| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | System and method for minimizing wave drag through bilaterally asymmetric design | EP13191646.2 | 2013-11-05 | EP2738092B1 | 2017-01-18 | Pflug, William; Tillotson, Brian J. |
| 22 | Wing and empennage leading edge structure made of thermoplastic material with a stiffened double-shell configuration | EP09159140.4 | 2009-04-30 | EP2130762A3 | 2013-01-23 | Rinaldi, Ernesto; Russo, Salvatore; Iannuzzo, Generoso; Riccio, Massimo; Sagnella, Giovanni |
A leading edge structure (1) is described for wing structures and empennage, comprising an outer shell (2) suitable to define a front portion of a airfoil. The outer shell is formed by a bent plate of fiber-reinforced thermoplastic resin composite material. The structure further comprises |
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| 23 | Wing and empennage leading edge structure made of thermoplastic material with a stiffened double-shell configuration | EP09159140.4 | 2009-04-30 | EP2130762A2 | 2009-12-09 | Rinaldi, Ernesto; Russo, Salvatore; Iannuzzo, Generoso; Riccio, Massimo; Sagnella, Giovanni |
A leading edge structure (1) is described for wing structures and empennage, comprising an outer shell (2) suitable to define a front portion of a airfoil. The outer shell is formed by a bent plate of fiber-reinforced thermoplastic resin composite material. The structure further comprises |
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| 24 | Trag- oder Leitelement | EP05011439.6 | 2005-05-27 | EP1602575A3 | 2009-04-22 | Schülein, Erich, Dr. |
Die Erfindung betrifft ein Trag- oder Leitelement, bspw. einen Gitterflügel (1) für ein fliegendes Objekt wie ein Luftfahrzeug, ein Flugkörper oder ein Raumfahrzeug. Der Gitterflügel (1) besitzt gitterartig angeordnete Lamellenflügel (5, 6), die Strömungskanäle (7) begrenzen. Erfindungsgemäß ist mindestens eine Stirnkontur (8, 9) eines Lamellenflügels (5, 6) mäanderförmig ausgebildet. Durch die erfindungsgemäße Ausgestaltung der Stirnkontur (8, 9) wird der Widerstand jedes einzelnen Lamellenflügels verringert, wodurch der Gesamtwiderstand des neuen Gitterflügels (1) reduziert werden kann.
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| 25 | ELASTISCHES FEDERELEMENT | EP98959776.0 | 1998-10-29 | EP1025375A1 | 2000-08-09 | WULZ, Hans, Georg; BECKER, Wilfried; KNABE, Helmut |
| An elastic spring element is made of ceramic reinforced with endless fibres. | ||||||
| 26 | RUNBACK ICE FORMATION CONTROL | EP17180370.3 | 2017-07-07 | EP3266711A1 | 2018-01-10 | WILSON, Jr., Tommy M. |
An ice protection system (100) includes an aircraft surface (102) and a gutter (104) defined in the aircraft surface (102) between raised rails (106). The gutter (104) includes a mouth (108) that narrows into a trailing portion of the gutter (104). The mouth (108) is configured to channel water runback rivulets into the trailing portion of the gutter (104). The gutter (104) can be a first gutter (104) of a plurality of side by side gutters (104), each including a respective mouth (108) narrowing into a respective trailing portion, wherein the gutters (104) are separated from one another by respective rails (106).
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| 27 | CLIP FOR RIBS AND STRINGERS IN AN AIRCRAFT STRUCTURE | EP15175758.0 | 2015-07-07 | EP2965984A1 | 2016-01-13 | MARKS, OLIVER |
The invention relates to a structure having a panel, a stringer and a rib. The stringer has a stringer flange that is joined to an inner surface of the panel and a stringer web that extends away from the stringer flange. The rib has a rib web and a rib foot. The rib foot has a rib foot flange that is joined to the stringer web, first and second rib foot base parts that are joined to the inner surface of the panel or to the stringer flange and a rib foot web that is joined to the rib web. The rib foot is formed as a single folded piece such that the rib foot flange is connected to the rib foot web by a first folded corner, the first rib foot base part is connected to the rib foot flange by a second folded corner and the second rib foot base part is connected to the rib foot web by a third folded corner.
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| 28 | Wing and empennage leading edge structure made of thermoplastic material with a stiffened double-shell configuration | EP09159140.4 | 2009-04-30 | EP2130762B1 | 2015-04-29 | Rinaldi, Ernesto; Russo, Salvatore; Iannuzzo, Generoso; Riccio, Massimo; Sagnella, Giovanni |
| 29 | System and method for minimizing wave drag through bilaterally asymmetric design | EP13191646.2 | 2013-11-05 | EP2738092A2 | 2014-06-04 | Pflug, William; Tillotson, Brian J. |
An air vehicle (100, 102) having a bilaterally asymmetric configuration may include a body (104) having a longitudinal axis (106). The air vehicle (100, 102) may further include longitudinally offset engine nacelles (234, 236), asymmetrically lengthened engine nacelles (232), and/or longitudinally offset protruding aerodynamic surfaces (190). ( |
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| 30 | Trag- oder Leitelement | EP05011439.6 | 2005-05-27 | EP1602575A2 | 2005-12-07 | Schülein, Erich, Dr. |
Die Erfindung betrifft ein Trag- oder Leitelement, bspw. einen Gitterflügel (1) für ein fliegendes Objekt wie ein Luftfahrzeug, ein Flugkörper oder ein Raumfahrzeug. Der Gitterflügel (1) besitzt gitterartig angeordnete Lamellenflügel (5, 6), die Strömungskanäle (7) begrenzen. Erfindungsgemäß ist mindestens eine Stirnkontur (8, 9) eines Lamellenflügels (5, 6) mäanderförmig ausgebildet. Durch die erfindungsgemäße Ausgestaltung der Stirnkontur (8, 9) wird der Widerstand jedes einzelnen Lamellenflügels verringert, wodurch der Gesamtwiderstand des neuen Gitterflügels (1) reduziert werden kann. |
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| 31 | ELASTISCHES FEDERELEMENT | EP98959776.0 | 1998-10-29 | EP1025375B1 | 2002-09-25 | WULZ, Hans, Georg; BECKER, Wilfried; KNABE, Helmut |
| 32 | FOLDABLE AIRCRAFT WITH ANHEDRAL STABILIZING WINGS | US15272311 | 2016-09-21 | US20180079488A1 | 2018-03-22 | Brad J. Roberts; Steven R. Ivans |
| An aircraft including a fuselage having a longitudinal axis extending through the fuselage front end and the fuselage rear end; a foldable wing located on the fuselage and being movable between a flight position wherein the wing is generally perpendicular to the longitudinal axis, and a stowed position wherein the wing is generally parallel to the longitudinal axis; and a pair of stabilizing wings having an anhedral orientation disposed on the fuselage. | ||||||
| 33 | MOLD WITH INTEGRAL DRIVER BLOCKS | US15042972 | 2016-02-12 | US20170232642A1 | 2017-08-17 | Michael Fiegl; Craig Robinson; Shawn Canela |
| Aspects of the disclosure are directed to a toolset configured to fabricate a component of an aircraft, the toolset comprising: a mold base configured to seat at least one mandrel, a mold lid configured to be coupled to the mold base, and at least one driver block that is integral with the mold lid and projects from an interior surface of the mold lid. | ||||||
| 34 | Multi-layer film adhesive | US12143939 | 2008-06-23 | US09694560B2 | 2017-07-04 | Stephen Barnes; Thomas Lowe |
| There is provided a multi-layer adhesive for reducing squeeze out. The multi-layer adhesive comprises a first adhesive layer having a first adhesive property and a second adhesive layer having a second adhesive property. The second adhesive property is different from the first adhesive property. The first adhesive layer and the second adhesive layer form a film adhesive. In another embodiment, there is provided a structure comprising a first component and a second component bonded with the multi-layer adhesive. | ||||||
| 35 | Bilaterally asymmetric design for minimizing wave drag | US14628218 | 2015-02-21 | US09522727B2 | 2016-12-20 | William Pflug; Brian J. Tillotson |
| An air vehicle may include a body having forwardly-swept fixed wings or unswept fixed wings. The body may have a longitudinal axis continuously oriented parallel to a forward flight direction when the air vehicle is in flight. The air vehicle may include at least one of the following components being mounted on opposite sides of the body: longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and longitudinally offset protruding aerodynamic surfaces comprising at least one of stabilizers, canards, empennage control surfaces, external stores, and high aspect ratio wings. | ||||||
| 36 | METHOD FOR MANUFACTURING AN AERONAUTICAL TORSION BOX, TORSION BOX AND TOOL FOR MANUFACTURING AN AERONAUTICAL TORSION BOX | US14494012 | 2014-09-23 | US20150343702A1 | 2015-12-03 | Diego GARCÍA MARTÍN; Carlos ROMÓN BANOGON; Pablo CEBOLLA GARROFE; Francisco Javier HONORATO RUIZ; Aquilino GARCíA GARCíA; Francisco Javier CHAMORRO ALONSO; Julio NÚÑEZ DELGADO |
| Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.—positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.—subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8). | ||||||
| 37 | BILATERALLY ASYMMETRIC DESIGN FOR MINIMIZING WAVE DRAG | US14628218 | 2015-02-21 | US20150284073A1 | 2015-10-08 | William Pflug; Brian J. Tillotson |
| An air vehicle may include a body having forwardly-swept fixed wings or unswept fixed wings. The body may have a longitudinal axis continuously oriented parallel to a forward flight direction when the air vehicle is in flight. The air vehicle may include at least one of the following components being mounted on opposite sides of the body: longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and longitudinally offset protruding aerodynamic surfaces comprising at least one of stabilizers, canards, empennage control surfaces, external stores, and high aspect ratio wings. | ||||||
| 38 | TRAILING EDGE OF AN AIRCRAFT AERODYNAMIC SURFACE | US13775471 | 2013-02-25 | US20140339370A1 | 2014-11-20 | Yolanda DE GREGORIO HURTADO; Alberto BALSA GONZALEZ |
| The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7). | ||||||
| 39 | MULTI-LAYER FILM ADHESIVE | US12143939 | 2008-06-23 | US20090317610A1 | 2009-12-24 | Stephen Barnes; Thomas Lowe |
| The disclosure provides for a multi-layer adhesive for reducing squeeze out. The multi-layer adhesive comprises a first adhesive layer having a first adhesive property and a second adhesive layer having a second adhesive property. The second adhesive property is different from the first adhesive property. The first adhesive layer and the second adhesive layer form a film adhesive. In another embodiment, the disclosure provides a structure comprising a first component and a second component bonded with the multi-layer adhesive of the disclosed embodiments. | ||||||
| 40 | Wing and empennage leading edge structure made of thermoplastic material with a stiffened double shell configuration | US12387589 | 2009-05-05 | US20090277996A1 | 2009-11-12 | Ernesto Rinaldi; Salvatore Russo; Generoso Iannuzzo; Massimo Riccio; Giovanni Sagnella |
| A leading edge structure is described for wing structures and empennage, comprising an outer shell suitable to define a front portion of a airfoil. The outer shell is formed by a bent plate of fiber-reinforced thermoplastic resin composite material. The structure further comprisesan inner shell having a convex profile that is oriented in the same direction as the profile of outer shell, which is formed by a bent plate of fiber-reinforced thermoplastic resin composite material and is bonded to the outer shell at the longitudinal edges thereof, andat least one reinforcing element, transversally extending such as to connect the outer shell and inner shell to each other , which is formed by at least one piece of fiber-reinforced resin composite material and is fixed at opposite ends to the outer shell and inner shell, respectively. | ||||||
