Time filter

Source Type

Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design and Research Institute | Date: 2017-02-15

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.


Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design, Research Institute and Shanghai Aircraft Manufacturing Co. | Date: 2017-02-15

The present disclosure provides an aircraft wing assembly, comprising: an aircraft wing having a wing box; a winglet disposed at a wing tip of the aircraft wing, the winglet being connected to the aircraft wing through the wing box; a connection comprises a joint rib for assembling with the wing box and a central joint for assembling with the winglet, wherein the joint rib has a first shearing pins hole and a second shearing pins hole, for being pressed into corresponding first and second shearing pins to form an interference fit, respectively; the central joint has a first bushing hole and a second bushing hole, for being pressed into corresponding first and second bushings to form an interference fit; a positional relationship between the first shearing pins hole and the second shearing pins hole is identical to a positional relationship between the first bushing hole and the second bushing hole, such that when the winglet assembled with the central joint moves towards the wing box assembled with the joint rib, and when the first and second shearing pins are inserted into the first bushing hole and the second bushing hole on the center joint, respectively, small clearance fit is achieved between the first and second shearing pins and between the first and second bushings, respectively.


Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design and Research Institute | Date: 2015-05-27

The present invention relates to the technical field of ice detection, and provides an ice detector, comprising: an icing assembly comprising an icing rod having an ice accretion surface and a support structure; at least one visual sensor configured to obtain an image of the ice accretion surface; a controller electrically connected to the visual sensor and comprising 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; wherein, the icing assembly further comprises 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.


Patent
Commercial Aircraft Corporation Of China., Shanghai Aircraft Design and Research Institute | Date: 2014-08-20

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.


Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design and Research Institute | Date: 2016-02-24

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.


Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design and Research Institute | Date: 2015-03-18

Disclosed is a front installation node integrated with an aircraft pylon. The front installation node is suitable for integral forming with a front end frame (100) of an aircraft pylon and comprises: a first lug (10) and a second lug (20), both respectively protruding outwardly from two sides of the front end frame; and a first connecting rod (70) and a second connecting rod (80), 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, wherein the first connecting rod can pivotally connect to the first lug at a first connection point (1), the second connecting rod and the second lug are respectively connected at a second connecting point (2) and a third connecting point (3). The front installation node for engine is integrated with the pylon frame, saving on weight; and using the front installation node to transmit torque is beneficial in reducing the external width of a rear installation node, reducing engine fuel consumption.


Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design and Research Institute | Date: 2016-02-24

The present invention provides a nose cone structure for a pylon (20) of an aircraft with a wing-mounted layout. The nose cone comprises a front nose cone (21) located in front of a wing leading edge (31) and a rear nose cone (22) located behind the wing leading edge (31). The nose cone is characterized in that at least a part of the rear nose cone (22) is modeled and shaped by cross section control segments and comprises at least one group of latitudinal position control segments (P01, P02, P03, P04) and at least a group of longitudinal position control segments (S01, S02, S03, S04, S05). The rear nose cone of the pylon is shaped by latitudinal position control segments. The pylon design of the present application optimizes the passageway area of the space between the pylon/wing/engine nacelle by controlling the rear nose cone curvature of the pylon without deflection of the rear portion of the pylon.


Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design and Research Institute | Date: 2015-03-18

Disclosed is an integrated pylon structure for a propulsion system, wherein it 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 comprises a pylon box section (110) formed from an upper and a lower beam, a frame (100) and a side wall panel (102). The pylon structure further comprises a thrust reverser hood connection structure, provided on the side wall and connected with a nacelle thrust reverser hood comprising a front fixed hood (301) and a rear movable hood (302). The thrust reverser hood connection structure comprises at least one guide rail used for guiding the rear movable hood to make the rear movable hood 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 the opening of the thrust reverser hood is guided by means of the guide rail on the side wall, thus a guide rail beam is eliminated, which saves on space while meeting the installation requirements of an engine and reduces the weight of the entire propulsion system.


Patent
Commercial Aircraft Corporation Of China Ltd, Shanghai Aircraft Design and Research Institute | Date: 2016-02-24

Disclosed is a linkage mechanism (100) for driving an aircraft landing gear bay door, comprising: a primary torsion tube (10) comprising a first portion located inside a landing gear bay and a second portion outside the landing gear bay; a first drive apparatus connected between the first portion and a strut (201) of a landing gear (200) so as to transfer the driving force of the strut to the primary torsion tube (10); a secondary torsion tube (20) comprising an inner end portion located inside the bay and an outer end portion located outside the bay; a secondary drive apparatus connecting the primary torsion tube (10) and the secondary torsion tube (20) outside the bay; and two third drive apparatuses respectively connected between the inner end portion of the secondary torsion tube (20) and one of the bay doors. The secondary drive apparatus is located outside the landing gear bay, saving on space inside the bay, and reducing interference between motion mechanisms. A single side of the secondary torsion tube (20) transfers torque so that synchronism of the bay door is high. The number of components is reduced and power drive performance is high.


Patent
Commercial Aircraft Corporation Of China, Shanghai Aircraft Design and Research Institute | Date: 2014-08-28

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.

Loading Commercial Aircraft Corporation of China collaborators
Loading Commercial Aircraft Corporation of China collaborators