691results about "Aircraft accessories" patented technology

A door assembly configured to be mounted in an opening of a cabin area of an aircraft. The door assembly includes a door configured to be movable between a deployed position across the opening and a stowed position out of the opening. A lock is mounted to the door and movable between a locked position and an unlocked position. An engagement assembly is mounted to the door and movable between an engaged position and a disengaged position. The engagement assembly includes a plunger, a lock mechanism, and an elongated member that extends between the lock and the lock mechanism. In the engaged position, the lock mechanism and the elongated member position the plunger in an extended position outward from the door. In the disengaged position, the lock mechanism and the elongated member position the plunger in a retracted position relative to the door.

The invention provides an interchangeable helicopter hinge cabin door structure and a preparation method thereof, and belongs to the technical field of helicopter cabin doors, a cabin door main body is of a composite sandwich structure and is of an inner skin and outer skin structure, the cabin door main body structure is divided into inner and outer skin secondary glue joint curing, and inner cavities with different section shapes are formed after the inner and outer skin secondary glue joint curing; other cabin door accessories are arranged on the cabin door main body structure; the cabin door is provided with two metal hinge joints, the metal hinge joints are connected with the cabin door body, and the cabin door is installed on the fuselage structure through cooperation of the metal hinge joints and hinge joints on the fuselage door frame. The structure is simple, the integration is high, the process difficulty is low, the assembly is convenient, and the product consistency is good.

A closure assembly for a fluid port having a fluid flow channel defined along an axis, the channel ending in a port opening. The assembly includes: a closure cap extending in a first plane arranged to seat across, and close the port opening, in use, in a closed state, a guide arm extending from the cap in a second plane substantially perpendicular to the first plane; a lifting guide to accommodate and retain the guide arm for movement of the guide arm in the second plane as the cap moves axially away from the opening; and a pivot mechanism between the guide arm and the lifting guide about which the cap is able to pivot relative to the lifting guide to an open position.

A barrier door system to control movement of persons through an opening in an interior space of an aircraft. The barrier door system having a frame with outer members that extend around a gap. A barrier door has a first panel and a second panel that are pivotally connected together with the barrier door pivotally connected to the frame. The barrier door is movable between a stowed position and a deployed position. The stowed position includes the first panel and the second panel folded together in an overlapping configuration and positioned in the gap in the frame and away from the opening. The deployed position includes the first panel and the second panel positioned away from the gap and extending across the opening.

The invention provides an aircraft passenger accommodation unit (1000) comprising a seat (100), a shell (110) defining an opening (120), and a door (130). The door (130) is translatable along a first path across the opening (120) between a closed position in which passenger egress through the opening (120) is at least partially blocked, and an open position which allows passenger access between a seat (100) and an aisle (300). The door (130) is translatable in a second direction that is transverse to the first direction, between a first configuration and a second configuration. In the first configuration, the door (130) is translatable across the opening (120) along the first path, and when the door (130) is in the second configuration, the door (130) is translatable across the opening (120) along a second path. The invention also provides a door arrangement and a method of using a door.

The invention provides a transparent bulletproof ceramic composite structure with an electric heating function and a preparation method of the transparent bulletproof ceramic composite structure. The composite structure comprises an anti-splashing layer (1), a first middle layer film (2), a multi-layer stacked structure (3) of glass sheets and films, a first transition layer (4), an electric heating film layer (5), a second transition layer (6), a ceramic layer (7), a first antireflection film layer (8), a second antireflection film layer (9), a third antireflection film layer (10), a second middle layer film (11), an inorganic glass layer (12), a third transition layer (13) and an anti-static layer (14) which are arranged in sequence. The composite structure provided by the invention has excellent impact resistance and bulletproof grade, can effectively resist the damage of high-speed elastic sheets or impact objects, and meets the requirements of high-safety application scenes such as weapon armors, armed airplanes and high-speed trains; and the anti-static film has clear optical observation capability, high transmissivity and anti-static property.

A barrier door system configured to be positioned at an opening within an interior of an aircraft. The barrier door system comprises a door that is movable between a stowed position away from the opening and a deployed position that extends across the opening. A lock is mounted to the door and configured to lock the door in the deployed position with the lock configured to be immediately movable from a locked position to an unlocked position from a forward side of the door and to delay moving from the locked position to the unlocked position from a rear side of the door.

The invention relates to a system or an assembly comprising a laminated glazing, consisting of at least one first outer glass sheet (1) set back with respect to at least two structural glass sheets (3, 5), bonded pairwise by an adhesive interlayer (2, 4), wherein the peripheral portion of the structural glass sheets (3, 5) overhanging the first glass sheet (1) comprises through-holes, in which screw-nut assemblies (11) are screwed in order to rigidly connect the structural glass sheets (3, 5) to a mounting structure (17), each through-hole is cylindrical and a cylindrical interface system (15) is positioned between the through-hole and the screw (11), or each through-hole has, in each of the structural glass sheets (3, 5), a conical or biconical geometry, for the insertion of studs (21, 22) of corresponding conical or biconical geometry, with a conical or biconical clamping interlayer (23) positioned therebetween; a method for producing this system.

The invention relates to the technical field of aircraft windshields, in particular to an organic laminated windshield transparent part with asymmetrically connected edges. The organic laminated windshield transparent part comprises a composite transparent part provided with a mounting hole; the first pressing plate is arranged on the first surface of the composite transparent part; the second pressing plate is arranged on the second surface of the composite transparent part; the fastening piece is used for connecting the first pressing plate, the composite transparent piece and the second pressing plate; the composite lining is contained in the mounting hole in the axial direction of the composite lining partially or completely, the fastener penetrates through the composite lining, the composite lining comprises an inner lining body and an outer lining body provided with a plurality of branch lining bodies, the branch lining bodies correspond to at least one layer of the composite transparent part, the inner lining body is selected according to the function of the fastener, and the outer lining body is selected according to the function of the fastener. And each sub-bushing is selected according to the function of at least one layer of the corresponding composite transparent part. According to the windshield transparent part, the effects of load transmission, sealing, protection and the like can be improved, the stability and reliability of the windshield transparent part are improved, the using effect of the windshield transparent part is enhanced, and the service life of the windshield transparent part is prolonged.

Advancements in executive aircraft interior design explicitly address the limitations of traditional physical windows within aircraft cabins. The passenger experience is transformed by integrating advanced hybrid technology, replicating expansive exterior views, fostering a sense of connection to the surroundings, and an immersive travel experience through a mimetic virtual display.

An emergency backup power source for an electrically controlled and motorized window shade unit includes an input power switch, and charge and discharge control circuit, and a supercapacitor bank. During normal operation a nominal voltage level from a main power source of the aircraft is provided directly to the window shade unit through the input power switch, and the supercapacitor bank is charged. The input voltage is monitored by the emergency backup power source, which controls the input power switch. When the input voltage drops below a threshold level, the input power switch is opened and the charge and discharge circuit operates to provide an emergency output voltage to the window shade unit from the supercapacitor bank so that the window shade can be fully opened or closed, as is required.

The invention relates to the field of microcrystalline glass, and provides high-hardness microcrystalline glass and a preparation method thereof. The high-hardness microcrystalline glass is prepared from the following raw materials in percentage by mole: 50 percent to 65 percent of SiO2, 15 percent to 25 percent of Al2O3, 10 percent to 18 percent of MgO, 3 percent to 8 percent of Li2O, 2 percent to 5 percent of ZrO2, 0.5 percent to 2 percent of Y2O3, 1 percent to 3 percent of B2O3, 0.5 percent to 2 percent of ZnO and 0.1 percent to 1 percent of CeO2. According to the high-hardness glass ceramic provided by the invention, the hardness, wear resistance and other properties of the glass ceramic are effectively improved, and the stability of the properties is improved.

This document describes a system that can be attached to the outer skin of a vehicle, such as an aircraft. A disclosed version of the system comprises an antenna component, a support frame, brackets, and an aerodynamic fairing. The antenna component is connected to the support frame, which has a plurality of clevis mounting features. Each support fitting can be coupled between one of the clevis mounting features and the outer skin of the vehicle. The fairing consists of an upper and a lower part. The upper part has a defined opening. The lower part is configured and arranged to connect to the outer skin of the vehicle. The opening is shaped and dimensioned to accommodate at least a portion of the support frame that is connected to the upper part of the fairing.

A panel assembly (such as for an internal cabin of an aircraft) includes at least one liquid flow path formed on at least one surface through surface treatment. The at least one liquid flow path is formed in relation to at least one bank on the at least one surface. The at least one liquid flow path is configured to divert liquid to a desired location.

A system includes a first camera located within a cockpit of an aircraft to track the eye movement of at least one pilot, and a second camera to track an ambient light source. The system includes an electrochromic panel having an array of dimmable cells. The system further includes a controller, equipped with one or more processors responsible for modifying the array of dimmable cells. The controller receives eye tracking data from the first camera associated with a gaze target of the pilot, and light tracking data from the second camera, which includes parameters associated with the ambient light source. Based on the eye tracking and light tracking data, the controller determines a glare location on a surface of the electrochromic panel where the gaze target intersects. The controller may then selectively modify a tint level of specific dimmable cells in the panel to address the determined glare location.

The utility model relates to the field of unmanned aerial vehicle structural design, and provides an unmanned aerial vehicle parachute cabin opening cover device capable of guiding a parachute to exit from a cabin, the unmanned aerial vehicle parachute cabin opening cover device comprises a parachute cabin opening cover and a bounce-off mechanism, and the rear end of the parachute cabin opening cover is connected with a parachute cabin wall on one side of the parachute cabin through the bounce-off mechanism. A front cover of the parachute cabin opening cover is pressed on the other side of the parachute cabin device through a pressing piece so as to seal a parachute cabin opening, when the unmanned aerial vehicle needs parachute landing and drives the pressing piece to be loosened, the parachute cabin opening cover is bounced through the bouncing mechanism, the parachute cabin opening is opened, the bouncing mechanism is provided with a protruding end, and the protruding end is connected with the parachute cabin opening cover. The protruding end is used for limiting the parachute hatch cover when the parachute hatch cover bounces, so that the parachute hatch cover is opened by a certain angle, and then the parachute is pulled out along the inner surface of the parachute hatch cover along the opening angle of the parachute hatch cover. The parachute can be pulled out in a certain direction, and the releasing reliability of the recovery parachute is guaranteed.

An air vehicle structure includes a first component having a plurality of first component openings, and a second component positioned on the first component and having a plurality of second component openings aligned with the plurality of first component openings. A plurality of fasteners extend through the second component openings and into the plurality of first component openings to secure the second component to the first component. A cover assembly is installed over the second component covering the plurality of fasteners and includes a cover frame, and a plurality of wedge lock assemblies. Each wedge lock assembly is positioned at a second component opening of the plurality of second component openings. Each wedge lock assembly of the plurality of wedge lock assemblies are engaged to an interior surface of a corresponding second component opening of the plurality of second component openings to secure the cover assembly to the second component.

The invention provides a helicopter full-view cabin door, and belongs to the technical field of helicopter cabin doors, the helicopter full-view cabin door specifically comprises a door plate and a visual window, the visual window bulges towards the outside of a helicopter cabin, the visual window is composed of two transparent units, and the two transparent units are rotationally connected with the door plate; the limiting and fixing assembly is installed in the door plate in a sliding mode, and an adjusting block is fixed to the limiting and fixing assembly; the output end of the driving assembly is connected with the limiting and fixing assembly through a connecting rod, and the driving assembly is used for driving the limiting and fixing assembly to be close to the edge of the transparent unit to limit rotation of the transparent unit or driving the limiting and fixing assembly to be away from the transparent unit to release limitation on the transparent unit; and the forcible entry assembly is used for damaging the connecting rod, the adjusting block is used for being manually operated to drive the limiting and fixing assembly to be away from the transparent unit to release limitation on the transparent unit after the connecting rod is damaged, and through the treatment scheme of the application, the escape probability after the helicopter has a safety accident is improved.

The invention belongs to the field of aircraft structure design, and particularly relates to a self-adaptive bolt lock support structure. According to the structure, a movable support is fixedly installed on a cabin door, a first connector is arranged on the movable support, an installation hole is formed in the first connector, and a joint bearing is installed in the installation hole; the limiting stop piece is fixedly connected with the movable support and is provided with a first limiting part and a second limiting part, the deflection angle of the inner ring of the knuckle bearing is limited through the first limiting part, and the outer ring of the knuckle bearing is limited through the second limiting part; the fixed support is fixedly installed on the machine body, a second connector is arranged on the fixed support, a plug pin hole is formed in the second connector, and when the cabin door is closed, the plug pin hole is aligned to the bearing hole of the knuckle bearing; and the bolt penetrates through the bearing hole of the knuckle bearing and the bolt hole to finish locking. The limiting blocking pieces are installed on the two sides of the movable support, the knuckle bearing can be prevented from being disengaged when the plug pin is inserted, and the situation that the deflection angle of the knuckle bearing is too large to block the plug pin hole is prevented.

The utility model provides a glass assembly, a window assembly and a vehicle. The glass assembly includes: a glass body; the first functional layer is suitable for adjusting the visible light reflectivity and is arranged on one side of the glass body; and the second functional layer is suitable for adjusting haze and is arranged on one side of the first functional layer. According to the glass assembly, the first functional layer with the visible light reflectivity adjusting function and the second functional layer with the haze adjusting function are integrated, and the visible light reflectivity and / or the haze can be adjusted according to different application occasions and user requirements, so that the glass assembly has multiple functions, the user experience is improved, and the cost benefit requirement is met.

The invention discloses an unmanned aerial vehicle double-opening cabin door mechanism and belongs to the field of unmanned aerial vehicle body structures. The two sets of mechanisms are symmetrically installed on the inner sides of the left double-opening cabin door and the right double-opening cabin door and control opening and closing of the installed side cabin doors. In the mechanism, a rotating shaft assembly is fixed on a framework in a cabin door, a control part is located outside the cabin door, and a rotating pin on the inner side of the rotating shaft assembly is controlled to rotate through the control part; the two bolt assemblies are oppositely and coaxially fixed to the upper end and the lower end of the inner side of the cabin door and used for locking or unlocking the cabin door. The pull rod assembly comprises an upper pull rod assembly and a lower pull rod assembly which are correspondingly connected with the bolts of the bolt assemblies at the upper end and the lower end respectively and used for transmitting rotation of the rotating pins into axial up-and-down movement of the bolts in the bolt assemblies. The diagonal draw bar assembly is an elastic piece and is used for preventing the rotating pin from freely rotating under non-operation. The double-opening cabin door solves the problems that an existing double-opening cabin door is limited in opening and closing life and prone to damage by adopting an opening cover lock structure, and a linear steering engine electric control structure is high in cost and consumes power of an unmanned aerial vehicle.

A window roller shade and dimming pane assembly includes a rigid frame having a first side member on a first side and a second side member on a second side opposite the first side. An outer pane and an inner pane are disposed within the rigid frame with a gap between the outer pane and the inner pane. A roller shade includes a motor for rolling and unrolling the roller shade. A first constant force spring and a second constant force spring are each configured to pull the roller shade downwardly through the gap while the motor is unrolling the roller shade. A dimming film is disposed on the inner pane for dimming light through the inner pane. A window interface is operatively coupled to the inner pane for receiving touch input for controlling the dimming film and the roller shade.

The invention provides a double-bolt lock mechanism, and belongs to the field of aircraft cabin door locks, the double-bolt lock mechanism comprises a transmission mechanism, two bolt assemblies and a spring boosting assembly; wherein the transmission mechanism comprises a handle, a driving rocker arm, a driven rocker arm and a mounting seat, the mounting seat is fixedly mounted on the cabin door structure, the driving rocker arm and the driven rocker arm are pivoted on the mounting seat, the driving rocker arm is respectively pivoted with one plug pin assembly and the driven rocker arm, and the driven rocker arm is respectively pivoted with the driving rocker arm and the other plug pin assembly. The handle is fixedly connected with the driving rocker arm; the plug pin assembly comprises a plug pin support, a plug pin, a lock ring support and a lock ring, the plug pin support and the lock ring support are fixed to the cabin door structure, the lock ring is fixed to the lock ring support to form a plug pin limiting structure, and the plug pin is installed on the plug pin support and can slide relative to the plug pin support; the spring boosting assembly comprises a spring booster and a spring support, one end of the spring booster is hinged to the driving rocker arm, and the other end of the spring booster is hinged to the spring support.

A linkage mechanism for the lifting and lowering of a photoelectric platform and the opening and closing of a hatch includes a cable assembly, a motor-driven concentric pulley, a photoelectric platform, a hatch guide rail, and a hatch. The motor-driven concentric pulley comprises a small-diameter pulley, a large-diameter pulley, and a rotary motor. One end of the hatch is connected to the small-diameter pulley via the cable assembly, and the other end is connected to the hatch guide rail. The photoelectric platform is connected to the large-diameter pulley via the cable assembly. The rotary motor is connected to both the small-diameter and large-diameter pulleys, and the diameter ratio of the small-diameter and large-diameter pulleys is the same as the ratio of the lifting stroke of the photoelectric platform to the movement stroke of the hatch guide rail. A single power source is used to achieve both hatch opening and photoelectric platform lifting, effectively saving costs, reducing weight, and decreasing energy demand.

This invention relates to a control device for switching aircraft door modes, comprising a handle assembly including a control handle and a handle shaft, the control handle being operable to move to an emergency position or a non-emergency position, and the handle shaft being rotatable in response to the movement of the control handle; a linkage assembly including a lower rocker arm, a link, an upper rocker arm, and an intermediate shaft, the lower rocker arm transmitting rotation of the handle shaft to the upper rocker arm via the link, such that the upper rocker arm can rotate together with the intermediate shaft; and a misoperation prevention component that moves between a locked position and an unlocked position, the linkage assembly being configured such that during the movement of the control handle from the emergency position to the non-emergency position and during the movement of the control handle from the non-emergency position to the emergency position, the upper rocker arm of the linkage assembly and the aforementioned intermediate shaft initially rotate in the same direction, and the misoperation prevention component prevents rotation of the intermediate shaft in the same direction in the locked position.

The utility model relates to a follow-up hatch cover, a nacelle and a tilt rotor aircraft, belongs to the technical field of aircrafts, and solves the problems that the appearance of a rotor shaft fairing in the prior art has a bulge, and interference exists between the rotor shaft fairing and the nacelle. The device comprises a hatch cover unit, a hinge unit, a sliding rail unit and a sliding unit, the hinge unit and the sliding unit are arranged at the two ends of the hatch cover unit respectively, the sliding rail unit is arranged on a power cabin, the hinge unit is used for connecting the hatch cover unit with a rotor shaft cabin, and the sliding rail unit is used for connecting the hatch cover unit with the rotor shaft cabin. The sliding unit is used for enabling the hatch cover unit to slide along the sliding rail unit. The cabin cover unit can slide along the sliding rail unit along with rotation of the rotor shaft cabin, and when the aircraft takes off and lands vertically, the cabin cover unit moves towards the power cabin and exposes the sunken part, so that the rotor shaft fairing can be inserted into the sunken part, and interference between the rotor shaft fairing and the power cabin is avoided.

The invention provides a cabin door opening position locking mechanism, and belongs to the field of airplane cabin door design, the cabin door opening position locking mechanism comprises a lock ring support fixed on a door body structure, and a lock ring mounted on the lock ring support; one end of the lock support is fixed on the machine body structure, and the other end of the lock support is provided with a mounting space for mounting the lock hook; the spring bolt is arranged in the mounting space, a locking groove is formed in the spring bolt, and a wedge-shaped face is arranged on the side, facing the lock ring support, of the spring bolt and used for guiding the lock ring to enter the locking groove of the spring bolt; the handle shaft penetrates through the lock support and the spring bolt and is fixedly connected with the spring bolt; the handle is arranged at the end part of the handle shaft and is fixedly connected with the handle shaft; the torsion spring is arranged on the handle shaft in a sleeving mode, located between the spring bolt and the lock support and used for providing elastic force for the spring bolt; wherein the lock support is provided with a stop shaft, and the stop shaft is used for being in contact with the lower surface of the spring bolt when the spring bolt is matched with the lock ring, so that downward unlocking is prevented.