Abstract: A rotor for a hover-capable aircraft is described that comprises: a drive mast; a hub operatively connected to the drive mast and rotatable about a first axis; and at least two blades hinged to the hub, via a rigid or elastically deformable connection, so as to be able to assume an attitude rotated about and/or translated along at least a second axis with respect to said hub; the aircraft further comprising sensor means configured to detect the attitude of at least one said blade with respect to the hub; the sensor means are configured to acquire an optical image associated with the attitude of the blade with respect to the hub.

Abstract: A multirotor aircraft with an airframe and at least one wing that is mounted to the airframe, the at least one wing being provided with at least four thrust producing units that are arranged in spanwise direction of the at least one wing, wherein each one of the at least four thrust producing units comprises at least one rotor assembly that is accommodated in an associated shrouding, the associated shrouding being integrated into the at least one wing, wherein the associated shrouding defines an air duct that is axially delimited by an air inlet region and an air outlet region, wherein the air inlet region exhibits in circumferential direction of the air duct at least two different aerodynamic profiles.

Abstract: An elastic torsion element for connecting a rotor blade to a rotor hub of a rotor, the elastic torsion element comprising at least two elastically deformable plates, wherein each one of the at least two elastically deformable plates comprises fiber reinforced polymers, wherein respective fibers of the fiber reinforced polymers of each one of the at least two elastically deformable plates are at least arranged along one of a first and a second dominant fiber directions, wherein the first dominant fiber direction crosses the second dominant fiber direction in a predetermined fiber direction crossing region, and wherein the elastic torsion element comprises an integrated elastic lead-lag hinge that is formed at the predetermined fiber direction crossing region.

Abstract: A rotor assembly has a composite driveshaft extending between a transmission and a yoke for providing torque from the transmission to the yoke to cause rotation of the yoke and a plurality of rotor blade assemblies attached thereto. The rotor hub also has a composite static mast coupled to the yoke and a frame. The static mast being configured to carry the lift and thrust forces from the yoke to the frame.

Abstract: A VTOL aircraft has a substantially delta-shaped lifting body fuselage with airfoils disposed along all three sides. In vertical flight mode the airfoils act as exhaust diverters. A flow of exhaust gas flows from a centrally located vertical flight gas diffuser over the top surface of the lifting body and then is directed downward by the airfoils to provide vertical lift. In vertical flight mode, the entirety of the exhaust from the engine is diverted to the vertical flight gas diffuser by means of a transition duct that diverts the flow of gas through a 90° upward bend into the vertical flight gas diffuser. In horizontal flight mode the transition duct is fully retracted to permits the entirety of the engine thrust to be directed rearward to propel the aircraft in a horizontal flight mode.

Abstract: A kite control bar having a tensioning member anchored to the bar end float and secured to the trim line. The tensioning member is capable of expanding and contracting. The tensioning member has a default state which is either an expanded state or a contracted state. When an adjusting force is exerted upon the trim line, the tensioning member is drawn into another of the expanded state or the contracted state. When the adjusting force is released, the tensioning member tends to return to the default state. This biases the trim line to force excess trim line out of the bar end float.

Abstract: Devices and methods for transporting and storing a drone. Polycarbonate or material of similar resiliency is used to create a casing for the drone body. Stationary wing or retractable wing drones can be protectively coupled and attached to objects for transportation. The casing is comprised of a hood to cover the top of the drone and a carriage to receive the sides and bottom of the drone. The device allows quick access and greater versatility in storage and transportation of drones.

Abstract: A drone capture aerial vehicle includes a fuselage and a drone capture device. The drone capture device includes a middle post and a plurality of foldable frame arms; the middle post includes a first end and a second end; and each foldable frame arm includes a plurality of ribs and a plurality of links. A method of capturing a drone includes providing a drone capture aerial vehicle, the drone capture aerial vehicle having a drone capture device and the drone capture device having a foldable capture net; flying the drone capture aerial vehicle toward the drone; activating the drone capture device to deploy the foldable capture net; and capturing the drone with the capture net.

Abstract: A method for evaluating damage and providing passenger assistance in emergency events involving mass transit vehicles (MTVs), especially emergency events occurring in a tunnel, includes: (a) providing, on-board the MTV, at least one unmanned aerial vehicle (UAV), each UAV including a controller comprising a processor and memory; (b) determining, by the controller of the UVA while on-board the MTV in the tunnel, a change in at least one of the following: an acceleration, positive or negative, greater than a predetermined acceleration, an angle greater than a predetermined angle, a temperature greater than a predetermined temperature, and the presence of particles, gas or both greater than a predetermined concentration; (c) in response to the determining in step (b), the UAV separating from the MTV and becoming airborne within the tunnel; and (d) following step (c), executing, by the UAV, flight movement of the UAV within the tunnel.

Abstract: This invention is directed toward an aerodynamically designed drone with a unique angle of propulsion. The drone uses airfoil design to move more efficiently through the air, and the aerodynamic design is optimized when the drone is tilted forward at various degrees of “tilt” to provide the most aerodynamic profile to the oncoming air. The invention contemplates single hull, double hull and triple hull designs, and is applicable to heaving lifting drones, drones use for photography and remote sensing, and racing drones.

Abstract: An unmanned aerial system (UAS) may comprise an unmanned aerial vehicle (UAV) configured to display advertising. The UAV may include a connector configured to attach to a display screen. The display screen may be configured to receive data from the UAV and display a message based on the data. The UAS may be controlled by a remote control, which may command the UAV to display a specific message. The remote control may control the flight of the UAV as well as the functionality of the one or more components. The components attached to the UAV, may include a camera, a robotic arm, or a display screen. The UAS may be configured to, for example, display advertising messages in a predetermined area, display advertising messages in response to the UAV determining a specific event or recognizing a specific person, and/or launch fireworks.

Abstract: An unmanned aerial vehicle includes a platform configured to transport a second unmanned aerial vehicle and release the second unmanned aerial vehicle in response to satisfying a condition. The unmanned aerial vehicle includes a hybrid generator system including an engine configured to generate mechanical power; and a generator motor coupled to the engine and configured to generate electrical power from the mechanical power generated by the engine; and at least one rotor motor configured to drive at least one propeller to rotate, wherein the at least one rotor motor is powered by the electrical power generated by the generator motor.

Abstract: A passenger assistant system includes an artificial intelligence processing unit, a sensor interface, a flight crew interface, a passenger interface, and at least one end effector. The sensor interface couples the artificial intelligence processing unit with at least one sensor configured to provide environmental information regarding a cabin of an aircraft. The flight crew interface couples the artificial intelligence processing unit with at least one flight crew input. The passenger interface couples the artificial intelligence processing unit with at least one passenger input. The at least one end effector is coupled to the artificial intelligence processing unit. The artificial intelligence processing unit is configured to direct the at least one end effector to perform at least one task responsive to information acquired from one or more of the sensor interface, flight crew interface, or passenger interface.

Abstract: An aircraft passenger seat with dynamic seat back breakover including a pivotally-attached seat back element and a seat back breakover mechanism including an articulating weighted inertia linkage operable for coupling the seat back element in a first operating condition in which the seat back element is movable between an upright taxi takeoff and landing (TTOL) position and a reclined position, and decoupling the seat back element in a second operating condition to allow the seat back element to move forward past the upright position, the first operating condition corresponding to inertial loading below a predetermined threshold value and the second operating condition corresponding to inertial loading above the predetermined threshold value.

Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, and a turbine coupled to the compressor via the shaft. The turbine receives and expands a first medium to provide power to the compressor via the shaft. The compressor receives and compresses a second medium in accordance with the power provided by the turbine via the shaft. The turbine is fluidly coupled to a heat exchanger of an air conditioning system.

Abstract: A fan wheel rotatably arranged around an axis in a fan duct. The fan wheel includes a first side, a second side including an inner periphery forming a fan wheel inlet, and an outer periphery and at least four curved wings. The at least four wings extend between the inner and outer periphery of the second side and between the first side and the second side, such that channels are formed between the wings and the first and second side. The inner periphery of the second side is arranged at a first distance from the second side and the outer periphery of the second side is arranged at a second distance from the first side, such that the cross-sectional area of the channels at the inlet and the cross-sectional area of the channels at the outlet are substantially equal. Also, a heater including such a fan assembly.

Abstract: A heater assembly includes both a carbon allotrope heating element for ice protection and a metallic carrier material for lightning strike damaged protection. The carbon allotrope heating element is formed on the metallic carrier material to create an integrated heating and lighting protection assembly.

Abstract: Anti-icing methods and aerodynamic structures having laminated resistive heaters for de-icing are described. Several of the inventive aspects utilize laminated resistive heaters comprising a carbon nanotube layer and/or capacitors to store and supply electricity. The invention also includes methods of making aerodynamic structures having de-icing or anti-icing functionality.

Abstract: A system includes a signal monitor to monitor a time rate of change of a revolution per minute (RPM) trim signal that is received from an RPM command path to control a velocity of a helicopter rotor. An icing detector detects for the presence of ice accumulation on the helicopter rotor by comparing the time rate of change of the RPM trim signal to a predetermined threshold for the time rate of change.

Abstract: A parachute system includes a release that detachably couples a self-propelled projectile and parachute canopy to each other. The release detaches the two from each other in response to a triggering of the release. There is also a first path between the release and a payload where the first path includes the parachute canopy and a suspension line between the parachute canopy and the payload. At least part of the suspension line is bound such that the first path is effectively shorter than a second path. In response to the first path being drawn taut, the suspension line becomes unbound so that the first path becomes effectively longer than the second path. In response to the second path being drawn taut after the suspension line becomes unbound, the release is triggered.

Abstract: In an embodiment, a parachute deployment system includes a parachute coupled to a release via a first load path. The first path includes crown lines. The release is adapted to attach the parachute to a rocket via the crown lines, and disengage the parachute from the rocket if a load shifts from the first path to a second path. The system also includes a line constrainer between the release and the parachute. The crown lines pass through the line constrainer, and the line constrainer is adapted to restrict an extent to which the crown lines are able to extend away from a longitudinal axis. An example release includes a back plate configured to couple a tow line to crown lines and a soft pin. The pin is adapted to separate from the back plate in response to tensioning of the release line, causing the parachute to disengage.

Abstract: A slide for an evacuation system may comprise an inflatable slide rail structure. An aspirator may be fluidly coupled to the inflatable slide rail structure. An aspirator retention strap may be coupled between the aspirator and the inflatable slide rail structure. The aspirator retention strap may comprise an elastic material. The aspirator retention strap may be configured to stretch when a predetermined internal pressure threshold of the inflatable slide rail structure is exceeded.

Abstract: An aircraft with a jet engine that has a radially outer engine cowling and an auxiliary gear appliance that has multiple auxiliary devices and that can be driven by a shaft that is in operative connection with an engine shaft that rotates about a central axis. The auxiliary gear appliance is arranged in the radial direction of the jet engine at least partially outside the outer engine cowling of the jet engine.

Abstract: A jet engine with a linking device for linking the jet engine at an element of an aircraft optionally in a first mounting position and at least one second mounting position, and with at least one operating equipment appliance that has a first fluid area and a second fluid area. In the first mounting position, the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality. In the second mounting position, the fluid areas are assigned to the respectively other functionality. What is further described is an aircraft with at least one such jet engine.

Abstract: A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

Abstract: A nacelle may comprise a fan cowl and a tie rod assembly coupled to the fan cowl. The tie rod assembly may comprise a first tie rod coupled to the fan cowl and a second tie rod coupled to the first tie rod and the fan cowl. Rotational motion may be transferred between the first tie rod and the second tie rod. A retention structure may be coupled to an interior surface of the fan cowl.

Abstract: A manufacturing method is provided. During this method, a panel is provided that includes non-conductive material and a plurality of conductive elements at least partially embedded within the non-conductive material. The conductive elements include a first conductive element. An electric current is applied to the first conductive element such that the first conductive element produces a signature. A location of the first conductive element in the panel is determined based on the signature. An aperture is formed in the panel based on the determined location of the first conductive element.

Abstract: An aircraft engine air inlet lip takes an annular form about a longitudinal axis and delimits an air inlet stream, and includes: a wall having a U-shaped profile having an outer face oriented towards outside of the air inlet lip and an inner face oriented towards interior of the air inlet lip, an inner wall extending inside the wall between two zones of the inner face, so as to close an inner chamber delimited between the wall and the inner wall and filled with a gas, the inner wall having an upstream face oriented towards and a downstream face oriented away from the inner chamber, a fan configured to move the gas contained in the inner chamber, and at least one pipeline fixed to the upstream face and extending all around the air inlet lip and configured to be fed with a heat transfer fluid heated by a heat source.

Abstract: A structural panel is provided that includes a first core structure and a second core structure. The first core structure is configured with a first endwall and a plurality of first cavities that extend vertically through the first core structure. The second core structure is configured with a second endwall and a plurality of second cavities that extend vertically through the second core structure. The second core structure is laterally bonded to the first core structure at a complex splice joint between the first endwall and the second endwall.

Abstract: An aircraft is provided that includes a fuel storage tank for aviation fuel, and avionics systems interconnected by an avionics bus. The fuel storage tank receives aviation fuel during a fuel uplift for a flight according to a flight plan that includes and depends on a predicted fuel burn determined based on a reference lower heating value (LHV) of the aviation fuel. The avionics systems include temperature and density sensors, and a flight management system (FMS). The temperature and density sensors measure respectively the temperature and density of the aviation fuel. The FMS receives the measurements, estimates an actual LHV that is different from the reference LHV based on the measurements, and determines an adjusted predicted fuel burn for the flight based on the predicted fuel burn and the actual LHV. The FMS displays the adjusted predicted fuel burn and enable adjustment of the flight plan based thereon.

Abstract: The present general inventive concept relates to a system of method having an electronic flight display that meets the FAR 23.1311(b) regulatory requirement for redundant backup instruments in the cockpit. The present general inventive concept also provides a system and method to detect failures, obstructions, or improper operation of the aircraft pitot pressure sensing system using a combination of dissimilar sensor data that is independent from each other, e.g., allocated from different sources and employed for different purposes on different displays, and displays information on an avionics display screen.

Abstract: Method and apparatus to reduce static pressure measuring error are disclosed.

Abstract: A method for determining actual aircraft ground speed may comprise receiving a reference ground speed value; receiving a wheel speed value of a nose wheel of an aircraft; comparing the wheel speed value of the nose wheel and the reference ground speed value; and/or determining the actual aircraft ground speed based on the reference ground speed value and the wheel speed value.

Abstract: An airspeed indicator display for an aircraft having a main rotor system and a translational thrust system includes a first indicator operable to display an actual airspeed of the aircraft and a second indicator positioned adjacent the first indicator. The second indicator is operable to display an actual pitch angle of the translational thrust system.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: Embodiments include techniques for an automated aircraft landing analysis, the techniques includes requesting landing information corresponding to a current landing, wherein the landing information includes historic average landing information, and receiving the landing information. Techniques also include retrieving recorded aircraft system parameters corresponding to the current landing, and calculating a landing distance for the current landing. Techniques include calculating a deviation of the calculated landing distance for the current landing, and displaying results of the calculated deviation.

Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.

Abstract: Distributed monitoring systems and data synchronization methods are provided for monitoring a vehicle, such as a rotorcraft. One exemplary method involves a mobile device broadcasting measurement synchronization messages corresponding to a measurement window to measurement units onboard the vehicle over a wireless network, obtaining synchronization timestamp data corresponding to the measurement synchronization messages from each of the measurement units, obtaining measurement data obtained during the measurement window from the measurement units, and associating samples of measurement data from a first measurement unit with one or more samples of measurement data from a second measurement unit based on the synchronization timestamp data.

Abstract: A penetration device including a casing, a propellant positioned in the casing, and a flyer plate. The flyer plate is coupled to the casing and adjacent to the propellant. The flyer plate includes a center portion having a substantially constant first thickness and includes a peripheral portion around the center portion and defining an edge. The peripheral portion tapers from the first thickness to a second thickness at the edge, where the second thickness is less than the first thickness.

Abstract: A penetration device including a casing, a propellant positioned in the casing, and a flyer plate. The flyer plate is coupled to the casing and adjacent to the propellant. The flyer plate includes a center portion having a substantially constant first thickness and includes a peripheral portion around the center portion and defining an edge. The peripheral portion includes one or more recesses in a first surface of the peripheral portion.

Abstract: A multifaceted instrument console for use by an operator. In one embodiment, an instrument console for a vehicle comprises a primary mounting surface positioned directly in front of an operator of the vehicle, and a plurality of auxiliary mounting surfaces each being contiguous with the primary mounting surface or another one of the auxiliary mounting surfaces. Each of the auxiliary mounting surfaces is angled with respect to a contiguous mounting surface toward the operator.

Abstract: Flame deflectors for rocket launchpads have historically been constructed on-site by spraying on a layer of refractory cement material, resulting in large monolithic structures which lack durability and are vulnerable to degradation by ambient weather. By assembling together a plurality of metal modules and refractory material modules, one obtains a flame deflector structure whose set of modules is matched to an expected heat distribution pattern of the exhaust from the rocket to be launched. Further, modules can be prefabricated at another location, under controlled conditions, and subsequently installed. In case of damage during a launch, any damaged modules can be swapped out and replaced by new modules, thereby minimizing cost and downtime before a subsequent launch event. The modules can be made more weather-resistant by applying an epoxy sealant to their rocket-facing surfaces.

Abstract: An automatic packager including a cartridge and a cartridge mechanism is provided. The cartridge for the automatic packager includes a reservoir for storing a plurality of medications and a wheel including a bottom portion placed in the reservoir. The cartridge also includes a scooping member provided on the wheel to rotate with the wheel and singulate a medication from the reservoir. The cartridge mechanism for the automatic packager includes a platform configured to receive a medication from a cartridge and a camera system. The cartridge mechanism also includes an electronic processor coupled to the camera system configured to dispense the medication from the cartridge in response to determining that the expected medication is delivered to the platform and return the medication to the cartridge in response to determining that the expected medication is not delivered to the platform.

Abstract: A device for shaping the gable surfaces of packages with a slanted gable is shown and described, including: a conveyor system with cells fixed to it to receive the packages, at least one gable folder to fold a fin seam in the gable region of the packages and at least two ear folders to fold ears in the gable region of the packages. In order to enable rapid and reliable shaping of the gable even in packages with slanted gables, it is proposed that both the gable folder and the ear folders be mounted movably relative to the conveyor system and the packages to be transported therewith. A method for shaping the gable surfaces of packages with a slanted gable is also shown and described.

Abstract: Described and depicted is a method for forming package bodies open on one side from package sleeves open on both sides for the manufacture of filled packages, in which the package sleeves are folded flat and held ready for further processing in a stack around at least two folding edges running in the longitudinal direction of the package sleeves, in which the flat-folded package sleeves are transferred successively from the stack to a forming station, in which the package sleeves are unfolded in the forming station, in which the package sleeves are pulled in the forming station through a channel coming into contact with the two opposite folding edges of the package sleeve and tapering transversely to the package sleeve and/or the package sleeves are positioned in the forming station between at least two form halves of a form and unfolded by closing the form, and in which the unfolded package sleeves are slid from the forming station onto a mandrel for closing, in particular sealing, a longitudinal end of the

Abstract: Provided is a method for packaging piece good groupings, in which a plurality of piece goods, particularly containers, are at least partially interconnected by a first connector, wherein at least two-piece goods of this plurality are directly interconnected by the connector. According to the embodiment, this plurality of piece goods connected by the connector is packaged with a second connector in the form of a second wrapping element, and said plurality of piece goods connected by a first connector is conveyed by a conveyor device to a packaging device and enclosed, particularly wrapped, with the second wrapping element by said packaging unit.

Abstract: A tool for sealing overlying courses of a strap that includes a gripping unit, a power supply unit detachably affixed to one end of the gripping unit, and a motor in the gripping unit. A cam is coupled to the motor and a notching unit is coupled to the cam by a plurality of linkages.

Abstract: Provided is a method for packing arrangements of piece goods, in which a plurality of piece goods and particularly containers are at least partially interconnected by a first connection device, at least two-piece goods of said plurality of piece goods being directly interconnected by the connection device. According to the embodiments, this plurality of piece goods connected by means of the connection device is packed with a second connection device in the form of a second wrapping element and the plurality of piece goods connected by a first connection device is transported to a packaging device by a transport device and surrounded and particularly wrapped by said packaging device with the second wrapping element.

Abstract: Disclosed is a method for transferring products, to or from a product collection surface of a product processing line, on which they can accumulate, in which method products are stored in trays. The method includes a loaded tray transfer step, during which a tray, namely the collection tray, is separately moved between the collection surface and a receiving zone, where tray conveyor is provided, as well as a product transfer step, during which products are transferred between the collection surface and the collection tray with a planar sweeping movement, while the collection tray is held flush with the collection surface. Also disclosed is a corresponding device for transferring products.

Abstract: A packaging machine for grouping individual package units, the packaging machine comprising a feeder, a conveying system, a grouping station and a labeler. The packaging machine is configured to stack at least three package units one on top of the other to form a package stack and to encompass the package stack, at least partially, with a label. The label may comprise one or two labels, wherein the label sections are pressed against the top of the package stack and folded around the side and bottom of the package stack to secure the sections together. The packaging machine may further comprises a press plunger that presses at least one hinge-like tab formed on a main surface of the label onto a side face of a central package unit of the package stack to further secure the packages in the stack.