966results 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 sidewall assembly includes a window and a sidewall portion having an inner-facing side and at least partially surrounding the window. The sidewall assembly further includes a transparent display panel coupled to the sidewall portion covering the inner-facing side of the sidewall portion and the window. The sidewall assembly further includes a display controller operatively coupled with the transparent display panel. The sidewall assembly further includes a window shade movable between an open position to allow light to pass between the window and the transparent display panel and a closed position to obstruct light from passing between the window and the transparent display panel. The sidewall assembly further includes a blackout feature disposed between the window and the transparent display panel and a blackout control device configured to control the blackout feature to selectively obstruct light from passing between the window and the transparent display panel.

A dual purpose aircraft lavatory component that can be a dual purpose aircraft lavatory door that is configured to deploy in a vehicle cabin from an initial position as an aircraft lavatory monument component into a deployed position converting aircraft lavatory monument component into an aircraft cabin lockable barrier to prevent passengers from moving along an aisle in a vehicle cabin into a vehicle area forward of the lockable barrier.

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.

Disclosed are polyurethane-polysiloxane hybrid coating compositions (PUPSHCC) and their uses, processes for their preparation, and substrates incorporating the coating compositions.

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 present disclosure provides a glass assembly and a window assembly. The glass assembly comprises a light guiding component comprising a glass body and having a first surface and a second surface arranged oppositely, wherein incident light entering the light guiding component is capable of being totally reflected and transmitted between the first surface and the second surface; a light-emitting structure located in the light guiding component or arranged on the first surface or the second surface, and leading the incident light out from the second surface; a sealing component surrounding circumferential edge of the light guiding component, wherein one side of the sealing component facing the circumferential edge of the light guiding component is at least partially provided with a reflective layer or the sealing component comprises reflective material to increase the reflection of the incident light inside the light guiding component. The glass assembly of the present disclosure can especially reduce the loss of light brightness at the circumferential edge of the glass assembly on the premise of basically not affecting the performance and aesthetics of the glass itself, so that the luminous effect is effectively enhanced and the user experience is improved.

A windshield wiper system for an aircraft includes a wiper arm (12) and a wiper shaft (14) with a first end (34) connected to a base of the wiper arm. An electric motor (20) is coupled to the wiper shaft to rotationally drive the wiper shaft. The windshield wiper system also includes a brake system (24). The brake system includes an electromagnet (38) comprising an energized mode and a de-energized mode. The brake system also includes an anti-rotation assembly with a first element and a second element. The first element is connected directly to the wiper shaft. The second element is rotationally stationary relative the wiper shaft and the first element. The second element is configured to interlock with the first element to prevent rotation of the first element and the wiper shaft when both the electromagnet is in the de-energized mode and the wiper arm is in a park position.

The invention provides a helicopter rain sealing covering cap which comprises a covering cap assembly, a skin, a reinforcing structure, a sealing assembly, a supporting assembly and a locking mechanism, and the reinforcing structure comprises an upper longitudinal horizontal piece, a lower longitudinal horizontal piece, a front frame, a rear frame and a reinforcing plate; the sealing assembly comprises a sealing baffle, a sealing rubber strip and a flow guide groove. The upper longitudinal horizontal piece, the lower longitudinal horizontal piece, the front frame and the rear frame are all of a long plate frame structure, and in order to prevent local instability caused by compression, the width-to-thickness ratio of the inner edge strip is smaller than 12; the upper longitudinal horizontal piece, the lower longitudinal horizontal piece, the front frame and the rear frame are mounted on the inner side of the skin through rivet connection; the edge strip and the web plate at the junction of the upper longitudinal horizontal piece and the front frame and the rear frame are disconnected, and the edge strip and the web plate at the junction of the lower longitudinal horizontal piece and the front frame and the rear frame are disconnected.

The invention belongs to the technical field of aircraft cockpit windshield glass structure design, and particularly relates to an aircraft cockpit windshield glass structure which comprises an electromagnetic film, outer-layer glass, inner-layer glass, a metal frame, a metal sinking frame and a curved-surface wave-transparent fairing. The electromagnetic film is positioned between the outer-layer glass and the inner-layer glass; the inner-layer glass is arranged in the metal frame; the electromagnetic film is in flush contact with the outer side surface of the metal frame; the metal sinking frame is mounted in the windshield window, and the cross section of the metal sinking frame is L-shaped; the metal frame is arranged in the L-shaped opening of the metal sinking frame, the outer side surfaces of the metal frame and the metal sinking frame are flush and contacted with the aircraft body surface skin, and the outer-layer glass protrudes out of the aircraft body surface skin; the curved-surface wave-transparent fairing surrounds the periphery of the outer-layer glass and is in smooth transition between the outer-layer glass and the surface skin of the machine body.

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.

The invention belongs to the technical field of aircraft structure design, and particularly relates to an integral maintenance cabin door. The cabin door comprises a cabin door body structure (1), a hinge joint (2), a power assisting device (3), a handle mechanism (4) and a fixed pull rod (5), the cabin door body structure (1) is provided with a longitudinal and transverse framework, the upper portion of the cabin door body structure (1) is connected with a machine body through the hinge joint (2), the lower portion of the cabin door body structure (1) is connected with the machine body through the fixed pull rod (5), and the side portion of the cabin door body structure (1) is connected with the machine body through the handle mechanism (4); the handle mechanism (4) is provided with a rotating handle (41), and the rotating handle (41) is rotated to drive a bolt (44) to lock the side edge of the cabin door body structure (1); one end of the power assisting device (3) is fixed on a fixing structure (6) in the machine body, and the other end is connected with the cabin door body structure (1) through a gas spring. The integral maintenance cabin door is high in bearing efficiency, and the opening time of the cabin door can be shortened.

An aircraft windshield window frame framework assembly, comprising: window frame frameworks (20), which comprise main windshield opening frames (21) surrounding main windshields (11) of an aircraft and side windshield opening frames (22) surrounding side windshields (12) of the aircraft, wherein the main windshield opening frames (21) and the side windshield opening frames (22) are mounted on and fitted with the corresponding main windshields (11) and side windshields (12) by means of tight fit to form an integral whole, the two main windshield opening frames (21) are in direct contact and are connected in a butt joint manner, and each main windshield opening frame (21) and the corresponding side windshield opening frame (22) are in direct contact and are connected in a butt joint manner. The design of butt-joint connection of the opening frames of the four integral window frame frameworks and the use of connecting belt plates at butt-joint sections of the opening frames make a force transfer route of the window frame frameworks at connection sections more direct, thereby achieving higher load transfer efficiency and structural use efficiency, and reducing the manufacturing difficulty and manufacturing cost on the premise of meeting the load-bearing design requirement.

The invention provides an airplane curved surface windshield which comprises composite laminated glass, and the composite laminated glass comprises a PET anti-splashing film layer, inner layer glass, a first PU film layer, an electromagnetic shielding film coating layer, middle layer glass, a second PU film layer, an electric heating ITO film coating layer, outer layer glass and an anti-static film coating layer which are sequentially arranged in a laminated mode. The two ends of the inner-layer glass, the first PU film layer, the electromagnetic shielding coating layer and the middle-layer glass are connected with an aramid fiber area through longitudinal PU film layers, and the aramid fiber area comprises a first aramid fiber reinforced phenolic resin area, a transverse PU film layer and a second aramid fiber reinforced phenolic resin area which are sequentially stacked; one side, far away from the inner-layer glass, of the PET anti-splashing film layer is connected with a third aramid fiber reinforced phenolic resin area through a two-component polysulfide waterproof sealant layer; the anti-static coating layer is connected with an aluminum frame through a conductive copper net, and the aluminum frame is connected with an airplane body aluminum frame through conductive rubber.

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 belongs to the field of airplane cabin door design, and particularly relates to a cockpit top emergency door. Comprising a sliding rail which is fixedly installed on a machine body opening frame, and a supporting part is arranged on the sliding rail; the door body structure is installed on the sliding rail in a sliding mode, supporting rods are installed on the two sides of the door body structure respectively, and when the door body structure slides to the opening position, the supporting rods and the supporting parts are engaged and locked; the cabin door driving assembly comprises a handle, a rotating shaft, a rocker arm and a connecting rod, and the handle is installed on the inner side of the door body structure; two ends of the rotating shaft are respectively connected with the supporting rods on the corresponding sides; the rocker arm is mounted on the rotating shaft; the other end of the connecting rod is connected with the rocker arm; the handle, the rotating shaft, the rocker arm and the connecting rod form a four-rod mechanism, the handle drives the rotating shaft to rotate to drive the supporting rod to rotate, and the cabin door is opened and closed. The cabin door meets the requirements of multiple functions, simple and reliable mechanism, simplicity and convenience in operation and limited movement space.

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 system includes a robotic arm, a rotisserie control linkage, and a computer system. The robotic arm includes a touch probe and laser head. The rotisserie control linkage is configured to couple to a transport cart. The computer system is communicatively coupled to the robotic arm and the rotisserie control linkage and is configured to control the system to probe, using the touch probe of the robotic arm, a transparent outer layer of an aircraft canopy located on the transport cart in order to determine surface measurements of the aircraft canopy. The computer system also controls the system to ablate, using a plurality of predetermined parameters and the laser head of the robotic arm, an interface layer located between the transparent outer layer and the aircraft canopy, wherein movements of the robotic arm during the ablation are based on the surface measurements.

The invention discloses a thermoplastic composite T-shaped window frame structure and a compression molding process thereof, and relates to the technical field of composite structure manufacturing. A runway oval window frame is composed of a flange rib, a vertical flange and a base flange, the cross section of the runway oval window frame is of an inverted-T-shaped structure, and a window frame base body is formed by splicing a Z-shaped cross section pre-forming assembly located at the bottom, a first L-shaped cross section pre-forming assembly located at the top and a second L-shaped cross section pre-forming assembly located at the top. And a one-way prepreg layer is wound and laid in a splicing gap of the window frame base body to form a preformed body, and then the preformed body is subjected to hot-pressing curing forming. A thermoplastic composite material laminated flat plate is subjected to matrix type blanking and batch pressing to form a preformed split body with a Z-shaped section and two L-shaped sections, three preformed assemblies are annularly spliced and then spliced to form a window frame base body, meanwhile, annular reinforcement is conducted through prepreg, and finally hot-pressing curing forming is conducted, so that fiber wrinkles can be effectively reduced, and the window frame quality is improved. The overall strength of the window frame is guaranteed, and manufacturing difficulty and manufacturing cost are reduced.

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.