Abstract: The present invention belongs to the technical field of subsea equipment, and specifically pertains to a thrust reversal type emergency jettison device for an underwater vehicle. A thrust reversal type emergency jettison device for an underwater vehicle, comprises a thrust reversal mechanism, the thrust reversal mechanism comprises a casing and a gas reaction compartment provided in the casing; the gas reaction compartment communicates with a gas passage in a shell of the casing through a gas pipe; and a bottom end cover is provided at a bottom of the gas reaction compartment, and the bottom end cover is hermetically connected with the gas reaction compartment through a cylinder mechanism, and falls off automatically when a gas pressure in the gas reaction compartment increases.

Abstract: A jet-propelled boat includes a power unit that applies a propulsive force to a ship body by injecting water taken in from a water inlet while pressurizing the water, a position detection unit that detects a position of the ship body, a determination unit that determines whether or not an operation mode is a fixed position mode, and a power control unit that controls the power unit based on detection information by the position detection unit so that a position of the ship body falls within a target range including a specific anchor position in a case where the determination unit determines that the operation mode is the fixed position mode.

Abstract: The present invention relates to a sliding bracket device for a guide motor, which is located on the bow or stern of a boat to connect the guide motor to the boat, the sliding bracket device including: a fixed frame part disposed on the bow or stern of the boat; and a slide frame part sliding on top of the fixed frame part and configured to allow the guide motor to be disposed thereon, wherein if the slide frame part slides in one side direction thereof, the guide motor is located inside the boat, and if the slide frame part slides in the other side direction thereof, the guide motor is located outside the boat.

Abstract: A boat maneuvering system includes an operating unit including an operator, and a controller configured or programmed to control a magnitude and a direction of a propulsion force generated by a propulsion device of a boat in response to an operation performed on the operating unit. When a hold start operation is performed on the operating unit during boat maneuvering using the operator, the controller shifts to a first boat maneuvering state to perform a hold control to hold a control index that is at least either one of an index correlated with the magnitude of the propulsion force generated by the propulsion device or a velocity of the boat. When a steering operation is performed on the operator in the first boat maneuvering state, the controller changes the direction of the propulsion force generated by the propulsion device while maintaining the first boat maneuvering state.

Abstract: An example reusable high-altitude balloon system includes a balloon with a first end supporting a payload and a second end with an aperture and an apex fitting that is positioned within the aperture. A clamp applies a pressure to a plurality of pleated folds formed in the perimeter of the aperture around the apex fitting to form an air-tight seal against the balloon at the perimeter of the aperture. The reusable high-altitude balloon system further includes control circuitry that controllably releases the apex fitting from the balloon to initiate a descent sequence.

Abstract: A door sill protector includes a base rotatably mounted to a door sill via a hinge. The hinge allows the base to be rotated between a stowed position and a deployed position. A plurality of support feet are disposed on an underside of the base. Each of the support feet is pivotable for pivoting between an extended orientation and a retracted orientation. A linkage bar is mechanically coupled to the support feet such that the support feet collectively pivot in unison between the extended orientation and the retracted orientation.

Abstract: A system and method for unlatching an aircraft door is disclosed. The system includes a latch pin design which enables retraction of the pin in the event the ordinary unlatching mechanical systems fail. The system includes the use of a rod that is reversely threaded on each side. Rotation of the rod either extends or retracts the pin.

Abstract: An aircraft door system and related closure method. The system involves the use of a ball transfer device as an initial contact made in the closing of an aircraft door. The closing door next encounters guiding and fitting arrangements are also employed to laterally align the lower portion of the aircraft door with the corresponding portion of the frame upon the closing. Finally, the closing door then encounters load path ties which are employed about the door. The arrangement above allows the door refit the door within what is a deformed doorframe due to weight and structural considerations.

Abstract: An aircraft floor including a structure, a deck attached to the structure, and first and second sealing barriers superposed at least in line with a protection zone, the deck being configured to form the first sealing barrier at least in line with the protection zone. The second sealing barrier includes a sealing tarpaulin interposed between the deck and the structure and having several reinforcing strips fixed against a face of the sealing tarpaulin oriented toward the structure, at least some of the reinforcing strips being interposed between the sealing tarpaulin and longitudinal reinforcements of the structure of the floor.

Abstract: A wing assembly is disclosed having a fixed wing portion, a high-lift device, and a connecting assembly movably connecting the high-lift device to the fixed wing portion, such that the high-lift device is movable between a retracted position and at least one extended position. The connecting assembly includes a first connecting element, which extends from a first end portion, at which the first connecting element is rotatably connected to the fixed wing portion, to a second end portion, and a second connecting element, which extends from a first end portion, at which the second connecting element is rotatably connected to the second end portion of the first connecting element, to a second end portion.

Abstract: A wing (3) for an aircraft (1) including a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5). The trailing edge high lift assembly (9) includes a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5). The connection assembly (13) includes an actuator unit (35) moving the flap (11) between a retracted position and at least one extended position. The flap (11) includes a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) pivotable about a pivot axis (31).

Abstract: An electromechanical transmission apparatus for actuation systems for guidance systems of an aircraft, includes a planetary gear system configured to provide a kinematic transmission between a driving element and an output shaft. The planetary gear system includes a central sun gear planet gears coupled rotatably to a planet carrier, and an external ring gear; furthermore having an electromechanical brake and a viscoelastic damper, the electromechanical brake being configured to lock and release selectively the viscoelastic damper and the central sun gear so that the electromechanical transmission apparatus can be configured: in an active configuration, and An electronic control unit is configured to control the electromechanical brake so as to make the transmission apparatus pass from the active configuration to the passive configuration when a locking condition of the driving element occurs.

Abstract: An electromechanical actuator comprises: a motor; a gearbox; an anti-extension device mounted between the motor and the gearbox. The motor and anti-extension device are mounted on a housing of the actuator. The actuator further comprises a screw shaft; a nut mounted on the screw shaft; an output rod connected to the nut, the output rod having a linear range of motion defined between full extension of the output rod at a first end point (A) and full retraction of the output rod at a second end point (C). The screw shaft, nut, and output rod are located in a cavity of the housing. The output rod and nut are held against rotation relative to the housing, such that rotation of the screw shaft drives the output rod to move linearly within the housing.

Abstract: Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft can be sensitive to uneven weight distributions, e.g., the payload of an aircraft is primarily loaded in the front, back, left, or right. When the aircraft is loaded unevenly, the center of mass of the aircraft may shift substantially enough to negatively impact performance of the aircraft. Thus, in turn, there is an opportunity that the VTOL may be loaded unevenly if seating, luggage placement, and/or positions of internal components are not coordinated. Among other advantages, dynamically assigning the payloads and adjusting components of the VTOL aircraft can increase VTOL safety by ensuring the VTOL aircraft is loaded evenly and meets all weight requirements; can increase transportation efficiency by increasing rider throughput; and can increase the availability of the VTOL services to all potential riders.

Abstract: A method for adjusting the angular position of a wheel, in particular a wheel of a landing gear on an aircraft. The wheel being connected to at least one hydraulic cylinder controlled by a servo valve. The method comprising a step for determining an angular deviation between a measurement of the angular position and a setpoint angular position, a first proportional correction step, a second integral correction step and a step for adding the first current and the second current in order to determine a control current of the servo valve. The second integral control step comprising a sub-step for limiting the second current according to a parametric law imposing a second current of zero value when the angular deviation is less, in absolute value, than a first determined threshold.

Abstract: A helicopter active noise suppression device integrating a sound array and on-propeller control, which relates to the technical field of helicopter noise reduction, includes an annular loudspeaker array, a plurality of force exciters, an error microphone, an Active Noise Cancellation (ANC) controller, a cockpit sensor, and an airborne computer. The annular loudspeaker array is arranged at a rotor hub and unsteady force exciters are arranged at each blade trailing edge to construct a sound field in an reversed phase to the sound wave of an original sound field with an ANC principle, thereby counteracting the noise and realizing the noise reduction of all-domain and all-type helicopter noise.

Abstract: One embodiment is a rotorcraft comprising a fuselage; an empennage at an aft end of the fuselage; a tail rotor connected to the empennage; and a tail rotor guard (TRG) around the tail rotor, the TRG shrouding to the tail rotor; and a light emitting diode (LED) lighting element integrated into at least one surface of the TRG.

Abstract: One embodiment is an apparatus for inhibiting accidental contact by a human with a tail rotor connected to an empennage of an aircraft. The apparatus includes an inverted V-tail connected to an empennage of the aircraft forward of the tail rotor, the inverted V-tail stabilizer comprising a first V-tail stabilizer on a side of the empennage to which the tail rotor is connected and a second V-tail stabilizer on a side of the empennage opposite the side of the empennage to which the tail rotor is connected; and a shroud bar having a first end connected to an outboard end of the first V-tail stabilizer and a second end opposite the first end connected to the empennage aft of the tail rotor, wherein a horizontal distance from the shroud bar to the tail rotor is greater than a length of an arm of the human.

Abstract: In a front view of this aircraft, there is an over-lap portion where at least a part of a fuselage and at least a part of two cruising rotors overlap, and a rear portion of the fuselage has an inclined surface which is displaced downward from upward progressing from the front to the rear, such that the area of the overlap portion gradually becomes smaller progressing from the front to the rear.

Abstract: There is provided an arming apparatus for a store, the apparatus comprising: a first attachment system and a second attachment system; a linking connector coupled with the first attachment system and the second attachment system; and an arming clip; wherein each of the first attachment system and the second attachment system comprises: a first frangible connector coupled with the arming unit and the linking connector; and a second frangible connector comprising a first end coupled with the linking connector and a second end comprising a clip, the second end being configured to pass through a lug of said store and then couple to the second frangible connector.

Abstract: A system for deploying a payload from an aerial vehicle onto a target surface includes a delivery device that is detachably couplable to the aerial vehicle. The delivery device includes an elongated shaft comprising a proximal end and a distal end, a plurality of fins extending along the plurality of the shaft, and a payload holder coupled to the distal end of the elongated shaft. The delivery device may additionally include an attachment portion and a floatation device. The payload holder may be detachably coupled to the payload such that the delivery device detaches from payload upon impact at the target surface. The system may additionally include a release mechanism for detachably coupling the delivery device to the aerial vehicle. The release mechanism includes a receiver and a dropper device. The release mechanism may be remotely controlled by an operator to release the delivery device from the aerial vehicle.

Abstract: This invention relates to a body (2) exposed to air flow during the flight of the respective air vehicle, at least one ammunition (M) fired to attack a target, at least one machine cannon (3) enabling the ammunition (M) to be fired, at least one ammunition duct (4) on the body (2), enabling the ammunition (M) to be placed therein and the ammunition (M) to be transferred to the machine cannon (3), and a butt line (BL) arranged so as to extend lengthwise on the air vehicle and symmetrically divide the air vehicle in two.

Abstract: A doorway side guide system includes a base mechanically coupled with a bottom portion of a doorway. A mounting member is rotatably coupled to the base via a hinge for rotating between a deployed position and a stowed position. A contact member is mechanically coupled with the mounting member via a pivot such that the contact member is configured to rotate about the pivot. The contact member extends outside of the doorway in the deployed position for guiding cargo through the doorway and for protecting a doorframe of the doorway.

Abstract: Technology is described for providing electronic sponsor pages to passengers on an aircraft. An interface control and an inflight interactive environment may be combined at a server on the aircraft. The interface control may be associated with an electronic sponsor page and may enable a passenger on the aircraft to access the electronic sponsor page through the inflight interactive environment. The inflight interactive environment may be sent from the server to a client device onboard the aircraft over a network connection for display on the client device. A selection of the interface control included in the inflight interactive environment may be received. The electronic sponsor page may be sent from the server to the client device for display. The electronic sponsor page may include a sub-interface enabling access to one or more electronic objects.

Abstract: In accordance with at least one aspect of this disclosure, a contoured class divider for dividing an aircraft cabin arrangement between at least one forward passenger seat and at least one aft passenger seat, includes a panel positioned adjacent to and rearwardly of the at least one forward seat. The panel has a contoured shape for receiving the back of the forward passenger seat in at least one of a reclined position and an upright position. The panel extends substantially from an underside of an overhead bin to a cabin floor. In embodiments, at least a portion of the panel is configured to deform or break during a crash event due to one or more of a head impact by a passenger in the aft passenger seat with the panel and/or inertial forces of the crash event acting on the panel.

Abstract: A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

Abstract: The present invention relates to an aircraft seat unit, comprising: a seat that can be moved between a seated position and a reclining position and a privacy shield extending at least partly around the seat, the privacy shield comprising a fixed portion and a movable portion that can be moved relative to the fixed portion, the movable portion being movable between: a retracted position in which the movable portion delimits, with the fixed portion, a partially enclosed space around the seat to give the passenger privacy and a deployed position in which the movable portion is at a distance from the seat so as to free up space for accessing the seat.

Abstract: An environmental control system for an aircraft includes a first inlet configured to receive recirculation air from a cabin of the aircraft, a second inlet configured to receive fresh air and a manifold for mixing the recirculation air with the conditioned fresh air to form mixed air. The ECS further includes a contaminant removal system configured to remove contaminants from the mixed air to form cabin air and an outlet configured to supply the cabin air to the cabin. The ECS further includes a controller configured to receive air quality information from an air quality sensor, the controller configured to control the contaminant removal system based on the air quality information.

Abstract: Disclosed is a guided mannequin aerial unit. The mannequin includes a control unit having a central processing unit (CPU), memory for storing a computer software instruction set for execution by the CPU, a high-resolution camera for taking and providing to the CPU real time images of the drop area and a second memory unit for pre-storing images of the mannequin drop area and the drop target. Under the control of the software instruction set, the CPU compares the real time images to the pre-stored images to guide the mannequin to the drop target.

Abstract: In an aircraft that flies utilizing power generated by an engine or power charged in a battery, a temperature control system includes a battery that stores power for starting the engine and flying, a temperature adjusting apparatus for warming or cooling the battery by each of at least the power charged in the battery and power feeding from an external power source, and a control section for detecting presence or absence of the power feeding, and if the power feeding is present, controlling the apparatus to warm or cool the battery using the power feeding, and if the power feeding is absent, controlling the apparatus to warm or cool the battery using charged power of the battery. Even if the power feeding has been lost, it is possible to maintain a temperature and a state of charge of the battery enabling the engine to start and fly.

Abstract: A method is provided for operating an aircraft system. During this operating method, a plurality of drive units are provided that include a thermal engine drive unit and an electric machine drive unit. A mechanical load is powered using a first of the drive units. The first of the drive units includes a first rotating structure. A parameter of the first rotating structure is monitored. A failure of the first of the drive units is detected based on the monitored parameter. A switch is made from the first of the drive units to a second of the drive units to power the mechanical load where the failure of the first of the drive units is detected.

Abstract: A hybrid-electric or all-electric powertrain may include a power control unit electrically coupled to an energy storage system. The power control unit may determine a power level command based at least in part on a power level request for the powertrain, and a power level-UCL and/or a power level-LCL. The power level-UCL and/or the power level-LCL may be based at least in part on an aggregate obverse power level request representing a requested power level for one or more obverse powertrains electrically coupled to the energy storage system. The power level commands may be limited by the power level-UCL and/or the power level-LCL. The power level-UCL may be set equal to either an available discharge power capacity or an apportionate discharge power capacity. The power level-LCL may be set equal to either an available storage power capacity or an apportionate storage power capacity.

Abstract: 1. A vertical takeoff and landing vehicle which includes an allocation block that receives a set of desired forces or desired moments and a health metric associated with at least one of: (1) a motor controller or (2) a rotor that operates in a vertical takeoff and landing mode at least some of the time. A command signal is determined per a first manner that attempts to satisfy both the set of desired forces or desired moments and the health metric. If the command signal is unable to be determined in the first manner, a second manner is used that prioritizes flight control associated with one or more of a roll axis or a pitch axis over flight control associated with a yaw axis where the axes are mutually orthogonal. The command signal is output to the motor controller that controls the rotor using the command signal.

Abstract: A method is provided for operating an aircraft system. During this method, an electric machine of an electrical system is operated onboard an aircraft. A first set of electrical system waves produced by the electrical system is sensed. A set of electrical system attenuation waves is produced to attenuate a second set of electrical system waves produced by the electrical system in response to sensing the first set of the electrical system waves.

Abstract: The monitoring system (1) is used for detecting an incapacitation of the pilot of an aircraft, said aircraft being equipped with a piloting device (40) which can be actuated manually by the pilot. Same includes: at least one pressure sensor integrating a contact sensor (11, 12) mounted on the surface of the piloting device (40), so as to generate an elementary indicator when a pressure exerted by the pilot on the piloting device is adapted to the use of the piloting device; and a computing unit (2) programmed for processing the elementary indicator delivered by the pressure sensor and for determining a current state of the pilot and, when said current state corresponds to an incapacitation of the pilot, for issuing an alarm.

Abstract: An aviation integrated optics and lighting unit for securing to a light receptacle of an aircraft. The aviation integrated optics and lighting unit comprises a housing, a light-emitting device, and an optical sensor. The light-emitting device is secured to the housing. The optical sensor is positioned in the housing and is configured to capture optical data.

Abstract: This disclosure relates generally to aircraft tugs, which assist in the movement of small aircraft. More specifically, this disclosure relates to a remote power switch, which may also be referred to as an emergency tug shutoff (ETSO) switch, for remotely stopping movement of an aircraft tug. Systems that include such an aircraft tug and at least one remote power switch are also disclosed, as are methods for remotely stopping an aircraft tug.

Abstract: The present invention relates to a test system (1) for at least one aircraft navigation instrument (3), said system comprising: a test device (5) capable of being connected to at least one sensor on which the navigation instrument relies to provide a value, said test device being configured to test said sensor by changing its state; a database comprising at least one predetermined value corresponding to a value to be provided by said navigation instrument when said test device changes the state of said at least one sensor associated with said navigation instrument.

Abstract: A sampling system includes a sampler, a projector, a camera, an arm, and a controller with the sampler, projector, and camera being located at the distal end of the arm. The projector projects a reference mark including a line with a predetermined shape onto a ground surface and the camera captures images of the projected mark. The controller is configured to obtain the size of the projected line based on the camera images. The controller adjusts the projector height position based on the line size and specifies a sampling point for inserting the sampler based on the camera images of the projected mark.

Abstract: A display system can be configured to identify a space object and an object alert associated with a change in one or more movement parameters of the space object. The system can generate data configured to display a display region and an object alert indicator within the display region. The system can display the object alert indicator at a location within the display region and display, within a second display region, a listing of a plurality of alerts comprising the object alert. The system can receive a user selection of an alert from the plurality of alerts configured to be displayed in the second display region and automatically generate updated data configured to display an updated display region based on the user selection of the alert. The updated display region can include a panned, rotated, and/or zoomed perspective of the display region.

Abstract: The present invention relates to an unmanned aerial vehicle and a self-destruct drone operating system including the same, and according to an unmanned aerial vehicle related to one example of the present invention and a self-destruct drone operating system including the same, it can overcome gravity, descend vertically to a target at a high speed, and be precisely guided, by rotating a propeller of a rotor in the reverse direction.

Abstract: An apparatus, system, and/or method for carrying a power line device from an aircraft, such as an unmanned aerial vehicle (UAV), and for performing work on electrical power lines and/or splices on electrical power lines. The apparatus or system may include an attachment flange selectively and releasably coupled to the aircraft, a payload support frame selectively and releasably coupled to the attachment flange, an intermediary frame selectively and releasably coupled to the payload support frame, and a base frame selectively and releasably coupled to the power line device. The payload support frame may include at least three elongated rigid segments, each including a hollow elongated pole, at least three upper flexible segments, each at an upper end of a corresponding rigid segment, and at least three lower flexible segments, each at a lower end of a corresponding rigid segment.

Abstract: According to one embodiment, a flying body includes a radar, a supporter, a plurality of rotors supported by the supporter, and a controller. The rotors include a first rotor. The radar is configured to perform a detection operation and a non-detection operation. The controller is configured to perform a first control operation in a first transition from the non-detection operation to the detection operation. The controller is configured to perform a first change in the first control operation to change a rotational speed of the first rotor from a rotational speed of the first rotor in the non-detection operation. The detection operation is performed after the first control operation.

Abstract: A system includes a detector attachment member and a communication system. The detector attachment member includes a first end configured to be coupled to an unmanned aerial vehicle; a second end configured to be coupled to a detector; and a body extending between the first end and the second end, the body of a length selected such that an interference of the unmanned aerial vehicle at the detector is less than an interference threshold. The detector attachment member also includes a lift system coupled to the body. The communication system is coupled to the detector attachment member and is configured to provide communication between the unmanned aerial vehicle and the detector.

Abstract: A method for commissioning a field device or a service job on the field device uses a mobile transport unit having a position determination unit designed for navigation and further having an output unit. The method includes: transmitting a commissioning or service notification to the mobile transport unit, wherein the notification contains the identification of the field device and an operating action to be carried out on the field device; locating the installation position of the field device by the mobile transport unit based on the identification of the field device; guiding an operator to the installation position via autonomous navigation of the mobile transport unit through the installation; and assisting the operator when performing the operating action, wherein the mobile transport unit specifies and/or explains to the operator all operations or actions to be carried out.

Abstract: A container fixing device for pharmaceutical containers, a weighing station, and an apparatus for processing pharmaceutical containers. The container fixing device includes a main body and two or more fixing elements, each having a fixing member that can be placed onto the container, which elements are secured to the main body and between which elements an interspace is formed to accommodate a container. At least one fixing element is moveable on the main body. A container located in the interspace makes contact with an actuating member of the movable fixing element. The actuating member can transfer from a release position, in which the container can be introduced into and removed from the interspace, into a fixing position, in which the container is fixed by the fixing members. The container can be introduced into the interspace in a transport direction transverse to the actuation direction.

Abstract: A method for automatically closing an open end of a sample vessel with a closure cap, including, inter alia, the steps of grasping an upper part of the closure cap at its outer circumference by means of a cap gripper with at least two gripper fingers comprising respective top thrust ledges extending at least in part over a recess provided by a lateral gripping face, and of pushing the closure cap into the open end of the sample vessel by means of the top thrust ledge. In addition, a respective movable cap gripper for automatically closing the open end of the sample vessel with the closure cap as well as a respective sample vessel closure system is provided.

Abstract: A method and an apparatus for forming packages including plasters enclosed between two opposite flexible sheets having their edges joined by means of a thermally-activated adhesive.

Abstract: A method of loading articles in cartons. The method can comprise moving a carton in a generally flat configuration in a downstream direction with a carton opening carousel, at least partially opening the carton while moving the carton with the carton opening carousel, and transferring the carton from the carton opening carousel to a carton loading carousel in a transfer region. The transferring the carton can comprise moving the carton in an upstream direction. The method further can comprise loading a plurality of articles into the carton while moving the carton in a downstream direction with the carton loading carousel.

Abstract: A contact interfacing conductive receptacle is provided. The contact interfacing conductive receptacle includes a housing sized to receive an object including water. The housing includes one or more non-transfer material pieces and two or more transfer material pieces. Each transfer material piece is configured to provide conductivity and provides a field to a different portion of the object. The transfer material pieces are integrated with the non-transfer material pieces.