64results about "Aircraft accessories" patented technology

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.

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.

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 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).

A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets.

We provide the system. [Solution] Means for preprocessing the visual data of the monitored object received from the acquisition device, Means for identifying an object based on pre-processed visual data and determining whether the identified object is located in a predetermined prohibited area, A means of notifying relevant organizations of information about the object identified based on the judgment result, A means of notifying the user in real time about objects within a designated restricted area via a digital terminal and guiding them to an appropriate parking location. A system that includes this.

The present invention relates to an aircraft (1) equipped with a canopy (10) having at least a first windscreen (30) and a second windscreen (40) supported by a frame (20). Each windscreen (30, 40) extends along a vertical axis (Z) from a lower segment (33, 43) to an upper segment (34, 44) and along a transverse axis (Y) from an inner segment (31, 41) to an outer segment (32, 42).The inner segments (31, 41) of the first windshield (30) and the second windshield (40) are straight, the inner segments (31, 41) of the first windshield (30) and the second windshield (40) being connected to the same central post (21) of the frame (20), the outer segments (32, 42) of the first windshield (30) and the second windshield (40) being connected respectively to two lateral posts (22, 23) of the frame (20), the outer segment (32, 42) of each windshield (30, 40) being longer than the inner segment (31, 41) of that windshield (30, 40) and projecting from the inner segment (31, 41) of that windshield (30, 40) at least upwards or downwards towards the aircraft (1), each windshield (30, 40) having a surface developable. Abbreviated figure: figure 1.

The present invention relates to the protection of an aircraft fuselage. To provide a protective measure that is as lightweight as possible and easily integrated into the fuselage, a protective insert (10) for the tail section of an aircraft is provided. The protective insert comprises a protective panel (12), an absorption body (14) supporting the protective panel, and a force transmission device (16) holding the absorption body. The protective panel is designed for a pressure-loaded sliding contact with a runway in the event of a tail impact. The protective panel transmits a pressure force acting during the tail impact to the absorption body. The absorption body is designed to absorb the pressure force by damping it, whereby a portion of the energy due to the acting pressure force can be absorbed and converted into an elastic and / or plastic deformation of at least a part of the absorption body.The power transmission device is designed to hold the protective insert on the underside of a tail section of an aircraft and has a plurality of attachment points (18).

An electric VTOL aircraft has a fuselage having a nacelle that is flexibly connected to a power plant assembly that includes a plurality of electric rotors and arms. The power plant assembly may pitch and roll relative to and independently of the nacelle to produce efficient forward, rearward, and lateral thrust while the nacelle attitude remains unchanged. This provides a stable passenger experience as well as enhanced performance and controllability, while reducing cost and complexity. In some embodiments, the fuselage is vertically elongated, and the power plant assembly is mounted above the fuselage such that a person can walk fully upright below the rotors. Also disclosed is a VTOL docking station configured to allow an aircraft to land without the use of landing gears. The docking station also includes an electronic component configured to automatically provide charging to the aircraft when the aircraft is docked with the docking station.

The application provides a helicopter sliding passenger cabin door, and relates to the field of aviation machinery, which comprises a door, upper and lower sliding rails for the door to slide, a door frame matched with the door to open and close, and a locking mechanism for locking or unlocking between the door and the door frame, wherein the locking mechanism comprises an upper lock box assembly, a lower lock box assembly, a connecting rod assembly, an upper lock seat assembly, a lower lock seat assembly, a hook assembly and a hook limiting assembly; the upper lock box assembly and the upper lock seat assembly and the lower lock box assembly and the lower lock seat assembly are locked and matched to form lock points, two lock points ensure the stability of the door locking, and the force required for the operation of the hook is small, which is very convenient; the connecting rod assembly with rigid connection between the upper lock box assembly and the lower lock box assembly is used for transmission without motion stroke difference, which is synchronous, sensitive and reliable; the hook assembly and the hook limiting assembly are matched to limit the forward sliding of the door, so that the door can be kept in the open state.

A barrier rope assembly which can be disassembled on one side, the barrier rope assembly being provided in a door frame of an aircraft having opposite first and second door frames, and including a barrier rope and a hook for hooking the barrier rope. The barrier rope assembly includes a support member which is located on the side of the first door frame opposite the second door frame and supports one end of the barrier rope, and a connecting member which connects the support member to the first door frame in such a manner that the support member can be disassembled from the side of the second door frame relative to the first door frame.

A drone cargo hold device includes a cargo hold unit and a cargo door opening and closing unit. The cargo door opening and closing unit includes a cargo unloading door, a landing gear module, and a linkage module. The landing gear module is capable of reciprocating relative to the cargo hold unit in a first direction. The linkage module includes a drive assembly disposed on the cargo hold unit and a linkage assembly disposed on the landing gear module. When the landing gear module reciprocates relative to the cargo hold unit in the first direction, the drive assembly drives the linkage assembly to move, thereby actuating the cargo unloading door to switch to an open or closed position. This provides the function of automatically opening and closing the cargo unloading door without additional power consumption or with only a small amount of power consumption.

A long-range reconnaissance pod comprises a cylindrical body and a hollow enclosure forward to said body within which an optical sensor configured to image areas of interest during a long-range reconnaissance mission is housed, wherein a casing of said forward hollow enclosure comprises a target-facing section and a target-opposing section that both extend to a leading edge of said pod, and wherein an optical window adapted to protect said optical sensor from external flow is secured to said target-facing section, and both sections are configured with an external aerodynamic design that renders the optical window substantially optically distortion-free.

Activation tooling for a control integral with a support positioned in an interior zone separated from an exterior zone by a wall, the control comprising a return system tending to hold it in a deactivated state. This activation tooling includes a configured to cooperate with the control and a holding device. The holding device has a body integral with the tool and several arms connected to the body. For each arm, an abutment is connected to the arm and bears against the support or the wall. For each arm, an actuator brings the arm and the support closer together against the return system of the control.

The application relates to the technical field of aviation glass, in particular to an aircraft glass window. The aircraft glass window is fixed on a body framework; the aircraft glass window comprises a glass assembly, a frame assembly, a cushion block and a sealing gasket; a fixing bolt can sequentially penetrate the first connecting plate, the frame assembly, the cushion block, the sealing gasket and the second connecting plate from outside to inside; the sealing gasket comprises a base layer, a plurality of first sealing teeth are arranged on the side, away from the cushion block, of the base layer, the first sealing teeth are sequentially and spacedly arranged in the extension direction from the center to the edge of the glass assembly, the first sealing teeth are arranged around the glass assembly, the sealing gasket is provided with a through hole for the fixing bolt to pass through, a sealing boss is arranged around the through hole on the side, away from the cushion block, of the sealing gasket, and the thickness of the sealing boss is greater than that of the sealing tooth. Thus, the problem that the water vapor sealing property of the aircraft glass window is insufficient and the aircraft service requirement cannot be met is solved.

The present invention relates to a device (1) for protecting the cockpit door (92) of an aircraft (90), particularly a commercial aircraft, and an aircraft (90) equipped with such a security device. The device (1) is used to prevent unauthorized personnel from entering the cockpit (93) of the aircraft (90) when the cockpit door (92) is open, comprising: a curtain (10) fixedly attached to a wall at one edge (11), slidably suspended on a curtain track (95), and having a locking element (20) at its free edge (12) opposite to the attached edge (11); and a locking element (30) attached to the wall, wherein the locking element (20) and the locking element (30) are designed to interact with each other when the curtain (10) is closed, such that opening the curtain (10) requires a specific sequence of actions, and that the locking element (20) and the locking element (30) remain connected to each other if at least one specific sequence of actions is deviated from. The aircraft (90) has a cockpit door (92) that separates the cockpit (93) from the rest of the aircraft cabin (91), including a device (1) according to the invention, which is arranged such that when the curtain (10) of the device (1) is closed, it completely blocks the passage leading to the cockpit door (92) away from the cockpit (93) at a predetermined distance from the cockpit door (92).

A hatch locking device (100) for an aircraft or spacecraft hatch (10) including: a drivable spindle drive (101) with a longitudinal axis (X) and fixed relative to a hatch frame (11, 10) along the longitudinal axis (X); a locking bolt (102) driven by the drivable spindle drive (101) and guided along the longitudinal axis (X); and an adjustment bush assembly (110) mounted on a fuselage frame (1) and including a first eccentric bush (111) having a bolt receptacle (112) oriented centrally along the longitudinal axis (X) to receive the locking bolt (102). The hatch locking device (100) is positive-locking connectable in two axles (Y, Z) both perpendicular to the longitudinal axis (X).

Activation tooling for a control comprising at least one tool configured to cooperate with the control and at least one tool retention device. The invention relates to an activation tooling (30) for a control (24.1) attached to a support (22) positioned in an interior zone (ZI) separated from an exterior zone (ZE) by a wall (20), said control (24.1) comprising a return system tending to maintain it in a deactivated state. This activation tooling (30) comprises: at least one tool (26) configured to cooperate with the control (24.1) A holding device (32) comprising: a body (34) integral with the tool (26), several arms (38) connected to the body (34), for each arm (38), at least one support (40) connected to the arm (38) and configured to bear against an element of either the support (22) or the wall (20), for each arm (38), at least one actuator (42) configured to bring the arm (38) and the support (22) together against the control return system (24.1). This tooling is particularly suitable for holding a drain valve (24) in the open position. Figure 9.

The present invention relates to a protective device (1) for aircraft window units. Such a protective device (1) comprises a frame unit (7), a multi-part and lockable protective unit (9) arranged in the frame unit (7), at least one pre-tensionable movement unit (12) arranged on the protective unit (9), which is designed to move the protective unit (9) from at least one open position state to a closed position state, and a release unit (8) coupled to the at least one movement unit (12) via at least one coupling area (13).The release unit (8) is arranged in an installed state of the protective device (1) in an aircraft window unit between an outer window unit (2) of the aircraft window unit and the frame unit (7), so that mechanical forces acting on the outer window unit (2) can be transmitted to the release unit (8) for the purpose of a release process at the at least one movement unit (12). Furthermore, a protective device system (21) for aircraft and an aircraft (100) according to the invention are presented.

The invention relates to an assembly (2) for reinforcing a fuselage (10) of an aircraft (1), said aircraft (1) comprising a fuselage (10) having an opening (12) and a removable panel (14) intended to be received in said opening (12), said assembly (2) comprising: - a first support (22) intended to be fixed to an outer face of the fuselage (10) as well as around and outside an opening (12) of the fuselage; - a sub-assembly (24) intended to be fixed to an outer face of a removable panel (14) of the fuselage, where said sub-assembly (24) is housed inside said first support (22); - first means (32) for fixing said first support to said fuselage; and - second means (34) for fixing said sub-assembly to said removable panel. This makes it possible to reinforce the fuselage of an aircraft when removing the removable panel, for example when maintenance of the hydrogen tanks is necessary.

The application relates to the field of aircraft technology and discloses an aircraft and a door ladder system thereof. The aircraft door ladder system comprises a cabin door body and a ladder mechanism arranged on the inner side of the cabin door body. The cabin door body is rotationally connected with the aircraft and is used for opening or closing the entrance of the aircraft to form an unfolded state and a folded state. The ladder mechanism comprises a plurality of steps. When in the unfolded state, the steps are unfolded from the entrance to the ground so that a user can enter the interior of the aircraft along the steps. When in the folded state, the steps are automatically folded to the cabin door body. The door ladder system of the application can be automatically folded and does not occupy the interior space of the cabin, thereby improving the convenience of passengers getting on and off the aircraft.

The application discloses a side window AR film, a window assembly and a device, wherein the AR film comprises a substrate layer, a first metal layer, a first silicon dioxide layer, a first niobium oxide layer, a second metal layer and a second silicon dioxide layer arranged in sequence, wherein the first metal layer and / or the second metal layer for reducing light transmittance has a thickness of 1-30 nm, and the first metal layer and / or the second metal layer is a plating layer obtained by taking Ni and / or Cr as a target material. The application has good light transmission control, and through excellent layer structure design, the window glass has good heat insulation and privacy anti-peeping performance and good safety.

This application provides an aircraft, including: a first wing disposed at the front of the fuselage, and a second wing disposed at the rear of the fuselage, the second wing being higher than the first wing in a direction parallel to the fuselage. A first support rod and a second support rod are provided on both sides of the fuselage, the first support rod being closer to the fuselage than the second support rod, and the first and second support rods being parallel to the fuselage. In the direction of gravity, the first and second support rods are located below the first and second wings, and are connected to the first and second wings in a direction opposite to the direction of gravity to form an integrated load-bearing frame. Multiple electric rotors are spaced apart on both the first and second support rods, the electric rotors providing lift required for vertical takeoff and landing. A passenger cabin is located inside the fuselage, configured to accommodate at least 20 passengers, solving the problem that existing electric vertical takeoff and landing aircraft cannot support a high passenger capacity of 20 people.

The present invention relates to an aviation glass window (100) that behaves like a film, the aviation glass window comprising a frame supporting an outer layer (102) and at least two structural layers (103, 104), the total thickness of the structural layers being denoted as d, with bases (107a, 107b) formed at the periphery of each structural layer (103, 104), each structural layer being fastened to its corresponding base (107a, 107b) by inserts (108a, 108b, 109a, 109b), the frame consisting of an outer retainer (111) and an inner reverse retainer (112), the frame being configured to be fastened to an aviation structure (115) by one of the frame forming elements, wherein when the glass window comprises two structural layers, the thickness of the structural layer closest to the frame element configured to be fastened to the aviation structure is less than or equal to 40% of the thickness d, and when the glass window comprises more than two structural layers, the thickness is less than or equal to the thickness d divided by the number of structural layers.

This invention relates to a protective device for an aircraft window unit, a protective device system for an aircraft, and an aircraft. Such a protective device includes: a frame unit; multiple closable protective units arranged within the frame unit; at least one pre-tensionable motion unit, arranged on the protective unit and designed to switch the protective unit from at least one open position to a closed position; and a trigger unit connected to the at least one motion unit via at least one connection area of ​​the at least one motion unit. When the protective device is installed in the aircraft window unit, the trigger unit is arranged between the outer window unit and the frame unit, such that mechanical forces acting on the outer window unit can be transmitted to the trigger unit for triggering operation at the at least one motion unit.