Abstract: An airborne device which has a bus interface and a dedicated wireless transmission apparatus connected to the bus interface, the dedicated wireless transmission apparatus includes: an interface conversion module; and a wireless transmission module. The interface conversion module is configured to convert bus data received from the bus interface into a data packet suitable for transmission using a radio access technology, and/or to convert a data packet received from the wireless transmission module into bus data corresponding to the bus interface. The wireless transmission module is configured to use the radio access technology to transmit the converted data packet, and/or to receive the data packet transmitted using the radio access technology. In addition, a method and a system for wireless interconnection between airborne devices.

Abstract: A flap slat control lever and a method for operating the lever are disclosed. The lever includes: a first displacement sensor to detect a displacement of the flap slat control lever and generate a first displacement detection signal; a second displacement sensor to detect the displacement of the flap slat control lever and generate a second displacement detection signal; a first control command module to receive the first displacement detection signal; and a second control command module to receive the second displacement detection signal, wherein the first control command module is in a standby state and the second control command module is in a working state.

Abstract: An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

Abstract: A flap slat control lever and a method for operating the lever are disclosed. The lever includes: a first displacement sensor to detect a displacement of the flap slat control lever and generate a first displacement detection signal; a second displacement sensor to detect the displacement of the flap slat control lever and generate a second displacement detection signal; a first control command module to receive the first displacement detection signal; and a second control command module to receive the second displacement detection signal, wherein the first control command module is in a standby state and the second control command module is in a working state.

Abstract: The present invention provides a dewatering device for an air-conditioning system of a plane, comprising: one or more filter plates disposed within a mixing cavity of an air-conditioning system of a plane, for filtering liquid-state water in mixed air in the mixing cavity, wherein the filter plates are configured to be inclinable relative to an axis of the mixing cavity, and an inclination angle thereof is adjustable so as to change a filtering amount of the mixed air.

Abstract: An aircraft cockpit view enhancement system and method. The aircraft cockpit view enhancement system has: front-position, left-position and right-position camera devices. The front-position camera device is arranged between a driver's eye position point and an aircraft windshield pillar, with a photographing angle directly facing the aircraft windshield pillar, and the left-position and right-position camera devices are respectively arranged at a left side and a right side of the aircraft windshield pillar, with photographing angles respectively pointing to the right side and the left side deviated from the aircraft windshield pillar. An image processing device for performing image synthesis and image registration on a front-position image, a left-position image and a right-position image photographed by the front-position camera device, the left-position camera device and the right-position camera device, to obtain an image of a region shielded by the aircraft windshield pillar.

Abstract: An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

Abstract: An airplane wing assembly includes a wing, a winglet and a connection element. The wing has a wing box. The wing box is located at a wing tip of the wing and the winglet is connected with the wing by the wing box. The connection element includes a butt joint rib, which is assembled with the wing box, and a center connection, which is assembled with the winglet. The butt joint rib has a first shearing pin hole and a second shearing pin hole, into which are press fitted a corresponding first and a second shearing pin respectively to form interference fit. The center connector has a first sleeve hole and a second sleeve hole.

Abstract: A photocatalytic honeycomb assembly and a photocatalytic purification apparatus, which can maximally increase a contact area between polluted air and a photocatalyst while maximally ensuring that the surface of the photocatalyst receives sufficient irradiation of ultraviolet light, and can also make the flow resistance to air flowing in a channel meet requirements in the field of ventilation systems which have high requirements on flow resistance. The photocatalytic honeycomb assembly is formed of one or more photocatalytic honeycomb cores and a photocatalytic honeycomb assembly housing. The one or more photocatalytic honeycomb cores are arranged in a honeycomb form. The photocatalytic honeycomb core is formed of three or more basic core units and a light guide member that is Y-shaped in an end view.

Abstract: An aircraft cockpit view enhancement system and method. The aircraft cockpit view enhancement system has: front-position, left-position and right-position camera devices. The front-position camera device is arranged between a driver's eye position point and an aircraft windshield pillar, with a photographing angle directly facing the aircraft windshield pillar, and the left-position and right-position camera devices are respectively arranged at a left side and a right side of the aircraft windshield pillar, with photographing angles respectively pointing to the right side and the left side deviated from the aircraft windshield pillar. An image processing device for performing image synthesis and image registration on a front-position image, a left-position image and a right-position image photographed by the front-position camera device, the left-position camera device and the right-position camera device, to obtain an image of a region shielded by the aircraft windshield pillar.

Abstract: A photocatalytic honeycomb assembly and a photocatalytic purification apparatus, which can maximally increase a contact area between polluted air and a photocatalyst while maximally ensuring that the surface of the photocatalyst receives sufficient irradiation of ultraviolet light, and can also make the flow resistance to air flowing in a channel meet requirements in the field of ventilation systems which have high requirements on flow resistance. The photocatalytic honeycomb assembly is formed of one or more photocatalytic honeycomb cores and a photocatalytic honeycomb assembly housing. The one or more photocatalytic honeycomb cores are arranged in a honeycomb form. The photocatalytic honeycomb core is formed of three or more basic core units and a light guide member that is Y-shaped in an end view.

Abstract: Provided is an airplane suspension (20) fairing structure with a wing-mounted arrangement, the fairing structure comprising a front fairing located in front of the leading edge (31) of a wing and a rear fairing located at the back of the leading edge (31) of the wing; the vertical section line (G) of the front fairing is curved, ascending along air flow direction from a start point (p) of an engine nacelle (10) to the maximum height position and then descending and extending below the lower surface (32) of the wing. In the present invention, due to the curved vertical section line of the front fairing of the suspension, inner space of the suspension is met only in the position requiring greater inner space, thus enabling the engine to be mounted close to the wing without additional devices; and the fairing aerodynamic surface of the suspension will not extend to the upper surface of the wing, avoiding interference of the suspension with the wing during cruising.

Abstract: A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column to the primary torsion tube. A secondary torsion tube has an inner end portion located inside the hatch and an outer end portion located outside the hatch. A second drive apparatus is located outside the landing gear hatch and connects the primary torsion tube and the secondary torsion tube outside the hatch. Two third drive apparatuses are connected between the inner end portion of the secondary torsion tube and one of the hatch doors.

Abstract: An integrated pylon structure for a propulsion system is suitable for one end to be connected to an aircraft wing and the other end to be connected to an aircraft engine. The pylon structure includes a pylon box section (110) formed from an upper and a lower bean, a frame (100) and a side wall panel. The pylon structure has a thrust reverser hood connection structure, provided on the side wall and connected with a nacelle thrust reverser hood having a front fixed hood (301) and a rear movable hood (302). A guide rail allows the rear movable hood to slide and open relative to the pylon box section. The engine thrust reverser hood is directly connected to the side wall of the pylon box section and a guide rail on the side wall guides the opening of the thrust reverser hood.

Abstract: An airplane wing assembly includes a wing, a winglet and a connection element. The wing has a wing box. The wing box is located at a wing tip of the wing and the winglet is connected with the wing by the wing box. The connection element includes a butt joint rib, which is assembled with the wing box, and a center connection, which is assembled with the winglet. The butt joint rib has a first shearing pin hole and a second shearing pin hole, into which are press fitted a corresponding first and a second shearing pin respectively to form interference fit. The center connector has a first sleeve hole and a second sleeve hole.

Abstract: An ice detector includes an icing assembly that includes a transparent icing rod with an illuminating element is disposed therein and having an ice accretion surface and a support structure. The icing rod has at least one visual sensor configured to obtain an image of the ice accretion surface; a controller electrically connected to the visual sensor and including an image contrast module configured to compare the obtained image with an initial image so as to judge whether ice is formed on the ice accretion surface of the icing rod. The icing assembly includes a refrigerating element respectively connected to the icing rod and the support structure. The refrigerating element may perform active refrigeration for the icing rod, reduce the surface temperature of the icing rod and facilitate the ice detector detecting ice accretion before ice is formed on a wing/nacelle.

Abstract: A front installation node is suitable for integral forming with a front end frame of an aircraft pylon and includes a first lug and a second lug, each respectively protruding outwardly from one of the two sides of the frond end frame; a first connecting rod and a second connecting rod, one end thereof being respectively connected to the first lug and the second lug, and the other end thereof being respectively suitable for connecting to an aircraft engine. The first connecting rod can pivotally connect to the first lug at a first connection point. The second connecting rod and the second lug are respectively connected at a second connecting point and a third connecting point. Using the front installation node to transmit torque is beneficial in reducing the external width of a rear installation node, reducing engine fuel consumption.

Abstract: An icing detector probe includes three sections arranged sequentially along the direction of air flow, namely, a first section, a second section and a third section. The shape of the outer surface of the first section is suitable for collecting droplets in the air flow. The shape of the outer surface of the second section is suitable for full decelerating and releasing latent heat of large droplets during their movements. The outer surface of the third section is suitable for icing of large droplets. The probe detects icing by distinguishing and identify large droplets icing. The probe effectively detects types of traditional icing, thus being helpful for exact detection of icing thickness. An icing detector including said icing detector probe is also provided.

Abstract: An apparatus for testing the gas permeability on the inward facing direction of a pre-impregnated resin matrix composite material layer includes a mold, a loading apparatus, a temperature control apparatus, a vacuuming apparatus, and a flow detecting element. A test specimen is laid flat inside the mold between airtight sealing elements that leave exposed two ends of the test specimen on the inward facing direction of the layer. An air inlet and an air outlet respectively are arranged on the mold and correspond to the two exposed ends of the test specimen. The inlet is connected to the flow detecting element, and the outlet is connected to the vacuuming apparatus. Air is forced to move in a vacuumed cavity along the inward facing direction of the layer. Testing of air permeability of pre-impregnated material in solidification technique is allowed via adjustments of pressure and temperature.

Abstract: An apparatus for testing the air permeability in the thickness direction of a resin matrix composite material layer includes a mold having a cavity and a covering plate, a loading apparatus, a temperature controlling apparatus, a vacuuming apparatus, and a flow detecting element. An air inlet is connected to the flow detecting element, and an air outlet is connected to the vacuuming apparatus. The covering plate has a through-hole with upper and lower ventilation pieces. The loading apparatus addresses the upper ventilation piece. A test specimen is laid flat between the ventilation pieces. Employment of the present invention allows for accurate testing of air permeability of pre-impregnated material in the thickness direction of the resin matrix composite material layer under different pressure and temperature conditions.