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1. 发明授权

US09475238B2 Repair method of repair target portion, and repaired product obtained from repairing 有权
标题翻译：修理目标部位的修理方法，修理后的产品修复
公开(公告)号：US09475238B2
公开(公告)日：2016-10-25
申请号：US14226983
申请日：2014-03-27
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Masayoshi Suhara , Toshikazu Shigetomi , Hideaki Tanaka , Morimasa Ishida , Shuhei Muto
IPC分类号： B29C73/10 , B29C73/12
CPC分类号： B29C73/10 , B29C73/12 , Y10T428/20
摘要： The present invention relates to a repair method using a pre-cured repairing patch, and a repaired product obtained from repairing using the repairing patch, and the present invention securely bonds a repairing patch, where an out-of-plane stiffness is required, to a repair target. In order to cover a repair target portion 23 formed in an outer panel 2 with a repairing patch 30, and bond the repairing patch 30 to a repair target, repairing plates 31, 32 that are formed of fibers and thermosetting resin, and pre-cured before repairing are used as the repairing patch 30, and a laminating step S4 of laminating the repairing plates 31, 32, and a bonding step S7 of bonding the repairing plates 31, 32 to each other are performed.
摘要翻译：本发明涉及一种使用预固化修复补片的修复方法以及使用修补补片进行修复的修补产品，并且本发明将需要的平面外刚度的修复补片牢固地结合到修复目标。为了覆盖用修补补片30形成在外板2中的修补目标部分23，并将修补补片30粘合到修复对象上，由纤维和热固性树脂形成的修复板31,32和预固化在修复之前用作修补贴片30，并且执行层压修复板31,32的层压步骤S4和将修复板31,32彼此粘合的粘合步骤S7。

2. 发明授权

US09809298B2 Drainage system 有权
公开(公告)号：US09809298B2
公开(公告)日：2017-11-07
申请号：US14977928
申请日：2015-12-22
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Hiromu Okamoto , Masayoshi Suhara , Ryuichi Nagase , Toshikazu Shigetomi , Morimasa Ishida
IPC分类号： B64C5/02 , B64C1/14
CPC分类号： B64C5/02 , B64C1/1453
摘要： There is provided a drainage system of an aircraft which discharges moisture having entered inside horizontal tails, which are structures of an airframe of an aircraft, toward the rear end of a fuselage, the drainage system including: a drainage channel which includes an introduction end and a discharge end, and by a capillary action delivers moisture introduced from the introduction end toward the discharge end; and a heater which heats and dries the moisture delivered through the drainage channel. The drainage channel of the present invention is preferably composed of a paper drainage material. It is also preferable that the introduction end of the drainage channel is provided in a lowermost region in the vertical direction within an area in which moisture can accumulate inside the horizontal tails while the aircraft is parked.

3. 发明授权

US10336020B2 Heat dispersion device and repair and joining methods 有权
公开(公告)号：US10336020B2
公开(公告)日：2019-07-02
申请号：US14568279
申请日：2014-12-12
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Toshikazu Shigetomi , Masayoshi Suhara , Morimasa Ishida , Shuhei Muto
IPC分类号： B29C65/00 , B29C65/02 , B32B37/00 , B32B38/00 , B29C73/00 , B32B43/00 , A63B39/00 , A63B41/00 , C09J5/02 , B29C65/78 , B65B9/00 , B30B5/02 , B30B5/04 , B30B15/34 , H05B3/02 , H05B3/34 , H05B3/50 , F28F3/12 , B29C73/34 , B29C73/10 , B29C73/02 , B29C35/04 , B29L31/30 , B29C65/18 , B29C65/48
摘要： The present invention provides a device which can uniformize heat distribution by using an existing heater mat for repairing or joining members. A heat dispersion device includes a bag with a fluid sealed inside, and is disposed on a second surface of a heater mat which has a first surface to be directed toward an object to be heated and the second surface opposite to the first surface. The fluid inside the bag is preferably heated with a heat source.

4. 发明授权

US10288584B2 Method for locating machining position in repair material, and repairing method 有权
公开(公告)号：US10288584B2
公开(公告)日：2019-05-14
申请号：US14875982
申请日：2015-10-06
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Toshikazu Shigetomi , Masatsugu Shimizu , Ryuichi Nagase , Morimasa Ishida , Shuhei Muto
IPC分类号： B23P6/00 , B64F5/40 , B64F5/60 , B29C70/00 , B29C73/10 , B29C73/26 , G01N29/04 , G01N29/07 , G01N29/24 , G01N29/44
摘要： The present invention provides a method for locating a machining position in a repair material that is arranged on a member including a machined portion formed by predetermined machining, the method including: a step of arranging a marker including a portion having a different propagation characteristic of an ultrasonic wave from that of a peripheral portion in the machined portion existing in the member before the repair material is arranged on the member; and a step of applying the ultrasonic wave to the member covered with the repair material and locating the machining position at a position of the marker captured by the ultrasonic wave after the repair material is arranged on the member.

5. 发明授权

US10202202B2 Method for repairing lightning protection material, and member provided with lightning protection material 有权
公开(公告)号：US10202202B2
公开(公告)日：2019-02-12
申请号：US14876137
申请日：2015-10-06
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Toshikazu Shigetomi , Masayoshi Suhara , Morimasa Ishida , Shuhei Muto
IPC分类号： B64D45/02
摘要： The present invention provides a method for repairing a lightning protection material that is made of a metal material and is provided along a surface of a member formed by using a fiber reinforced resin includes: bonding a repair material made of a metal material over a lost region of the member where the lightning protection material is lost by using a liquid adhesive and a sheet-shaped holder that contains and holds the adhesive and is arranged at the lost region.

6. 发明申请

US20160257430A1 INTERNAL STRUCTURE VISUALIZATION METHOD AND AIRCRAFT REPAIR METHOD 审中-公开
标题翻译：内部结构可视化方法和飞机维修方法
公开(公告)号：US20160257430A1
公开(公告)日：2016-09-08
申请号：US15041539
申请日：2016-02-11
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Shotaro Hayashi , Ryuichi Nagase , Masayoshi Suhara , Hiromu Okamoto , Kiwamu Arikawa , Morimasa Ishida
IPC分类号： B64F5/00 , G03B21/00
CPC分类号： G03B21/00 , B64F5/60 , G03B17/54
摘要： An object of the present invention is to visualize an internal structural members, which are covered with a skin and therefore unrecognizable to the naked eye, from the outside of the skin. There is provided an internal structure visualization method applied to a main wing of an aircraft, which includes a skin with a front surface and a back surface and structural members supporting the skin from the back surface side, to display, when necessary, a trace map composed of lines extending along projection regions of the structural members, wherein functional lines, which are a developing element of the trace map, are provided along the projection regions of the front surface, and the trace map is displayed by performing a predetermined process on a predetermined region of the front surface where the functional lines are provided.
摘要翻译：本发明的一个目的是从皮肤的外部可视化由皮肤覆盖并且因此不能被肉眼识别的内部结构构件。提供了一种应用于飞机的主翼的内部结构可视化方法，其包括具有前表面和后表面的皮肤以及从背面侧支撑皮肤的结构构件，以在必要时显示轨迹图由沿着结构构件的突出区域延伸的线组成，其中作为轨迹图的显影元件的功能线沿着前表面的投影区域设置，并且轨迹图通过在提供功能线的前表面的预定区域。

7. 发明申请

US20140141190A1 METHOD OF REPAIRING COMPOSITE MATERIAL AND COMPOSITE MATERIAL 有权
标题翻译：修复复合材料和复合材料的方法
公开(公告)号：US20140141190A1
公开(公告)日：2014-05-22
申请号：US14079952
申请日：2013-11-14
申请人： Mitsubishi Aircraft Corporation
发明人： Toshikazu Shigetomi , Masayoshi Suhara , Morimasa Ishida , Shuhei Muto
IPC分类号： B29C73/24 , B64C3/26
CPC分类号： B64C3/26 , B29C73/06 , B29C73/10 , B29C73/26 , B29C2073/264 , B29C2073/268 , B32B37/1009 , B32B38/10 , B64F5/40 , Y10T428/20
摘要： A method of repairing a composite material is provided in which a frustum-shaped portion of a composite material is removed, and the composite material and a repair material are bonded with each other while evacuating. The repair method includes step S2 of removing a damaged part 11 from the front side so as to pass through in the thickness direction while leaving a support wall protruding inward in the radial direction from the periphery of the top face of the frustum-shaped portion; step S3 of sealing the back side by placing a sealing plate, which is inserted from the front side into a through hole formed by the removing step, on the support wall; step S5 of placing the repair material through an adhesive on the composite material where the frustum-shaped portion has been removed; and step S6 of evacuating in a state in which the front side is sealed.
摘要翻译：提供一种修复复合材料的方法，其中去除复合材料的截头圆锥形部分，并且复合材料和修复材料在抽真空时彼此粘合。修理方法包括步骤S2，从前侧移除损坏部件11，使其沿着厚度方向通过，同时留下从截头圆锥形部分的顶面的周边沿径向向内突出的支撑壁; 通过将从前侧插入到由移除步骤形成的通孔中的密封板放置在支撑壁上来密封背面的步骤S3; 将修复材料通过粘合剂放置在去除了截头圆锥形部分的复合材料上的步骤S5; 以及在前侧被密封的状态下抽真空的步骤S6。

8. 发明授权

US10940937B2 Aircraft reinforcing structure 有权
公开(公告)号：US10940937B2
公开(公告)日：2021-03-09
申请号：US15041503
申请日：2016-02-11
申请人： Mitsubishi Aircraft Corporation
发明人： Hiromu Okamoto , Masayoshi Suhara , Ryuichi Nagase , Toshikazu Shigetomi , Morimasa Ishida
IPC分类号： B64C3/26
摘要： An object of the present invention is to prevent accumulation of moisture which has entered inside a honeycomb sandwich panel used for a stressed-skin structure of an aircraft. A reinforcing structure includes an outer panel constituting an outer shell of a tailplane and a honeycomb sandwich panel reinforcing the outer panel. The honeycomb sandwich panel includes a honeycomb core having a plurality of cells, an outer skin joined on the front side of the honeycomb core and disposed on the side of the outer panel, and an inner skin joined on the back side of the honeycomb core and disposed on the inner side of the tailplane. The inner skin has drainage channels formed therein through which each of the plurality of cells communicates with the outside of the honeycomb sandwich panel.

9. 发明授权

US09815546B2 Method for repairing honeycomb core sandwich structural body and repaired product 有权
公开(公告)号：US09815546B2
公开(公告)日：2017-11-14
申请号：US14221595
申请日：2014-03-21
申请人： MITSUBISHI AIRCRAFT CORPORATION
发明人： Kotoyo Mizuno , Toshikazu Shigetomi , Hideaki Tanaka , Morimasa Ishida , Shuhei Muto
IPC分类号： B29C73/00 , B32B43/00 , B29C65/00 , B32B37/00 , H05K13/04 , C09J5/00 , B32B3/26 , B32B3/00 , B32B3/12 , B64C3/26 , B64C1/12 , B29C73/06 , B64F5/40 , B29C73/10 , B32B37/12 , B29C65/52 , B29C65/54 , B29L31/60
CPC分类号： B64C3/26 , B29C65/524 , B29C65/542 , B29C73/06 , B29C73/10 , B29L2031/608 , B32B3/12 , B32B43/00 , B32B2037/1253 , B64C1/12 , B64F5/40 , Y10T428/20
摘要： A method for repairing a honeycomb core sandwich structural body according to the present invention is a method in which a damaged portion that is formed in a honeycomb core sandwich structural body where a honeycomb structured core is held between a first outer skin and a second outer skin and that reaches the core through the first outer skin is repaired, the method including: a repair material mounting step of mounting a repair material on the damaged portion, the repair material including a patch that covers an opening of the damaged portion, and one or a plurality of braces that support the patch; a patch bonding step of bonding the patch to the first outer skin; and a brace bonding step of bonding the brace to the second outer skin or the core.

10. 发明申请

US20160236768A1 AIRCRAFT REINFORCING STRUCTURE 审中-公开
标题翻译：飞机加固结构
公开(公告)号：US20160236768A1
公开(公告)日：2016-08-18
申请号：US15041503
申请日：2016-02-11
申请人： Mitsubishi Aircraft Corporation
发明人： Hiromu Okamoto , Masayoshi Suhara , Ryuichi Nagase , Toshikazu Shigetomi , Morimasa Ishida
IPC分类号： B64C3/26
CPC分类号： B64C3/26
摘要： An object of the present invention is to prevent accumulation of moisture which has entered inside a honeycomb sandwich panel used for a stressed-skin structure of an aircraft. A reinforcing structure includes an outer panel constituting an outer shell of a tailplane and a honeycomb sandwich panel reinforcing the outer panel. The honeycomb sandwich panel includes a honeycomb core having a plurality of cells, an outer skin joined on the front side of the honeycomb core and disposed on the side of the outer panel, and an inner skin joined on the back side of the honeycomb core and disposed on the inner side of the tailplane. The inner skin has drainage channels formed therein through which each of the plurality of cells communicates with the outside of the honeycomb sandwich panel.
摘要翻译：本发明的目的是防止进入用于飞机的应力 - 皮肤结构的蜂窝夹层板内的水分积聚。加强结构包括构成尾板外壳的外板和加强外板的蜂窝夹层板。蜂窝状夹层板包括具有多个单元的蜂窝芯，连接在蜂窝芯的前侧并且设置在外板一侧的外皮和在蜂窝芯的背面上接合的内皮，以及设置在尾翼的内侧。内皮具有形成在其中的多个细胞中的每一个与蜂窝夹心板的外部连通的排水通道。

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