| Document |
Document Title |
|
JP5922367B2 |
The aircraft (10) has a body (12) with a pair of airfoils (14-1, 14-2) distant from each other in a transverse direction (y), where each airfoil includes inner airfoil sections (16-1, 16-2) and outer airfoil sections (20-1, 20-2). The in...
|
|
JP5919266B2 |
A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a l...
|
|
JP5906158B2 |
|
|
JP5901516B2 |
A wing structure is provided, wherein the wing structure comprises; an upper covering, a lower covering, and a spar, the spar comprising; a spar web, an upper spar cap attached to the upper covering, and a lower spar cap attached to the ...
|
|
JP5898175B2 |
A method of manufacturing a composite structural member including laying up a stack of fiber reinforced laminate plies, wherein at least one of the plies is laid up as discrete first and second ply portions, and the fibers of the second ...
|
|
JP5886201B2 |
A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) (100,400,1000,1500) configured to control pitch, roll, and/or yaw via airfoils (141,142,1345,1346) having resiliently mounted trailing edges opposed by fuselage-ho...
|
|
JP5886327B2 |
A low-heat-transfer coupling or assembly is configured to mechanically couple together a pair of mating parts, one of which may be in a heat-producing environment. By roughening at least part of the surface of one of the parts, the conta...
|
|
JP5875377B2 |
The present invention prevents misassembly of access doors while reducing stress concentrations. A hole-side convex portion 80 is formed in each opening 12 at one or more locations in a circumferential direction, and a door-side rib 70 i...
|
|
JP5871508B2 |
To provide an impeller wheel airplane and an impeller wheel in which bird's wing-flapping motion is converted into parallel rotary motion.The impeller wheel 4 converts the bird's wing-flapping motion into rotary motion by periodically sw...
|
|
JP5865840B2 |
A compound motion structure (3) for connection between two surfaces comprising a first arm (5) and a second arm (7) swingable coupled together through a first hinge connection (13), a first surface (35) coupled to an opposite end of the ...
|
|
JP5852255B2 |
The purpose of the present invention is to provide: a structural material for structures which is capable of attaining reductions in working time and cost in production steps and of preventing an increase in weight; a fuel tank; a main w...
|
|
JP5851813B2 |
A curvature retaining device (1) includes two support points (25a) that can abut against one surface of a plate-shaped workpiece W, one or more pressing points (40a) that can abut against a position of the other surface of the plate-shap...
|
|
JP2016500597A |
Methods and devices for covering the fastener system (102) are provided. In one exemplary embodiment, the device comprises a cover (100). The cover (100) is configured to rest on the fastener system (102) on the surface (101) of the obje...
|
|
JP5837579B2 |
A carbon fiber composite structure including a first plurality of carbon fiber prepreg plies; and a second plurality of sheets of shape memory alloy interleaved with the first plurality of carbon fiber prepreg plies.
|
|
JP2015227154A |
To provide a method for producing a wing box which can reduce the number of parts to assemble thereby reducing costs and production time and can reduce the risk of leaks when used as a tank.A main wing box comprises an upper panel 32, a ...
|
|
JP5829683B2 |
A linkage guides a flexible cable between two structures. The linkage includes a proximal arm with a proximal pivot joint for coupling the proximal arm to a first one of the two structures; and a distal arm which is coupled to the proxim...
|
|
JP5823667B2 |
The wing end form has a profile running transversely from front edges of a wing (1) to a rear edge of the wing, where the profile extends into a wingspan direction of the wing. A transition area (2) is arranged between the wing and a win...
|
|
JP5818715B2 |
A composite structure comprising a first section; a second section; and a curved corner (18,19) joining the first section to the second section. The structure comprises a stack of fibre-reinforced plies (20-27). The stack includes a firs...
|
|
JP5815240B2 |
|
|
JP5808112B2 |
A composite material structure having holes and enabling weight reduction is provided. The composite material structure is provided with: a forward section (3a) that is a composite material made of fiber reinforced plastic, and extends i...
|
|
JP5809249B2 |
A stringer having a stringer end trim that reduces pull-off forces in a stringer connection structure, including a stringer body; a stringer free edge provided on said stringer body; and a stringer end trim having at least one curvature ...
|
|
JP5808111B2 |
Provided is a composite material structure that reinforces areas around holes against stress concentrations, and also enables weight reduction. A wing (1) has a box structure. A lower outer plate (3) on the wing (1) is provided with: a c...
|
|
JP5808379B2 |
A wing joint (1) including a T-chord (10) and a splice plate (15) for connecting an inboard wing panel assembly (20) and an outboard wing panel assembly (30). The wing panel assemblies include a stringer (60) co-bonded or co-cured with a...
|
|
JP5791741B2 |
An aircraft wing slat (20) is formed from composite materials using lay-up and vacuum bagging techniques. The slat lay-up comprises a central honeycomb core (26) sandwiched between upper (22) and lower (24) composite skins, a pre-cured s...
|
|
JP5791055B2 |
The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ...
|
|
JP5784747B2 |
Technologies are described herein for enhancing joint capability and reducing the risk of delaminating a stringer using skew-angle radius fillers. A skew-angle radius filler for enhancing joint capability includes a top surface and a bot...
|
|
JP5773679B2 |
This carbon-fiber-reinforced plastic structure includes: an electroconductive layer (233) formed by being laminated on a carbon-fiber prepreg (231); and an electric-conductor-made jumper (24) that penetrates through the electroconductive...
|
|
JP5769213B2 |
Concepts and technologies described herein provide for a low noise aircraft wing slat system. According to one aspect of the disclosure provided herein, a cove-filled wing slat is used in conjunction with a moveable leading edge element ...
|
|
JP5770786B2 |
A method of manufacturing a part, the method comprising: arranging a first set of components (30, 31, 33, 36),on an outer face of a first inner mould line tool (1); arranging a second set of components on an outer face of a second inner ...
|
|
JP5769412B2 |
The method for manufacturing the structure includes an imaging device installation process in which a camera 41 that obtains an image of a target hole 33 formed in an upper panel 31 is installed on the rear spar 22, and a positioning pro...
|
|
JP2015131487A |
To provide a method and apparatus for manufacturing a composite laminate panel to be used for an outer plate or the like of an aircraft.The thickness of a panel can be accurately controlled by forming a compaction tool 45, a plug 75, and...
|
|
JP5751871B2 |
A spar (2), which is an embodiment of this carbon-fiber-reinforced plastic structure, is equipped with both a carbon fiber prepreg (6) and a conduction layer (8) that is provided on the surface (6a) of the carbon fiber prepreg (6) and th...
|
|
JP5747343B2 |
In designing supersonic aircrafts, a method of designing a natural laminar flow wing is provided which reduces friction drag by delaying boundary layer transition under flight conditions of actual aircrafts. A target Cp distribution on w...
|
|
JP2015127121A |
To manufacture at a low cost, an isogrid panel structure formed by reinforcing an outside plate with ribs.A method of manufacturing an isogrid panel structure comprises: a step S1 of cutting a tube 11 into a plurality of tubes 12-1 throu...
|
|
JP5718569B2 |
A method of manufacturing a composite panel, the method comprising: fitting a control member (70) through the panel; fitting a plug (75) through a compaction tool (45); engaging the control member with the plug; engaging the plug with a ...
|
|
JP5713568B2 |
An object of the invention is to provide a method for producing a structural member and the structural member, in which the structural member including a composite material can efficiently be produced such that strength of the structural...
|
|
JP5712202B2 |
A wing tip device for a wing includes a root and a tip, and the following determinant characteristics: the local dihedral of the wing tip device continuously increases or decreases from the root to the tip; the local sweep of the trailin...
|
|
JP2015083462A |
To provide, e.g., a wing tip device for fixing to an outboard end of a wing.A wing tip device for fixing to an outboard end of a wing defines a wing plane includes: an upper wing-like element 404 projecting upwardly with respect to the w...
|
|
JP5694143B2 |
A shape-changing structure has a superelastic metal foam structural member that changes shape (morphs) to change configuration of the structure. The superelastic metal foam structural member changes shape while maintaining a continuous o...
|
|
JP5694144B2 |
A shape-changing structural member has a shape-changing material, such as a suitable foam material, for example a polymer foam capable of withstanding at least 300% strain or a metal alloy foam capable of withstanding at least 5% strain....
|
|
JP5694931B2 |
A method of stiffening a rib (19, 20) during the assembly of an aircraft wing is described. A stiffener panel (40, 41) is attached to a face of the rib (19, 20). The rib is aligned with one or more wing components with the stiffener pane...
|
|
JP5686286B2 |
A composite material elongate structural member, such as a spar (102), for use in an aerospace structure, comprises a web (108) disposed between upper and lower flanges (104, 106). The web (108) may include a clockwise twist about an axi...
|
|
JP5669635B2 |
Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between ...
|
|
JP5658248B2 |
The disclosure relates to Aeronautics, more particularly relating to wing planforms that reduce wing drag substantially in aircraft driven by propellers or other rotors in tractor configuration. An aircraft comprising a wing and propelle...
|
|
JP5643291B2 |
A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has ...
|
|
JP5628813B2 |
An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mou...
|
|
JP5619931B2 |
|
|
JP5610662B2 |
According to a non-limiting embodiment of the present invention, an appliqué coating is provided for a substrate. The appliqué coating includes a metal foil and a first polymer film underlying the metal foil. A topcoat overlying the me...
|
|
JP5607935B2 |
According to one aspect, the present invention relates to a method 200 of manufacturing at least one non-uniform thickness composite spar component 152. The method comprises braiding 202 a plurality of fibres 126 over a non-cylindrical m...
|
|
JP2014193717A |
To increase aircraft efficiency and reduce the amount of fossil fuels consumed.A wing 120 comprises: an angled portion 106 attached on an outer side of the aircraft relative to an aileron 116; and a controllable airflow modification devi...
|
