along the support surface. The rail cross-section has two mutually opposing legs which are spaced apart from each other and run perpendicularly to the support surface, and the fixing inserts are configured so as not to protrude beyond the support surface.

Abstract: Systems for securing fixtures to the floor of a transportation vehicle. The securing system has a simplified structure comprising a securing device with two C-profiles comprising a web extending between a top plate and a bottom plate, the profiles being joined by an omega-shape fishplate. Vertical lateral walls formed by the webs of the profiles are perforated.

Abstract: An insert for an air intake of a suction duct, the insert including an inner portion configured to extend within the suction duct, a mating portion configured for sealingly engaging the air intake, and an outer portion configured for extending outside of the suction duct. The inner portion includes a conduit having a central axis extending along an inlet direction at the inlet end and along an outlet direction at the outlet end, the inlet and outlet directions being non-parallel. The outlet end has a smaller cross-sectional area than that of the suction duct. The insert includes an inlet in fluid communication with the inlet end of the conduit. The outer portion includes a curved lip surrounding at least part of an inlet opening of the inlet, the lip configured to direct a flow into the inlet opening and toward the inlet end of the conduit.

Abstract: A parachute assembly for decelerating an occupant of an ejection seat may comprise a left shoulder riser configured to be located over a left shoulder of the occupant upon deployment of the parachute assembly. A right shoulder riser may be configured to be located over a right shoulder of the occupant upon deployment of the parachute assembly. A head restraint, configured to be behind a head of the occupant upon deployment of the parachute assembly, may be located between the left and right shoulder risers.

Abstract: An inflatable head restraint system for a parachute assembly may comprise an inflatable volume configured to inflate in response to a deployment of the parachute assembly. The inflatable volume may be located between a left shoulder riser and a right shoulder riser of the parachute assembly. A conduit may be fluidly coupled to the inflatable volume.

Abstract: A parachute assembly for an ejection seat may comprise a canopy and a first suspension line coupled to the canopy. A first riser may be coupled to the first suspension line. A seat cushion may be coupled to the first riser. The seat cushion may be configured detach from the ejection seat and restrict rearward translation of a head of an occupant of the ejection seat upon deployment of the parachute assembly.

Abstract: A system for translating a head restraint of a parachute assembly away from a head of an occupant supported by the parachute assembly may comprise a chord coupled to the head restraint and at least one of a control line configured to manipulate a canopy of the parachute assembly or a handle coupled to the control line.

Abstract: An inflation control system includes a valve module and a controller. The valve module includes a first valve fluidly connected to a fluid source, a second valve fluidly connected to the first valve, and a pressure regulator fluidly connected to the second valve and an aspirator. The controller is in communication with the first valve.

Abstract: Disclosed is a system for a gas turbine engine, the gas turbine engine comprising a primary shaft, the system including a rotor shaft; a plurality of components connected to the rotor shaft, including a wound field synchronous main machine (MM) and a permanent magnet generator (PMG); and wherein the PMG, alone or with the MM provide torque to change rotational speed of the rotor shaft, thereby changing rotational speed of the primary shaft.

Abstract: A flying drone, which includes: a fuselage composed of a single central body; wings composed of a forward aerofoil and an aft aerofoil, the aft aerofoil being offset in height and in length along the fuselage relative to the forward aerofoil; propulsion powered at least by electrical accumulators and/or photovoltaic cells; and photovoltaic cells essentially covering the upper faces of the forward aerofoil and the aft aerofoil.

Abstract: An unmanned aerial vehicle (UAV) charging control method includes detecting whether a battery of a UAV is electrically connected to an external power supply, disconnecting a load power supply circuit in response to detecting that the battery is electrically connected to the external power supply, and controlling the battery to be charged by the external power supply. The load power supply circuit is configured for the battery to supply power to a load of the UAV.

Abstract: A structure for an aircraft is disclosed including a fixed part, a panel member which is an outer member of the structure, and a plurality of connection units. Each of the plurality of connection units connects the panel member to the fixed part in an articulated manner. The plurality of connection units collectively forms an iso-static connection between the panel member and the fixed part, so that the structure has an invariant geometry. A suspension system, an engine assembly, and an aircraft including the structure are also disclosed.

Abstract: In an embodiment, a rotorcraft includes: a plurality of engines; a flight control computer connected to the plurality of engines, the flight control computer being configured to: receive an operating parameter of a first engine of the plurality of engines; determine an engine output ramping rate for the first engine according to a difference between the operating parameter of the first engine and a nominal limit of the first engine; and increase the output of the first engine in response to detecting an outage of another engine of the plurality of engines, the output of the first engine being increased according to the engine output ramping rate.

Abstract: A set of one or more desired forces or desired moments associated with an aircraft having a plurality of rotor modules is received. A plurality of health metrics associated with the plurality of rotor modules is received. A plurality of commands for the plurality of rotor modules is determined based at least in part on the set of desired forces or desired moments and the plurality of health metrics. The plurality of commands is sent to the plurality of rotor modules where each rotor module in the plurality of rotor modules is configured to perform a corresponding command in the plurality of commands.

Abstract: An intake duct designing method includes: setting a value of a design parameter concerning a design target directed to an aircraft intake duct including a bypass mechanism that suppresses an aerial vibration phenomenon; setting a shape of the design target using the design parameter value; performing computational fluid dynamics analysis including calculating aerodynamic characteristics of the design target and a necessary bypassing flow rate of air released through the bypass mechanism for suppressing the aerial vibration phenomenon, by creating an analytical model for the analysis using the shape of the design target; determining whether an analysis result satisfies a preset design condition; updating the design parameter value when the analysis result is determined as not satisfying the design condition; and repeating the shape setting, the computational fluid dynamics analysis, the determining, and the design parameter value updating, until the analysis result is determined as satisfying the design condit

Abstract: This method of managing the display of an aeronautical map from cartographical data is implemented by an electronic management device and comprises the following steps: acquiring a display scale of the map; determining a set of symbol(s) representative of obstacle(s) to be displayed, the obstacle(s) being included in the cartographical data, where: if the distance between two obstacles is greater than a visible distance threshold that depends on the display scale, two separate symbols are determined for these obstacles, each being representative of a respective obstacle, and if the distance between two obstacles is less than or equal to the visible distance threshold, a symbol representative of a grouping of obstacles is determined for these obstacles.

Abstract: An aircraft area having a textile display, aircraft passenger seat having a textile display, and aircraft including an aircraft area. An aircraft area includes an interior component, a textile display on the interior component and including at least one textile fiber capable of changing a color at at least one section of the textile fiber, and a controller operatively coupled to the textile display and configured to change color of the at least one section of the textile fiber, such that the textile display displays information. An aircraft passenger seat includes a back rest, seat pan, and textile display integrated into a seat cover covering the backrest and/or the seat pan. The textile display includes at least one textile fiber capable of changing a color at at least one section of the textile fiber. An aircraft may include one or more aircraft areas and/or one or more aircraft passenger seats.

Abstract: An exterior aircraft light includes a housing configured to be mounted to an exterior portion of an aircraft; at least one light source mounted to the housing; a lens cover, cooperating with the housing for forming an inner space of the exterior aircraft light, with light from the at least one light source leaving the exterior aircraft light through the lens cover into an outside environment of the aircraft; and a gasket arranged between the housing and the lens cover, the gasket having at least one flap portion forming at least one check valve for fluid discharge from the inner space of the exterior aircraft light towards the outside environment of the aircraft.

Abstract: An aircraft light for a foldable wing tip of an aircraft includes a first lighting structure, including at least one first light source and a first optical system, with the at least one first light source and the first optical system in operation generating a first light output; a second lighting structure, including at least one second light source and a second optical system, with the at least one second light source and the second optical system in operation generating a second light output; wherein the first light output and the second light output are of the same color and wherein the first light output and the second light output are angled with respect to each other; and wherein the aircraft light is configured to control the at least one first light source and the at least one second light source depending on a wing tip orientation signal, which is indicative of an orientation of the foldable wing tip.

Abstract: An exterior aircraft light for indicating a movement of a foldable wing tip between a folded up position and a laterally extended position includes a light source; and a control unit; wherein the control unit is configured to operate the light source to emit a warning light output in response to a warning light control signal indicative of the movement of the foldable wing tip.

Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.

Abstract: Systems and methods are provided for inspecting installation of a fastener. One method includes monitoring hydraulic pressure of a tool that is installing the fastener, detecting that the hydraulic pressure has dropped by more than a threshold amount within a period of time, determining that a pintail of the fastener has snapped in response to the detecting, and reducing the hydraulic pressure in response to the determining.

Abstract: A method for assembling a fuselage section which comprises producing a lower part of the section from at least two panels and an upper part of the section from at least two panels, then assembling the lower and upper parts so as to obtain the fuselage section. A lower or upper mounting support, a gear and a production unit are used in the method.

Abstract: An apparatus includes a head mounted display (HMD) configured to generate sensor data indicative of user inputs. The apparatus further includes a processor configured to communicate with the HMD and a memory coupled to the processor. The memory stores instructions that, when executed by the processor, cause the processor to obtain a data package including technical manual data and one or more visual representations. The instructions also cause the processor to categorize the technical manual data of the data package based on content and formatting of the technical manual data. The instructions cause the processor to select a particular parser based on a categorization of the technical manual data. The instructions further cause the processor to parse, by the particular parser, the technical manual data to convert the technical manual data into converted technical manual data and to generate a data analytics object based on the converted technical manual data.

Abstract: The blade support apparatus relates to capturing and stabilizing airfoils such as helicopter blades to enable ground transport without requiring removal of airfoils or blades with the blade support apparatus and blades in a protective container. The blade support apparatus captures and stabilizes helicopter blades utilizing a support frame with vertical and radial adjustable supports. These supports have contoured padded cradles and means of adjusting the height and angle of the cradles to match the profile being captured. The blade support apparatus enables loading, transport, and unloading of the airfoils for transport in a separate blade container which may either be stand alone or attaches to a helicopter transport apparatus. An alternate embodiment utilizes a support frame which is vertically and radially adjustable. Within the support frame are the same contoured padded swivel cradles which also adjust to the height and angle of the profile being captured.

Abstract: A component equipped with a high-visibility impact detection system. The component includes a composite layer with a minimum impact energy level known to potentially cause damage to the composite layer, a high-visibility layer covering at least a portion of the composite layer, and a top layer covering the high-visibility layer. The top layer is configured to fracture, and expose the high-visibility layer, when subjected to an impact energy level greater than or equal to the minimum impact energy level known to potentially cause damage to the composite layer.

Abstract: There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.

Abstract: Provided is a multilayer heat-insulating material which reduces a deterioration in heat-insulating performance at the periphery of a mounting means for mounting on a mounting subject and which facilitates deformation into a desired shape. This multilayer heat-insulating material comprises a heat-insulating member (2) in which heat-insulating sheets (2a) and spacers (2b) are laminated, an engagement sheet (3) provided adjacent to the heat-insulating member (2), heat-insulating member engagement fixtures (5) for penetrating through and engaging the heat-insulating member (2) and the engagement sheet (3), and a mounting member (4) that is provided on the engagement sheet (3) and that can be removably attached to a mounting subject (9). Engagement of the heat-insulating member engagement fixtures (5) is such that the layers of the heat-insulating member (2) do not adhere to each other.

Abstract: A kitting machine is disclosed. In various embodiments, the machine includes an actuator configured to move a surface or receptacle to a position associated with item retrieval; and a controller configured to control operation of the actuator to position an item in the position associated with item retrieval, in a manner that is synchronized at least in part with operation of a robotic retrieval device configured to retrieve the item from the position associated with item retrieval.

Abstract: A roll of sanitary tissue product that includes a shaped line of weakness, wherein the roll of sanitary tissue product exhibits a roll compressibility of from about 2% to about 10%, and a Full Sheet Tensile Strength of between about 400 g and about 850 g, as measured by the Full Sheet Tensile Strength Test Method.

Abstract: A cable tie mounting tool comprises an upstream jaw and a downstream jaw having concave guidance path portions for the strap of a cable tie, a placing mechanism configured to place a cable tie portion along the common concave guidance path by pushing it strap-end-first along the common concave guidance path starting at the upstream end of the upstream jaw and pushing it in downstream direction, an insertion mechanism for feeding the cable tie strap end of the placed cable tie through the head of the placed cable tie, and a tightening mechanism for tightening the cable tie and possibly cutting it. Also provided is a length adjustment mechanism for adjusting the length of the common concave guidance path.

Abstract: Described herein is an arrangement (1) for guiding a wire in a wire binding machine (3), wherein the arrangement (1) comprises a guide member (5) and a first spring (7) arranged to act with a first spring force against the guide member (5), wherein the guide member (5) is arranged to bear against the wire and act against the wire with said first spring force in order to guide the wire during a wire binding process when the wire moves relative to the guide member (5). The guide member (5) is arranged so that a movement of the guide member (5) substantially away from the wire is allowed in order to reduce friction forces between the guide member (5) and the wire during the wire binding process, so that locking of the wire against the guide member (5) is prevented. Also described herein is a wire binding machine (3) comprising an arrangement (1).