380results about "Aircraft accessories" patented technology

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.

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.

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.

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 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.

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.

A system for monitoring a pressure change within at least one compartment of an aircraft and operating a pyrotechnic device associated with a door latch, includes a securing mechanism arranged in an aircraft door that includes a pyrotechnic actuator and a latch bolt. The system includes the pyrotechnic actuator configured to move the latch bolt when the pyrotechnic actuator is actuated. The system also includes a pressure sensor configured to provide a pressure signal. The system also includes a controller configured to determine a pressure drop representing a decompression event. The system also includes an output driver configured to generate an output signal to actuate the pyrotechnic actuator when the controller determines the occurrence of a decompression event.

The invention belongs to the technical field of airplane structure design, and particularly relates to a cabin door closing and locking sequence control monitoring mechanism. The device comprises a support base, a locking position electric switch pressing block assembly and a closing position electric switch pressing block assembly. The support base is fixed to a cabin door frame and provided with a groove for installing an electric switch. The locking and positioning switch pressing block assembly comprises a connecting rod rocker arm hinged to the base, one end of the connecting rod rocker arm is coupled with a roller on the cabin door, and the other end of the connecting rod rocker arm is provided with a pressing block with a first pressing rod and connected with a reset tension spring. One side of the pressing block rocker arm is provided with a second pressing rod corresponding to the closing position pressing type electric switch, the other side is provided with a locking pin below the pressing block, and the bottom side of the end is in contact with an approaching assembly on the cabin door. When the cabin door is opened, the reset torsion spring enables the second pressing rod to press the electric switch, meanwhile, the locking pin abuts against the bottom of the pressing block, mechanical interference is formed, and mistaken locking signal output is prevented. The safety and reliability of cabin door state monitoring are improved.

A dimmable window system (200) includes a window side (204) holding a window (205), a dimmable member (212), and an energy harvester (220) configured to harvest energy to provide power to the dimmable member (212) and other components of the dimmable window system (200). The dimmable window system (200) can be configured for a vehicle, such as an aircraft (100).

Provide a system. 【Solution means】 Means for receiving visual data acquired by an unmanned aircraft, Means for analyzing the acquired visual data to detect the existence of illegal acts or waste, Means for notifying in real time information regarding detected illegal acts or waste, Means for providing an interface that enables residents to monitor problems and participate in countermeasure actions, Means for receiving complaints from residents, Means for analyzing the complaints and determining the priority of problems, Means for automating the provision of information to residents, Means for automatically generating and sending countermeasure plans to locations with problems, A system including the above.

The invention relates to a system or assembly comprising a laminated glazing consisting of at least one first outer pane (1) retracted relative to at least two structural panes (3, 5) joined in pairs by adhesive interlayers (2, 4), in which peripheral portions of the structural panes (3, 5) protruding out of the first pane (1) comprise through-holes, a screw-nut assembly (11) is screwed into these through-holes in order to rigidly connect the structural glass sheets (3, 5) to the mounting structure (17), each through-hole being cylindrical and a cylindrical interface system (15) being positioned between the through-hole and the screw (11), or each through-hole having a conical or biconical geometry in each of the structural glass sheets (3, 5), a stud (21, 22) for insertion of a corresponding conical or biconical geometry, between which a conical or biconical clamping interlayer (23) is positioned; a method for producing the system.

An aircraft window barrier and aircraft window assembly including the aircraft window barrier for impeding debris entry into aircraft multi-pane windows during aircraft construction, aircraft storage, and non-flight aircraft phases, and methods for installing the aircraft window barrier and forming the aircraft window assembly are disclosed.

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 present application relates to an aircraft door assembly. The aircraft door assembly includes a door; a hinge arm; an upper lift arm and a lower lift arm; a lift shaft including a lift shaft drive secured to the lift shaft; a guide cam block secured to the door, the other end of the lift shaft pivotally connected to the guide cam block; a lower link assembly including a lower link member connected between the lift shaft and the lower lift arm, and a stop member in contact with the lift shaft drive and the guide cam block, respectively, to limit movement of the stop member relative to the lift shaft, wherein the guide cam block and the lift shaft drive collectively restrain the stop member from moving relative to the lift shaft when the door is in a closed condition, and wherein the guide cam block restrains and guides the movement of the stop member relative to the lift shaft during movement of the door between the closed condition and a fully raised condition, and the lift shaft drive actuates movement of the stop member.

The invention relates to a method for hydrophobizing a glass substrate, the method comprising the following consecutive steps: - forming a primer layer, preferably comprising silicon oxide, on one of the surfaces of a glass substrate, - forming a hydrophobic layer by applying, on the primer layer, a composition comprising at least two non-fluorinated alkylsilane compounds A and B, the compound A having an alkyl chain Ra comprising 1 to 5 carbon atoms, and the compound B having an alkyl chain Rb comprising 6 to 16 carbon atoms. The invention also relates to a hydrophobic glass product that can be obtained by the method according to the invention, comprising a glass substrate, one surface of which is at least partially covered with a coating comprising: - a primer layer, preferably comprising silicon oxide, in contact with said surface of the substrate; and - a hydrophobic layer comprising at least two different non-fluorinated alkylsilyl groups Ga and Gb, grafted onto said primer layer, the group Ga having an alkyl chain Ra comprising 1 to 5 carbon atoms, and the group Gb having an alkyl chain Rb comprising 6 to 16 carbon atoms.

The present invention relates to a fuselage (G) which is an aircraft, at least one door (2) located on the fuselage (G) for providing a passenger with access into or out of the fuselage (G); at least one hinge (3) located on the fuselage (G) providing for the pivoting of the door (2) such that it can move on the fuselage (G); at least one fastener (4) providing for the securing of the door (2) to the fuselage (G) by means of the hinge (3); a handle (5) located within the fuselage (G) so as to be accessible to a user; a first position (I) in which the door (2) is fixedly positioned on the fuselage (G) so as to have a connection with the fuselage (G); at least one rod (6) located between the handle (5) and the fastener (4) in such a way that one end is connected to the handle (5) and the other end is connected to the fastener (4) for transmitting the rotational motion of the handle (5) to the fastener (4); a second position (II) having a door (2) that is separated from the fuselage (G) by the free movement of the fastener (4) which is triggered by the rod (6) with the rotation of the handle (5) by the user; the handle (5) which is brought from the first position (I) to the second position (II) by being rotated by the user; the fastener (4) which is brought from the first position (I) to the second position (II) by being triggered by the rod (6) with the rotation of the handle (5) by the user, and a trigger (7) positioned on the fuselage (G) which, with the movement of the handle (5) from the first position (I) to the second position (II), provides for the separation of the fastener (4) from the hinge (3) by the rod (6) pulling the fastener (4) from the hinge (3).

The invention belongs to the technical field of aircraft passenger cabin arrangement design, and particularly relates to a passenger cabin with discontinuous longitudinal main aisles and a design method. A method for designing a passenger cabin with a discontinuous longitudinal main aisle is characterized in that a row of backward seats are arranged at the position, close to a first row of seats of a cockpit, in the passenger cabin, a row of forward seats are arranged at the position, close to the last row of seats, in the passenger cabin, the two rows of seats are the whole row of seats, and no longitudinal main aisle exists between the first row of seats and the last row of seats; other rows of seats in the passenger cabin are arranged according to 2-1 or 2-2 seats with longitudinal main aisles; seats are arranged on a longitudinal main aisle of a certain row of seats to form a whole row of seat layout, so that a passenger cabin is divided into a front compartment and a rear compartment by the whole row of seats.

The invention relates to:-a laminated glass sheet comprising a first glass sheet (1) forming the outer face of the glass sheet, the first glass sheet (1) being connected to a second glass sheet (3) by means of a first interlayer adhesive layer (2), the edge of the first glass sheet (1) being indented relative to the edge of the second glass sheet (3), the peripheral portion of the free surface of the first glass sheet (1), the edge face of the first glass sheet (1), the edge face of the first interlayer adhesive layer (2) and the surface portion of the second glass sheet (3) extending beyond the first glass sheet (1) describe a continuous stepped profile covered with stepped elements (7) in which an adhesive (6) is inserted, said stepped element (7) being made of a polymeric material, which may contain a reinforcing filler, exhibiting a water vapor permeability of at most equal to 5 g / m2 / day; a method for the production thereof; -its use (aeronautical engineering and the like).

The invention relates to a method for manufacturing an aircraft window frame (118.1), said frame comprising a first surface (S1) having a curved junction zone (133) extending around the entire perimeter of the frame (118.1), the latter being made of composite material and comprising a stack of fiber layers (132, 134, 134') as well as at least one reinforcement (136) located at the junction zone (133). The manufacturing method includes an assembly step of the different fiber layers (132, 134, 134') and the reinforcement (136) during which at least one first seam (140) is made to join at least the reinforcement (136) and certain layers (134', 138), the first seam (140) comprising stitches offset from the first surface (S1). The invention also relates to a porthole frame obtained from this process and to an aircraft comprising said frame.

A system for shading or unshading of an aircraft window is disclosed herein. The system includes the aircraft window, a photochromatic material coupled to the aircraft window, and a light source within a cabin of the aircraft. Responsive to exposing the photochromatic material to the light source, the photochromatic material transitions from a first state to a second state.

An unmanned aerial vehicle (UAV) includes a fuselage assembly, a further portion that attaches with the fuselage assembly, and a propulsion assembly coupled with the further portion. The propulsion assembly is constructed and arranged to provide propulsion for the UAV. The fuselage assembly includes a fuselage body constructed and arranged to operate as a forward portion of the UAV, lateral stringers coupled with the fuselage body and extending laterally along the fuselage body, and a set of interchangeable covers to cover at least a portion of a payload bay opening defined by the fuselage body. Utilizing such a fuselage assembly offers a highly configurable mounting architecture to accommodate a wide variety of payloads.