Abstract: In one aspect the subject matter herein describes a cable tilt actuator for an aircraft propulsion unit. One embodiment comprises: a cable spool, fore and aft cable sections, a compression beam, a compression beam guide, and a linear actuator. As the linear actuator drives the compression beam, relative rotation is imposed between the compression beam and the spool. Described, in one aspect, is an embodiment configured to tilt an aircraft propulsion unit.

Abstract: An exemplary tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode includes tiltable rotors located at forward boom ends, tiltable ducted fans located at wings aft of the forward boom ends, and aft rotors located on aft boom portions.

Abstract: An aerial vehicle having more basic structure and safety measures. The aerial vehicle according to the present invention includes a thrust unit having a plurality of rotary vanes for generating thrust, a tail, a fuselage that connects the thrust unit and the tail, a main wing provided in a substantially center of the fuselage, and a control unit for controlling at least the main wing. When the aerial vehicle makes a landing, the control unit controls the main wing so that a part of the main wing becomes a lower end.

Abstract: Disclosed is a transformable wing, which comprises: a main wing including multiple ribs extending in the forward and backward direction of the wing wherein the multiple ribs are arranged at intervals in a lengthwise direction of the wing; and a span morphing part including an auxiliary wing extending in the lengthwise direction, a scissors part connected to one end of the auxiliary wing in the lengthwise direction, and a driving part for extending or reducing the scissor part in the lengthwise direction.

Abstract: A modular blended wing body (BWB) aircraft includes common components containing a nose structure having a left aft edge and a right aft edge intersecting on a centerline of the BWB on one end and intersecting on a leading edge of the BWB on another end, and two wing structures attached to the nose structure, wherein the at least two rear structures includes a left-wing structure arranged on the left side of the centerline, wherein the left-wing structure includes a left forward edge, and a right-wing structure arranged on the right side of the centerline, wherein the right-wing structure includes a right forward edge, and wherein the left-wing structure and the right-wing structure are laterally symmetrical to the centerline, and wherein there is no clear demarcation between the at least two wing structures and the nose structure of the plurality of common components of the BWB aircraft.

Abstract: An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body.

Abstract: Aircraft assemblies comprise an aerostructure, a sealing structure, and a flexure spring. The aerostructure comprises an end surface. The flexure spring is operably coupled between the aerostructure and the sealing structure and is configured to urge the sealing structure away from the end surface of the aerostructure. The flexure spring has a neutral configuration and a range of deflected configurations. The flexure spring is biased toward the neutral configuration.

Abstract: A sealing device for covering an aperture in a wing part of an aircraft is disclosed having an interface section for fixedly mounting the sealing device to a surface of the wing part adjacent the aperture, a connecting section, and a cover section for covering at least a part of the aperture. The connecting section is arranged between the interface section and the cover section and connects the interface section and the cover section. The connecting section is adapted to resiliently hold the cover section in a predetermined orientation relative to the interface section to cover at least a part of the aperture. The cover section comprises a contact portion for contacting a surface of an actuation element that protrudes through the aperture.

Abstract: A method for stabilizing drones performing a mid-air package transfer. One or more processors detecting the proximity of a second drone to a first drone. Interference of air pressure between rotors of the first drone and rotors of the second drone is detected by data from sensors included on the first and second drone. Positions of the rotors of the first drone are adjusted by moving rotor arms in a first direction and the rotors of the second drone are adjusted by moving rotor arms of the second drone in a second direction that increases separation between the rotors of the first drone and the second drone, and the amount of separation is based on reduced interference of air pressure between rotors of the first and second drone. Responsive to determining completion of a package transfer, the positions of the rotors are adjusted to original positions.

Abstract: An agricultural chemical spraying drone with improved safety is provided. The drone includes an altitude measurement sensor and a speed measurement sensor and controls not to exceed an altitude restriction and a speed restriction of an airframe by using a flight controller. The sensors are desirable be combination of multiple types. Particularly, the altitude is desirably measured by a GPS during take-off and by a sonar during chemical spraying. Weight of the airframe is measured from time to time, and the altitude restriction and the speed restriction may be adjusted according to the weight.

Abstract: Described is a passenger seat assembly that may include a seat back including a rearward surface, a seat shroud positioned proximate to the rearward surface of the seat back and fixedly coupled to a seat frame, wherein the seat shroud remains stationary as the seat back moves between a stowed position and a deployed position, and at least one moveable shroud member coupled to the seat shroud at an attachment point and positioned proximate a rearward surface of the seat shroud, wherein a location of the attachment point is adjustable.

Abstract: A method of manufacturing a metal component with an anti-microbial molecular layer may comprise: disposing the metal component in a piranha solution; washing the metal component; and grafting a surface of the metal component with a Si-Quat or hybrid Si-Quat molecular layer.

Abstract: An aircraft cabin (100) is disclosed. The aircraft cabin (100) comprises a plurality of pairs of seat units (120) positioned along an aisle (101). Each aisle seat unit (122A) comprises an aisle seat (125A) and an aisle footwell (126A) and each non-aisle seat unit (123A) comprises a non-aisle seat (127A) and a non-aisle footwell (128A). The aisle seat unit (122A) and non-aisle seat unit (123A) are positioned with respect to one another such that the aisle seat (125A) faces towards a first end of the cabin (100) and has direct access to the aisle (101), the non-aisle seat (127A) faces towards a second, opposite end of the cabin (100). The aisle seat unit (122A) is oriented at an angle with respect to the non-aisle seat unit (123A) to provide the non-aisle seat unit (123A) with an aisle access path (129A) between the non-aisle seat (127A) and the aisle footwell (126A).

Abstract: An offset leg assembly for a passenger seat for a vehicle such as an aircraft is provided. The leg assembly can include a base leg portion having a lower end configured to operably couple to a seat track coupling assembly and an upper end opposite the lower end, and an upper leg portion coupled to a lateral side of the upper end of the base leg portion, the upper leg portion having an aperture configured to receive a base frame tube of the passenger seat. The upper leg portion can be positioned laterally offset from the seat track coupling assembly along the base frame such that the upper mounting location on the base frame tubes is not vertically aligned with the lower mounting location to the aircraft fuselage attachment points.

Abstract: A cooling system of a vehicle including an inlet for receiving a medium and a turbo-generator fluidly connected to the inlet. The turbo-generator includes a turbine operably coupled to a generator by a shaft. The turbine has a turbine inlet and a turbine outlet, the turbine inlet being fluidly coupled to the inlet. The medium is ram air.

Abstract: An electric power system for a vehicle includes at least one electric machine, one or more power rectifiers, and a plurality of DC channels. The at least one electric machine includes a plurality of tooth-wound multi-phase windings that are substantially magnetically decoupled, and the at least one electric machine is mechanically balanced even if one of the plurality of windings is de-energized. The one or more power rectifiers are configured to produce rectified power from the power generated by the at least one electric machine. The plurality of DC channels are formed after the at least one power rectifier and are configured to provide DC power to one or more loads within a vehicle.

Abstract: A motor-integrated fan 1 including one or more motors integrated therein comprises: a shaft part 11 which serves as a supporting system disposed at the center of a rotational axis; a rotation part 12 which is a rotating system rotating about the shaft part 11; a duct 13 which serves as a supporting system provided on the outer periphery of the shaft part 11; and a motor 14 which rotates the rotation part 12, wherein the rotation part 12 comprises: a plurality of blades 32 rotatably supported at least on the shaft part 11 and rotating thereabout, the blades 32 being arranged in a circumferential direction of the rotational axis I; and a rotation support ring 33 connected on one side of each of the blades 32 in a radial direction of the rotational axis, the rotation support ring 33 supporting the plurality of blades 32.

Abstract: One example provides a method for generating and using electric power in a hybrid power system for an aircraft. The hybrid power system has an engine and a high-voltage DC (HVDC) bus interconnecting a generator-motor system, an AC distribution system, and a DC distribution system. The method comprises operating the engine through a plurality of different operation phases. The method further comprises selectively providing, based on thrust demands of the engine, electric power from the HVDC bus to the generator-motor system to assist the engine in providing thrust. The method further comprises selectively extracting, using the engine driving the generator-motor system with a high-pressure spool (HPS) shaft and/or a low-pressure spool (LPS) shaft of the engine, electric power from the engine. The method further comprises selectively delivering the electric power extracted from the engine to the AC distribution system and/or the DC distribution system.

Abstract: A hybrid aircraft power plant includes an air mover for propelling an aircraft, a gas turbine engine operable to drive the air mover, a bifurcated exhaust duct conveying combustion gas from the gas turbine engine, and an electric motor mounted to the exhaust duct and operable to drive the air mover. The turbine engine includes a turbine extracting energy from an annular stream of the combustion gas and being rotatable about a rotation axis. The exhaust duct includes a first branch conveying a first portion of the combustion gas toward a first direction away from a rotation axis of the turbine, and a second branch conveying a second portion of the combustion gas toward a second direction away from the rotation axis.

Abstract: Methods, apparatus, systems and articles of manufacture for mounting a gas turbine engine are described. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Abstract: A propulsion unit for an aircraft, includes a support structure, a nacelle and a turbomachine. The support structure is configured to independently support, on the one hand, the turbomachine and, on the other hand, preferably by a cradle, an air inlet and/or a rear section of the nacelle.

Abstract: This invention pertains to reliable, lightweight and efficient hybrid electric powertrain and components thereof to power hybrid electric aircraft from one or more sources of electrical energy. In particular, a novel architecture is proposed for power panels that receive, condition and distribute high levels of electrical power to and from the propulsion electric motors and the one or several sources of electrical energy. Systems and methods for architecting the power panels using efficient, reusable and modular power electronics building blocks (PEBBs) is described, along with additional systems and methods for the optimal control of the power panels and components thereof. In addition, novel systems and methods are described for the efficient and lightweight thermal management for hybrid electric powertrain components, ranging from distribution manifolds for the powertrain or power panels, to micro fluid channels for cooling electronics with extreme heat flux.

Abstract: A casing system mounted between an upstream solenoid valve of an upstream pipe and a downstream solenoid valve of a downstream pipe and which has a casing divided by a separation wall into a first volume which is placed under reduced pressure and a second volume, a heat exchanger which is fixed inside the casing with a first inlet which is arranged in the first volume and which is connected to the upstream pipe and a first outlet which is arranged in the second volume and which is connected to the downstream pipe, and a control unit which closes the solenoid valves if the deviation between two successive values of the pressure in the first volume or in the second volume is greater than a threshold.

Abstract: An aircraft emergency guidance assembly adapted to be mounted in an aircraft cabin comprises a longitudinally extending layer of photoluminescent material and a cover over the photoluminescent material. The assembly has a height and a width and a ratio of the width to height is from 0.5:1 to 3.5:1.

Abstract: An aircraft vibration detecting device applicable to an aircraft having a moving surface to be driven by an actuator includes a difference calculating unit for calculating a difference between a target value of an angle of the moving surface and an actual measured value of the angle of the moving surface, a threshold value determining unit for determining whether an absolute value of the difference is equal to or greater than a threshold value, and a vibration determining unit for determining that the moving surface is vibrating if the absolute value of the difference is equal to or greater than the threshold value.

Abstract: A system for monitoring impact on an electric aircraft is presented. The system includes a sensor communicatively connected to a flight component, wherein the sensor is configured to detect a measured force datum and generate an impact datum as a function of the measured force datum. The system further includes a computing device configured to simulate a landing performance model output as a function of the impact datum, generate a landing performance datum as a function of a comparison between the landing performance model output, determine an alert datum as a function of the landing performance datum, and display the landing performance datum on a user device.

Abstract: Systems and methods are provided for assembling aircraft fuselages. One embodiment is a method for assembling a fuselage of an aircraft. The method includes indexing an arcuate section of a fuselage to a frame installation station, feeding a frame at the frame installation station into a concavity defined by the arcuate section, placing the frame against an Inner Mold Line (IML) of the arcuate section while the frame is within the concavity, and affixing the frame to the arcuate section.

Abstract: A turbine engine cleaner assembly comprising: at least one drive block coupled to a driver for rotatably driving said at least one drive block, said at least one drive block comprising at least one passageway having an inlet and an outlet, said inlet coupled to a pneumatic supply; and a wiper comprising at least one paddle, said at least one paddle having at least one inflatable bag detachably mounted thereto, said at least one paddle adapted to be detachably mounted to said at least one drive block so that when air is received in said inlet, it passes into and through said at least one passageway and said outlet to inflate said at least one inflatable bag, said at least one drive block rotatably driving said at least one paddle so that said at least one paddle is rotatably driven.

Abstract: First and second signals respectively associated with first and second motors are obtained. First and second motor wear metric that respectively represent an amount of wear associated with the first and second motors are determined based at least in part on the first and second signals, respectively. It is determined whether at least one of the first or second motor wear metrics exceeds a failure threshold. The VTOL vehicle is automatically prevented from performing a vertical takeoff attempt if least one of the first or second motor wear metrics exceeds the failure threshold. The first and second rotors are respectively positioned at first and second angles relative to a horizontal plane, at least during a hovering mode of the VTOL vehicle. The first and second angles are different angles. The first and second motors are respectively associated with the first and second rotors.

Abstract: An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.

Abstract: A database (102) of a rocket launch assistance device records orbit forecast information of a mega-constellation satellite group (301) that is acquired from a space information recorder included in a mega-constellation business device and space object information that is acquired from a rocket launch business device. The orbit forecast information of the mega-constellation satellite group (301) is composed of a prediction value of an orbit of at least one representative satellite (331) out of the mega-constellation satellite group (301) and a prediction value of an orbit of a constituent satellite (332), which is a value relative to the prediction value of the orbit of the representative satellite (331).

Abstract: An orbital satellite has a pair of multi-axis booms including both thrusters for course/attitude adjustment and an end effector for grappling payloads and manipulating other tools and objects. The satellite may launch with a primary payload affixed to a bus and one or more secondary payloads affixed to an ESPA ring. Once in orbit, the end effector may be used to grapple the primary and/or secondary payloads and rearrange them on the bus. In further aspects, the end effector may be used to make bus repairs or take measurements, or hold tools that are used to make bus repairs or take measurements.

Abstract: The present invention relates to an assembly apparatus for assembling components of spacecraft in space. The assembly apparatus includes: a core platform; and a mobile platform including an end effector configured to perform an assembly or manufacturing task. The mobile platform is connected to the core platform by a tether. The core platform includes a body and a coupling element connected to and extendable from the body such that the coupling element may be spaced from the body of the core platform. The tether connects the mobile platform to the body via the coupling element. The assembly apparatus further includes an actuator configured to vary the length of the tether extending between the coupling element and the mobile platform to control the position of the mobile platform relative to the body of the core platform.

Abstract: Disclosed are an apparatus and method for controlling an aerial vehicle. The apparatus includes a camera that obtains an terrain image during flight, a sensor that obtains scan information of a landing point of the aerial vehicle, and a controller that estimates a location of the landing point based on the terrain image if it is determined that the landing point is recognized in the terrain image, determines whether an obstacle exists at the landing point based on the scan information, and determines whether landing of the aerial vehicle is possible based on a determination result.

Abstract: A Remote Drop Zone Atmospherics and Marking Platform provides wind speed and direction information to parachutists or operators who are using parachutes to deliver a parachutist or autonomous load to the ground.

Abstract: A transformable Unmanned Aerial Vehicle (UAV), can operate as a coplanar hexacopter or as an omnidirectional multirotor based on different operation modes. The UAV has 100% force efficiency for launching or landing tasks in the coplanar mode. In the omnidirectional mode, the UAV is fully actuated in the air for agile mobility in six degrees of freedom (DOFs). Models and control design are developed to characterize the motion of the transformable UAV. Simulation results are presented to validate the transformable UAV design and the enhanced UAV performance, compared with a fixed structure.

Abstract: Provided includes the main body part 100 in which a number of rotors 101 controlled by the control unit 110 are installed on the outside, a number of wing bodies 200 in which the elastic member 220 is opened to both sides to absorb the impact in the event of a collision with the guide 210 placed on the outer side of the rotor 101, a parachute deployment unit 300 installed on the upper side of the main body part 100 and ejecting the parachute canopy 320 upward in an emergency situation, a lower airbag ejection unit 400 installed under the main body part 100 and inflating the lower airbag 401 downward in an emergency situation, and a landing gear unit 500 installed under the main body part 100.

Abstract: An adaptable lattice structure (110, 120, 130, 140) for a an Unmanned Aerial System, UAS, comprising: a plurality of lattice voxels (100, 102), wherein each lattice voxel (100, 102) comprises: a plurality of same shape elements (10, 12); wherein each same shape element (10, 12) comprises a plurality of connector elements (20), wherein the plurality of connector elements (20) are configured to temporarily couple a first same shape element (10) to at least a second same shape element (12); wherein the plurality of same shape elements (10, 12) are configured to be temporarily coupled so as to form a three dimensional lattice voxel (100); and wherein at least one of the connector elements (20) on a first lattice voxel (100) is configured to temporarily couple the first lattice voxel (100) to a second lattice voxel (102) after the formation of the first lattice voxel (100) and the second lattice voxel (102).

Abstract: The present invention relates to a drone having a movable propeller shaft, the drone comprising: a drone body having an opening formed thereon; a plurality of propeller shafts arranged radially on the drone body, each propeller shaft having one side portion passing through the opening of the drone body to be disposed inside the drone body and a propeller housing equipped with a propeller and a propeller motor; adjustment means disposed on the drone body, linked to the plurality of propeller shafts, respectively, and configured to adjust the respective angles and heights of the plurality of propeller shafts; a sensor for sensing a rotation angle of each of the plurality of propeller shafts; and a motor driver connected to each propeller, a current check circuit for determining whether current flow is normal, an MCU for transmitting and receiving signals in connection with the current check circuit and transmitting signals to the motor driver, and a main controller connected to the MCU through a wireless commun

Abstract: A stage has a takeoff and landing surface. The takeoff and landing surface has an opening through which loading and unloading to and from a flying object is carried out. The takeoff and landing surface has a plurality of markers formed thereon. Each marker is a figure or the like for identifying a relative position between the flying object and the stage. The opening is formed in the takeoff and landing surface such that an edge of the opening does not cross the markers.

Abstract: A drone port is portable to be disposed on a landing surface for a drone and includes a covering section configured to cover the landing surface and provided with markers of different sizes. The covering section includes a restraining section configured to restrain the drone on the covering section. The restraining section includes a first hook-and-loop fastener disposed on the covering section. The first hook-and-loop fastener is configured to join with a second hook-and-loop fastener configured to be disposed on the drone.

Abstract: A robot system and a method for packaging coils of sheet metal is provided. The method and robot system for coil packaging, having two industrial robots, each robot being provided with a robot arm provides for a solution where the direction of travel along the envelope surface of the coil is inclined relative the rotational axis of the coil, positioning of the roll of wrapping material in three-dimensional along the circumferential edge may be adjusted for each pass and/or where the positioning of the longitudinal axis of the roll or wrapping material is in an inclined angular direction relative the direction of rotation.

Abstract: A method of forming an automatic dishwashing pouch comprising the steps of: providing a sheet of material (10); identifying one or more regions of the material; heating the material with a heating device having a non-uniform heating profile, the non-uniform heating profile arranged to heat the identified region(s) to a greater temperature than other regions of the material; and forming the material in a mould to form the automatic dishwashing pouch, the automatic dishwashing pouch including a plurality of cavities (12).

Abstract: A component mounting system including: a component mounting device group in which a plurality of component mounting devices that mount components supplied to a board transported in from an upstream side by a tape feeder and transport out the board to a downstream side, and cut a carrier tape after supplying the components by a cutter device and discharge scraps of carrier tape, are installed on a floor surface while being arranged in a direction of conveying the board; a main conveyor that is installed along an arrangement direction of the plurality of component mounting devices in a region on the floor surface under the component mounting device group, and transports the scraps of carrier tape discharged from each of the plurality of component mounting devices; and a scraps storage that is installed outside the region and stores the scraps of carrier tape transported by the main conveyor.

Abstract: A cutting, crimping and stacking machine that is capable of performing automatically cutting, crimping and stacking conical cornet cone packages by itself.

Abstract: A horizontal form, fill and seal (HFF&S) machine having a different package format in the forming section than in the fill and seal section.

Abstract: A device (6) for the insertion of flat good units (2, 3, 31) into a transport container (8, 81) includes an insertion module (63) for the insertion of flat good units (2, 3, 31) into a transport container (8, 81), a feed module (61) for feeding flat good units (2, 3, 31) to the insertion module (63), and a first identification module (65) for identifying flat good units (2, 3, 31). The feed module (61) includes a horizontal conveying device (613), by which flat good units can be conveyed along a conveying path. The identification module (65) is configured to determine the identity of a flat good unit.

Abstract: Various embodiments of the present disclosure provide a wrapping machine that includes an indicating device including one or more light sources configured to project a visible wrapping-zone indicator. The wrapping-zone indicator includes a boundary at least partially surrounding a wrapping zone of the wrapping machine to indicate the wrapping zone.

Abstract: A holder for consumables for use in an analyzer is disclosed. The holder has one or more receptacles for receiving a stack of consumables. The consumables are wrapped in packaging and are placed in the holder as a stack of packaged consumables. The receptacles have a height sufficient to receive the stack of consumable. The receptacles have an opening miming along the side of the receptacle for the entire portion of the height of the receptacle that receives the stack of consumables. The receptacles have a proximal end and a distal end. The proximal end is the end of the receptacles into which the stack of consumables is place and from which the consumables are removed. The distal portion of the receptacles support the stack of consumables in the receptacles.

Abstract: A cross seal device 100 is provided. The device 100 comprising a cross sealing table X having a cross sealing station (A) and a toggle assembly (B). The cross sealing station (A) comprising a front seal assembly (1) and a rear seal assembly (2) configured to engage and disengage by controlled oscillation of first pair of C shaped actuator levers (6c, 6d) and second pair of C shaped actuator levers (6a, 6b) via sealing drive shaft (5) of toggle assembly B. The cross sealing station (A) performs horizontal reciprocating action for sealing. The cross sealing device 100 further comprising Cross Sealing Up Down control assembly C which controls vertical reciprocating movement of cross sealing table X employing Stripping System D to ensure no PIS (Product in Seal) and improves packaging capacity.