公开(公告)号：US08899522B2

公开(公告)日：2014-12-02

申请号：US13229927

申请日：2011-09-12

Applicant: Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Esteban Martino Gonzalez ,  Enrique Guinaldo Fernandez ,  Pablo Goya Abaurrea

Inventor： Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Esteban Martino Gonzalez ,  Enrique Guinaldo Fernandez ,  Pablo Goya Abaurrea

IPC: B64C1/06 ,  B64C1/12

CPC classification number: B64C1/064 ,  B64C1/12

Abstract: A fuselage section of an aircraft includes a skin, a plurality of frames positioned transversely to a longitudinal axis of a fuselage of the aircraft, and a plurality of longitudinal stringers at least one of which is configured with a closed transversal section including a stringer hat, two stringer webs, and two stringer feet joined to the skin. At least one of the frames is configured in at least one sector with a frame foot joined to the skin, a frame web having holes at crossing zones with the stringers, a frame cap, and a frame cap extension which does not interfere with the stringers. The frames are joined to, at least, the stringer hats at crossing zones of the frames and the stringer hats.

Abstract translation: 飞行器的机身部分包括皮肤，横向于飞行器的机身的纵向轴线定位的多个框架，以及多个纵向纵梁，其中至少一个纵向纵梁具有封闭的横向部分，其包括纵梁帽， 两条桁条和两根连接在皮肤上的桁条脚。 至少一个框架被配置在具有连接到皮肤的框架脚的至少一个扇区中，具有与桁条交叉的区域的框架的框架框架，框架盖和不干扰桁条的框架延伸部 。 框架至少连接到框架和纵梁帽的交叉区域的纵梁帽。

公开(公告)号：US20130099057A1

公开(公告)日：2013-04-25

申请号：US13339897

申请日：2011-12-29

Applicant: Esteban Martino Gonzalez ,  Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Enrique Guinaldo Fernandez ,  Julien Guillemaut

Inventor： Esteban Martino Gonzalez ,  Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Enrique Guinaldo Fernandez ,  Julien Guillemaut

IPC: B64C1/00

CPC classification number: B64C1/068 ,  B64C1/06 ,  B64C1/061 ,  B64C1/062 ,  B64D27/14 ,  B64D2027/005 ,  Y02T50/66

Abstract: Aircraft fuselage section (32) subjected to impacts of external bodies, the aircraft fuselage having a curved shape with at least a vertical symmetry plane (A-A) and a central longitudinal axis and comprising a skin (35) and a plurality of frames (37) arranged perpendicularly to said longitudinal axis (33), the aircraft fuselage section also comprising at least an inner reticular structure (51, 53) mounted on a supporting structure (41, 43) comprising longitudinal beams (39) attached to the skin (35) and interconnected with said frames (37), said inner reticular structure (51, 53) being arranged for creating at least one closed cell (75) with the skin (35) for improving its resistance and its damage tolerance to said impacts. Said inner reticular structure (51, 53) can be formed by panels (61), rods (65, 65′), cables (67, 67′) or belts (69, 69′).

Abstract translation: 飞机机身部分受到外部物体的撞击，飞机机身具有至少具有垂直对称平面（AA）和中心纵向轴线的弯曲形状并且包括皮肤（35）和多个框架（37） 飞行器机身部分还包括安装在支撑结构（41,43）上的至少一个内部网状结构（51,53），该内部网状结构（51,53）包括连接到皮肤（35）的纵向梁（39） 并且与所述框架（37）相互连接，所述内网状结构（51,53）布置成用于产生具有皮肤（35）的至少一个闭孔（75），以改善其抵抗力及其对所述冲击的损伤容限。 所述内网状结构（51,53）可以由面板（61），杆（65,65'），电缆（67,67'）或皮带（69,69'）形成。

公开(公告)号：US20120166037A1

公开(公告)日：2012-06-28

申请号：US13041749

申请日：2011-03-07

Applicant: Eduardo VINUE SANTOLALLA ,  Diego FOLCH CORTES ,  Esteban MARTINO GONZALEZ ,  Enrique GUINALDO FERNANDEZ ,  Pablo GOYA ABAURREA

Inventor： Eduardo VINUE SANTOLALLA ,  Diego FOLCH CORTES ,  Esteban MARTINO GONZALEZ ,  Enrique GUINALDO FERNANDEZ ,  Pablo GOYA ABAURREA

IPC: G01M17/00 ,  G06F19/00

CPC classification number: B64D45/00 ,  B64D2045/0065

Abstract: Commercial aircraft (11) having a black box (41) comprising a flight data recorder (49) connected to suitable acquisition units (13, 14, 15) for recording information required for crash investigation purposes inside a container (43), wherein the aircraft (11) comprises a crash detection device (17); the black box (41) is installed in a suitable location for being ejected outside the aircraft in a crash event through a duct (21, 31) having its exit in a fuselage area where the ejected black box (41) would not impact on the aircraft; the aircraft (11) also comprises ejection means (23, 33), controlled by a black box ejection control unit (19) connected to said crash detection device (17), for ejecting the black box (41) through said duct (21, 31), when an impending crash is detected by said crash detection device (17).

Abstract translation: 具有黑盒（41）的商用飞机（11）包括连接到适合的采集单元（13,14,15）的飞行数据记录器（49），用于将容器（43）内的碰撞调查目的所需的信息记录在其中， （11）包括碰撞检测装置（17）; 黑盒（41）安装在合适的位置，以便在碰撞事件中通过其出口在机身区域中的出口的导管（21,31）在飞机外部被弹出，其中弹出的黑盒（41）将不会撞击 飞机; 飞机（11）还包括由连接到所述碰撞检测装置（17）的黑匣子弹出控制单元（19）控制的喷射装置（23,33），用于通过所述导管（21）喷射黑盒（41） 当所述碰撞检测装置（17）检测到即将发生的碰撞时，

公开(公告)号：US08678314B2

公开(公告)日：2014-03-25

申请号：US13339897

申请日：2011-12-29

Applicant: Esteban Martino Gonzalez ,  Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Enrique Guinaldo Fernandez ,  Julien Guillemaut

Inventor： Esteban Martino Gonzalez ,  Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Enrique Guinaldo Fernandez ,  Julien Guillemaut

IPC: B64C1/10

CPC classification number: B64C1/068 ,  B64C1/06 ,  B64C1/061 ,  B64C1/062 ,  B64D27/14 ,  B64D2027/005 ,  Y02T50/66

Abstract: Aircraft fuselage section (32) subjected to impacts of external bodies, the aircraft fuselage having a curved shape with at least a vertical symmetry plane (A-A) and a central longitudinal axis and comprising a skin (35) and a plurality of frames (37) arranged perpendicularly to said longitudinal axis (33), the aircraft fuselage section also comprising at least an inner reticular structure (51, 53) mounted on a supporting structure (41, 43) comprising longitudinal beams (39) attached to the skin (35) and interconnected with said frames (37), said inner reticular structure (51, 53) being arranged for creating at least one closed cell (75) with the skin (35) for improving its resistance and its damage tolerance to said impacts. Said inner reticular structure (51, 53) can be formed by panels (61), rods (65, 65′), cables (67, 67′) or belts (69, 69′).

Abstract translation: 飞机机身部分受到外部物体的撞击，飞机机身具有至少具有垂直对称平面（AA）和中心纵向轴线的弯曲形状并且包括皮肤（35）和多个框架（37） 飞行器机身部分还包括安装在支撑结构（41,43）上的至少一个内部网状结构（51,53），该内部网状结构（51,53）包括连接到皮肤（35）的纵向梁（39） 并且与所述框架（37）相互连接，所述内网状结构（51,53）布置成用于产生具有皮肤（35）的至少一个闭孔（75），以改善其抵抗力及其对所述冲击的损伤容限。 所述内网状结构（51,53）可以由面板（61），杆（65,65'），电缆（67,67'）或皮带（69,69'）形成。

公开(公告)号：US08489259B2

公开(公告)日：2013-07-16

申请号：US13041749

申请日：2011-03-07

Applicant: Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Esteban Martino Gonzalez ,  Enrique Guinaldo Fernandez ,  Pablo Goya Abaurrea

Inventor： Eduardo Vinue Santolalla ,  Diego Folch Cortes ,  Esteban Martino Gonzalez ,  Enrique Guinaldo Fernandez ,  Pablo Goya Abaurrea

IPC: G06F7/70 ,  G06F19/00 ,  G06G7/00 ,  G06G7/76

CPC classification number: B64D45/00 ,  B64D2045/0065

Abstract: Commercial aircraft (11) having a black box (41) comprising a flight data recorder (49) connected to suitable acquisition units (13, 14, 15) for recording information required for crash investigation purposes inside a container (43), wherein the aircraft (11) comprises a crash detection device (17); the black box (41) is installed in a suitable location for being ejected outside the aircraft in a crash event through a duct (21, 31) having its exit in a fuselage area where the ejected black box (41) would not impact on the aircraft; the aircraft (11) also comprises ejection means (23, 33), controlled by a black box ejection control unit (19) connected to said crash detection device (17), for ejecting the black box (41) through said duct (21, 31), when an impending crash is detected by said crash detection device (17).

Abstract translation: 具有黑盒（41）的商用飞机（11）包括连接到适合的采集单元（13,14,15）的飞行数据记录器（49），用于将容器（43）内的碰撞调查目的所需的信息记录在其中， （11）包括碰撞检测装置（17）; 黑盒（41）安装在合适的位置，以便在碰撞事件中通过其出口在机身区域中的出口的导管（21,31）在飞机外部被弹出，其中弹出的黑盒（41）将不会撞击 飞机; 飞机（11）还包括由连接到所述碰撞检测装置（17）的黑匣子弹出控制单元（19）控制的喷射装置（23,33），用于通过所述导管（21）喷射黑盒（41） 当所述碰撞检测装置（17）检测到即将发生的碰撞时，

公开(公告)号：US20120248247A1

公开(公告)日：2012-10-04

申请号：US13229927

申请日：2011-09-12

Applicant: Eduardo VINUE SANTOLALLA ,  Diego FOLCH CORTES ,  Esteban MARTINO GONZALEZ ,  Enrique GUINALDO FERNANDEZ ,  Pablo GOYA ABAURREA

Inventor： Eduardo VINUE SANTOLALLA ,  Diego FOLCH CORTES ,  Esteban MARTINO GONZALEZ ,  Enrique GUINALDO FERNANDEZ ,  Pablo GOYA ABAURREA

IPC: B64C1/06

CPC classification number: B64C1/064 ,  B64C1/12

Abstract: Fuselage section of an aircraft whose structure comprises a skin (10), a plurality of frames (30) positioned transversely to the longitudinal axis of the fuselage and a plurality of longitudinal stringers (20); the stringers being configured with a closed transversal section comprising a hat (21), two webs (23, 25) and two feet (27, 29) joined to the skin (10); the frames (30) being configured in at least one its sectors with a foot (31) joined to the skin (10), a web (33) having holes at the crossing zones with said stringers (20), a cap (35) and a cap extension (37) which does not interfere with the stringers (20); the frames (30) being joined to, at least, the stringer hats (21) at their crossing zones.

Abstract translation: 飞机的机身部分，其结构包括皮肤（10），横向于机身的纵向轴线定位的多个框架（30）和多个纵向纵梁（20）; 桁条被构造成具有闭合的横向部分，包括帽子（21），连接到皮肤（10）的两个腹板（23,25）和两个脚部（27,29）; 所述框架（30）在其至少一个扇区中配置有连接到所述皮肤（10）的脚（31），在所述横梁（20）的交叉区域具有孔的腹板（33），盖（35） 和不影响桁条（20）的盖延伸部（37）。 所述框架（30）在其交叉区域至少连接到所述纵梁帽（21）。