Abstract: A landing gear includes a strut and an electromechanical actuator coupled to the strut. The electromechanical actuator includes a motor assembly, a ball nut, a split ball screw disposed between the motor assembly and the ball nut, and an actuator release assembly coupled to the split ball screw.

Abstract: The invention relates to a hydraulic circuit for operating an aircraft landing gear comprising: a general valve (1) for admitting a supply pressure into the circuit; distributors (4, 6) for supplying undercarriages and/or landing gear doors operating actuators (3) or release actuators for hooks (5) maintaining the undercarriages and/or the doors in the retracted position; a depressurization valve (102) for, in an open position, allowing the selective distribution of supply pressure to an extension chamber (3A) or a retraction chamber (3B) of each operating actuator by the distributors, and, in a depressurization position, forcing the return of a retraction chamber of each operating cylinder. According to the invention, the depressurization valve is returned (105) in a stable manner to the depressurization position, and is moved into the open position only in response to the presence of supply pressure downstream of the general valve.

Abstract: A multi-rotor unmanned aerial vehicle (UAV) includes a central body, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, a communication module disposed within the central body and configured to establish a communication channel between the UAV and a remote device, and an indicator light disposed on one of the plurality of branch members. The indicator light is configured to indicate whether the communication channel is established.

Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight thrust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

Abstract: An unmanned aerial vehicle according to various embodiments of the present disclosure comprises: a housing; a wireless communication circuit connected to the housing or positioned in the housing and configured to connect wireless communication with an external controller; a plurality of propulsion systems connected to the housing or at least partially contained in the housing; and a navigation circuit configured to control the plurality of propulsion systems. At least one of the plurality of propulsion systems comprise a motor controlled by the navigation circuit and a propeller assembly connected to the motor.

Abstract: A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off.

Abstract: A rotorcraft that utilizes both a main compound rotor and a plurality of tiltrotors is disclosed. The main rotor and the thrusters can provide vertical lift for vertical take-off and landing of the rotorcraft. The thrusters of the rotorcraft can articulate to a horizontal position to facilitate horizontal flight. The main rotor of the rotorcraft can continue to provide vertical lift for the rotorcraft in horizontal flight, as well as operate in an autorotation mode. In the event of a failure of the main power source of the rotorcraft, the main rotor in autorotation mode can safety land the rotorcraft. In the autorotation mode, the main rotor can create electrical energy that is stored in a battery and can be used to power the plurality of thrusters. The rotorcraft can also be configured in an anti-torque mode, where the thrusters cancel out the torque of the main rotor.

Abstract: The present disclosure pertains to self-piloted, electric vertical takeoff and landing (VTOL) aircraft that are safe, low-noise, and cost-effective to operate for cargo-carrying and passenger-carrying applications over relatively long ranges. A VTOL aircraft has at least one wing that is rotatable relative to a fuselage of the VTOL aircraft for transitioning the VTOL aircraft between a hover configuration and a forward-flight configuration. Rotation of the wing may be passively controlled using aerodynamic forces, thereby obviating the need of using an actuator for actively controlling the rotation.

Abstract: A traction kite anchor device has a base provided at an end of at least one kite line and a release member able to move relative the base by a hand of a user of the kite. A trip arm is pivotally connected to the base to move between a first rotational position relative the base and a second rotational position relative to the base. The trip arm carries a latch that can lock and release a catch of a chicken loop upon moving the release member relative the base.

Abstract: A rotorcraft-convertible motorcar includes a passenger cabin with at least one seat, a pair of front wheels, a central rear wheel, and two pairs of left and right supporting arms located on opposed sides of the passenger cabin, each supporting arm carrying a respective rotor assembly. The supporting arms are pivotally connected to the passenger cabin so that the rotorcraft-convertible car is convertible between an on-road configuration, where the supporting arms with the rotor assemblies are arranged inside a lateral overall size of the passenger cabin, and a flight configuration, where the supporting arms with the rotor assemblies are arranged at least partially outside the overall lateral size of the passenger cabin. The supporting arms and the rotor assemblies are configured so that in the on-road configuration the rotor assemblies are accommodated underneath the passenger cabin, on opposed sides of the central rear wheel.

Abstract: A drone is operated by a sky diver. The drone is interfaced to a parachute pack worn by the sky diver. The sky diver has a device (e.g. smartphone, smartwatch) that communicates with the drone to initiate launch/lift and to release the sky diver. In some embodiments, after the sky diver is released, the drone maneuvers around the sky diver to capture pictures/video of the sky diver. In some embodiments, safety features are included to assure the drone has sufficient battery power to achieve a safe jump altitude above ground level and to assure the release is not made until the drone achieves that safe jump altitude.

Abstract: A management system of a work site includes an image data acquisition unit that acquires image data of an unmanned vehicle stopped at the work site due to generation of a trouble, the image data being imaged by an imaging device mounted in a movable body.

Abstract: The present invention discloses a drone or unmanned aerial vehicle (UAV) mounted on a law enforcement vehicle for the purposes of interfacing with occupants of a stopped vehicle after being pulled over for a traffic violation or routine stop. The drone is equipped with a navigation system, obstacle-avoidance sensors, a telepresence system (a camera, microphone, speaker and screen), and a robotic arm with a secure box and a device for estimating blood alcohol content. Once a suspect vehicle has been pulled over by a law enforcement officer, without leaving the safety of a law enforcement vehicle, the officer deploys the drone to perform a visual check of the interior of the suspect vehicle for dangerous items, ascertain if an occupant's face triggers any flags on a central database, administer a sobriety test, collect the necessary documents and deliver a citation to the driver via the secure box.

Abstract: Container retention and release apparatus are disclosed. An example container retention and release apparatus includes an actuator, a swaybrace coupled to the actuator, and a clamp pivotally coupled to the swaybrace. The clamp pivots between a clamping position to retain a container and a release position to release a container.

Abstract: Container retention and release apparatus are disclosed. An example container retention and release apparatus includes an actuator a swaybrace and retention assembly pivotally coupled to the actuator. The swaybrace and retention assembly pivot relative to the actuator between a first position to retain a container and a second position to release the container.

Abstract: Container retention and release apparatus are disclosed. An example container retention and release apparatus includes a swaybrace to engage an exterior surface of a container. A latch is to attach to an internal receptacle of the container to retain the container. The latch is movable between a latched position to retain the container and an unlatched position to release the container. A drive is to move the latch between the latched position and the unlatched position.

Abstract: Disclosed is a device and method to load stores on an aircraft. The device may include a controller configured to: assign one or more stores to the aircraft; and control at least one actuator to: control a position of the aircraft; load the one or more stores onto one or more corresponding lift portions; position the one or more stores relative to a position of the aircraft determined in accordance with sensor information from at least one sensor; and secure the one or more stores to the aircraft.

Abstract: An aircraft is disclosed, including a fuselage having a longitudinal axis and a passenger compartment having a floor and a ceiling. The aircraft further includes rows of seats fixed to the floor adjacent and aisle and a mobile container suspended from multiple tracks mounted on the ceiling over the aisle.

Abstract: A galley cart has a rear wall with an inlet port and an outlet port. A first divider has a first edge, wherein a first distance is defined between the first edge and a front wall. A second divider has a second edge, wherein a second distance is defined between the second edge and the front wall. The second distance is less than the first distance for control of the flow of cooling air.

Abstract: An occupancy detection system and method for a lavatory includes a door sensor operatively coupled to a door of the lavatory. The door sensor is configured to output a door sensor signal that indicates a status of the door. At least one presence sensor that is configured to output at least one presence sensor signal that indicates an occupancy status of the lavatory. An occupancy detection control unit is in communication with the door sensor and the at least one presence sensor. The occupancy detection control unit is configured to receive the door sensor signal and the presence sensor signal(s). The occupancy detection control unit is configured to determine an occupancy status of the lavatory based on the door sensor signal and the presence sensor signal(s).

Abstract: A two-flow jet engine comprising a high-pressure compressor and a drawing system configured to draw air from said jet engine and send it to an air system, and which comprises a pressurized air supply which draws pressurized air from the high-pressure compressor, a pipe which draws outside air, a turbine of which an inlet is connected to the outlet of the pressurized air supply, and a compressor of which an inlet is connected to the pipe, and an outlet is connected to the air system, and where the rotation of the turbine drives the rotation of the compressor. This particular arrangement makes possible an energy gain by virtue of the combined action of the turbine and of the compressor.

Abstract: Ice protection systems of aircraft and related methods are disclosed. In one embodiment, the system includes a gas-discharge lamp configured to emit infrared radiation toward an inner surface of an aircraft skin and an electric power source operatively connected to the gas-discharge lamp.

Abstract: A conventional parachute requires a velocity pressure during descent in order to open the parachute. As a result, a minimum descent distance and time are required from the beginning to the end of the parachute opening operation and use at low altitude has to be restricted. In order to remedy this issue, an airtight tube and a compressed gas device are provided together in a section of the parachute having the largest annular shape when the parachute has been opened. The tube is annularly expanded by the pressure of the gas, and the parachute is forcibly deployed and opened.

Abstract: A power supply device that supplies power to a power load of a flying body, comprises: a power generation unit; a hollow housing including a reserving portion configured to reserve a fuel of the power generation unit, and a storage portion configured to store the power generation unit; and a connecting portion configured to connect the housing to an airframe of the flying body. The housing has a shape long in a front-and-rear direction of the flying body, and is arranged outside the airframe, and the reserving portion and the storage portion are arranged in a longitudinal direction of the housing.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

Abstract: An aircraft nacelle which comprises a structure, an upstream cowl, an upper cowl arranged to the rear of the upstream cowl and having a starboard-side door and a port-side door, each being articulated between a closed position and an open position, each having a front edge, a rear edge, an inner edge and an outer edge. The nacelle comprises, for each door, an articulation and a locking system. Each door is articulated at the level of its outer edge and, in the closed position, the inner edge of one door is contiguous with the inner edge of the other door. Such a nacelle makes the technicians' work easier because the two articulated doors can be opened wide and give easy access under the cowl.

Abstract: An electric aircraft has a fault-tolerant electrical system designed to optimize competing concerns related to cost, performance, and safety. An electrical system in accordance with some embodiments of the present disclosure has a plurality of power sources (e.g., batteries) that are connected to other electrical components, such as motors for driving propellers or flight control surfaces, by a plurality of electrical buses. Each such bus is electrically isolated from the other buses to help the system better withstand electrical faults. Further, one or more of the electrical buses is connected to motors for driving multiple propellers. Selection of the propellers to be powered by energy received from the same bus is optimized so as to limit the effect of an electrical fault on the stability and controllability of the aircraft.

Abstract: There are described methods and systems for controlling an aircraft. The system comprises a power plant controller configured for controlling operation of an engine and a propeller coupled to the engine, a power throttle having at least one throttle lever to regulate output power of the engine and thrust produced by the propeller, and an autothrottle controller operatively connected to the power plant controller and to the power throttle and configured to modulate engine power without pilot input by causing a change to at least one setting of the power throttle.

Abstract: An acoustic absorption structure includes: at least one acoustic element which has at least one cavity delimited by at least one enclosure comprising at least one first drainage orifice passing through the enclosure, and a rotational indexing system making it possible to position the acoustic element so that at least one first drainage orifice is positioned in proximity to or at a lowest point of the cavity. An aircraft propulsion assembly including such an acoustic absorption structure is also described.

Abstract: An acoustic absorption structure comprising a plurality of resonators. Each resonator comprises a first chamber which has a first mouthpiece delimited by an edge pressed against an inner surface of a porous zone of a skin so that the first chamber and the skin delimit a first cavity, a second chamber, in which is positioned the first chamber, which delimits, with the first chamber, a second cavity, at least one acoustic orifice passing through the first chamber, at least one drainage orifice passing through the first chamber and at least one drainage hole passing the second chamber, each drainage orifice and each drainage hole being configured to limit an accumulation of fluid in the resonator. Also, an aircraft propulsive assembly or an aircraft comprising the acoustic absorption structure are provided.

Abstract: A system and method of controlling a fuel system on an aircraft includes selectively supplying fuel from either a main fuel tank or at least one wing fuel tank to a fuel consumer by varying a speed of at least one main fuel tank pump associated with the main fuel tank relative to a speed of at least one wing fuel tank pump associated with the at least one wing fuel tank.

Abstract: The invention relates to an actuation device (22) for a system (20) including an emergency ram air turbine (21). Said device includes a ram (22) extending along a longitudinal axis (29) and including: a cylinder (30) configured to be connected to an aircraft structure (23) and a piston (33) extending into the cylinder (30) and defining two chambers (31, 32) in the latter. The piston (33) is equipped with a rod (33a) partially extending outside the cylinder (30). Said rod portion extending outside the cylinder (30) is configured to be connected to the emergency ram air turbine (21). The piston (33) is configured to move, relative to the cylinder (30), between a retracted position and a released position, wherein the length of the portion (33b) of the rod (33a) extending outside the cylinder (30) is greater than in the retracted position.

Abstract: The display system has a three-dimensional and curved display surface made up of a single electronic display screen or several joined electronic display screens, the display surface having at least one main zone dedicated to a pilot and suitable for being located in front of said pilot, the main zone being substantially planar or concave, and at least one lateral zone associated with each main zone, each lateral zone being concave and laterally extending the associated main zone.

Abstract: A cockpit pedestal and an aircraft with a cockpit pedestal. The cockpit pedestal includes an integrally-formed frame including an instrument receiving portion defining a plurality of compartments for receiving instruments therein; and a plurality of legs supporting the instrument receiving portion, the plurality of legs being integrally formed with the instrument receiving portion, the plurality of legs being adapted for transferring a load of the plurality of instruments from the instrument receiving portion to a floor of the aircraft cockpit when the cockpit pedestal and the instruments are installed in the aircraft cockpit. In some versions the cockpit pedestal includes a conductive layer electrically grounding the instruments in the cockpit.

Abstract: In an example, an acoustically powered sensor unit for obtaining sensor data indicative of flight characteristics of an aircraft is described. The acoustically powered sensor unit includes a housing having a first portion comprising a diaphragm and a second portion coupled to an exterior of an aircraft and. The diaphragm is configured to receive acoustic energy from an engine of the aircraft. The acoustically powered sensor unit further includes a voice coil actuator disposed within the housing and coupled to the diaphragm. The voice coil actuator is configured to receive kinetic energy by way of a vibration of the diaphragm and responsively generate an electrical power signal. The acoustically powered sensor unit further includes one or more sensors disposed within the housing and powered using energy from the electrical power signal. The one or more sensors are configured to obtain the sensor data indicative of flight characteristics of the aircraft.

Abstract: An aircraft monitoring system includes a sensor operatively connected to at least a portion of an aircraft, a memory configured to store instructions, and a processor disposed in communication with the memory and the sensor. The processor, upon execution of the instructions, is configured to display a graphical representation of the portion of the aircraft reflecting real-time monitoring activity, and display a monitoring controller. A method of providing a graphical user interface (GUI) for an aircraft monitoring system includes displaying a graphical representation of at least a portion of an aircraft's geometry reflecting real-time monitoring activity. The method includes displaying one or more monitoring controllers. Each monitoring controller is associated with at least a portion of an aircraft monitoring system and a location on the aircraft's geometry.

Abstract: A broad good, comprising a plurality of fibers looped randomly throughout the broad good, a binder material binding the plurality of fibers together, the plurality of bound fibers forming a dimensionally stable nonwoven veil, a first metal coating covering a surface of the plurality of bound fibers of the veil, and a second metal coating covering the surface of the first metal coating, wherein the first and second metal coatings form a highly conductive metal screen that follows the shape of the dimensionally stable nonwoven veil.

Abstract: A spark prevention cap is disclosed. The cap forms a sealed cavity around an end of a fastener protruding from a surface of a structure, for example, an aircraft structure. The cap has a cap body with an annular base terminating at a rim. The rim surrounds an opening into a central cavity for receiving the end of the fastener. The annular base has an external circumferential surface extending from the base rim, and a mating feature on the external circumferential surface configured to contact a sealant material applied externally to the cap.

Abstract: A flying machine storage container is provided that comprises multiple charging stations and a clamping mechanism. The clamping mechanism is configured to secure flying machines in the charging stations and securely close charging circuits between the storage container and the flying machines. A system for launching flying machines is also provided. The system comprises two regions and a transition region between the two regions. The two regions each constrain the positioning of a flying machine and the transition region enables a flying machine to move from the first region to the second region to reach an exit. A flying machine having sufficient performance capabilities will be able to successfully launch. Centralized and decentralized communication architectures are also provided for communicating data between a central control system, multiple storage containers, and multiple stored flying machines stored at each of the storage containers.

Abstract: A landing platform for a hovering vehicle comprises an erectable and retractable boundary element which, when in erected position, defines a substantially closed volume.

Abstract: Provided is a passenger boarding bridge for docking a cab with an aircraft. The passenger boarding bridge includes: a tunnel unit; a cab; a drive wheel provided on the tunnel unit or the cab; a rotational mechanism configured to rotate the cab; a controller configured to control the drive wheel and the rotational mechanism; a camera configured to capture an image of an entrance of an aircraft; and an entrance position calculator configured to detect the entrance of the aircraft based on the image and calculate horizontal positional information of the entrance. The controller is, when the cab is at a predetermined standby position from which the cab starts moving at a time of performing docking of the cab with the entrance, configured to: calculate a target position based on the horizontal positional information; and move the cab from the standby position to the target position.

Abstract: A magnetically suspended control moment gyroscope comprising: a gimbal; a flywheel system, set in the gimbal; wherein the flywheel system comprises: a housing; a shaft, arranged in an inner cavity of the housing; a radial magnetic bearing, comprising: a first rotor portion and a first stator portion fixed to the shaft; an upper axial magnetic bearing and a lower axial magnetic bearing, wherein the upper axial magnetic bearing is fixed to an upper end of the first stator portion, the lower axial magnetic bearing is fixed to a lower end of the first stator portion; a wheel body, set in the radial magnetic bearing, fixed to the first rotor portion; an upper axial thrust plate and a lower axial thrust plate, wherein the upper axial thrust plate is fixed to an upper end of the wheel body, and is on an upper end of the upper axial magnetic bearing, the lower axial thrust plate is fixed to a lower end of the wheel body, and is under a lower end of the lower axial magnetic bearing.

Abstract: [Object] To provide a sheet-like structure capable of highly accurately estimating a sheet-like shape. [Solving Means] A sheet-like structure includes a sheet-like member and a plurality of detection sensors. The sheet-like member extends along an in-plane direction orthogonal to a thickness direction and receives light incident on the sheet-like member. The plurality of detection sensors are dispersedly arranged on the sheet-like member along the in-plane direction and are for detecting an incident angle of the light with respect to the sheet-like member at each arrangement position of the plurality of detection sensors.

Abstract: Disclosed is a device for carrying fuel in aircraft and spacecraft. The device includes a carrier element having a longitudinal axis, and a fuel tank with a side wall and a chamber at least partially delimited by the side wall. The tank is arranged in the carrier element. The chamber and the side wall extend in a direction along the longitudinal axis. The side wall has a pressure-receiving component that converts a pressure from the chamber on the side wall into a contraction force acting on the side wall along the longitudinal axis. The contraction force compensates for an expansion force, resulting from the pressure from the chamber and acting on the side wall along the longitudinal axis. This provides an improved device for carrying fuel in aircraft and spacecraft, wherein the aircraft and spacecraft has constant flight mechanical properties because of the device.

Abstract: A method for building an aerodynamic structure, an aerodynamic structure, and a vehicle that includes the aerodynamic structure are provided. The method includes providing a structure with at least one substantially-flat exterior surface. The method also includes attaching blocks of rigid fibrous insulation to the at least one substantially-flat outer surface of the structure. Outward-facing surfaces of the blocks of rigid fibrous insulation extend past a target outer mold line of a final aerodynamic shape. The method also includes machining the outward-facing surfaces of the attached blocks to the outer mold line.

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 flexible container is provided. The flexible container includes four panels. The four panels form (i) a body portion; (ii) a neck portion, and a flare portion that extends from the neck portion; (iii) a tapered transition portion between the body portion and the neck portion; and (iv) the neck portion has a reduced width. The flare portion has an expanded end. The width of the flare portion gradually increases from the neck portion to the expanded end.

Abstract: A system for packaging dosed quantities of solid drug portions comprises a plurality of dosing stations for dispensing a dosed quantity of solid drug portions, a plurality of guiding ducts, a plurality of collecting containers for receiving drug portions guided through the guiding ducts, and at least one discharge and packaging station for transferring drug portions collected by each collecting container to a packaging and for closing the packaging. The guiding ducts are coupled to a transport means for moving the guiding ducts along the dosing stations, wherein each guiding duct is adapted to receive drug portions dispensed from at least one of the dosing stations when the guiding duct is positioned at the at least one dosing station, and to guide the received drug portions to an passage opening of the guiding duct.

Abstract: A method determines a wrapping configuration of a film wrapped around products to form a palletized load to be moved along a path. The method includes using a defined wrapping configuration, measuring physical quantities acting on the load as a result of movements and/or stresses when the load is moved along different test paths, obtaining a path as a suitable composition of base elementary path stretches, obtaining physical quantities acting on the load along the path as physical quantities associated to the base elementary path stretches, positioning the load on a motion platform, operating the motion platform based on the physical quantities to simulate movements and/or stresses acting on the load moved along the path, checking if the load has remained stable and/or compact, modifying the wrapping configuration if the load did not remain stable and/or compact, and repeating the steps.

Abstract: A wrapping machine for wrapping a load with a plastic film includes a main frame with two supporting columns having upper portions interconnected by a beam, a supporting carriage slidingly supported by the main frame and moved along a working direction by first actuating device, a moving ring rotatably supported by the supporting carriage and rotatably driven by second actuating device around a wrapping axis parallel to the working direction, and an unwinding unit fixed to the moving ring and provided with a reel of film and rollers. The first actuating device includes a first actuator arranged to operate a driving shaft rotatably supported by the beam and provided with a driving pulley engaged to a flexible element connected to the supporting carriage. The driving pulley rotates with the driving shaft for moving the flexible element and therefore the supporting carriage along the working direction.