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1. 发明授权

US06976658B2 Cockpit door of aircraft 失效
标题翻译：飞机的驾驶舱门
公开(公告)号：US06976658B2
公开(公告)日：2005-12-20
申请号：US10747309
申请日：2003-12-30
申请人： Yasuo Sekikawa , Toshihisa Kasuya , Tadashi Watanabe
发明人： Yasuo Sekikawa , Toshihisa Kasuya , Tadashi Watanabe
IPC分类号： B64C1/14 , B64D45/00
CPC分类号： B64D45/0015 , B64C1/1469 , B64C2001/009
摘要： A cockpit door comprises a hinge 20 provided to one surface and a latch device provided to the other side that can be operated only from the cockpit side. To the inside of a door panel is disposed a reinforcement member 110 formed by laminating multiple layers of sheets with thermoplastic adhesives, the sheets formed by laminating aromatic polyamide fiber onto a honeycomb panel and processing the same into sheet form. A titanium alloy reinforcement plate 400 is disposed to cover the gap G1 between the door body and flap 60. Mounting portions 150 and 160 are provided to the rim of the reinforcement member body 110, and rivet holes 180 are provided thereto. The mounting portion is bent 90 degrees and fixed to the frame by rivets.
摘要翻译：驾驶舱门包括设置在一个表面上的铰链20和设置在仅能从驾驶舱侧操作的另一侧的闩锁装置。在门板的内部设置有通过将热塑性粘合剂层叠多层片而形成的加强部件110，该片材通过将芳族聚酰胺纤维层压在蜂窝板上而形成片状。钛合金加强板400设置成覆盖门体和折翼60之间的间隙G 1 1。安装部分150和160设置在加强构件主体110的边缘上，并且向其提供铆钉孔180。安装部分弯曲90度，并通过铆钉固定在框架上。

2. 发明申请

US20050082433A1 Cockpit door of aircraft 有权
公开(公告)号：US20050082433A1
公开(公告)日：2005-04-21
申请号：US10759252
申请日：2004-01-20
申请人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
发明人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
IPC分类号： E06B7/32 , B64C1/14 , B64D45/00 , E06B5/00
CPC分类号： B64C1/1469 , B64C2001/009 , B64D45/0015
摘要： A cockpit door body 10 can be opened toward a cockpit in a direction shown by arrow R1 by a crew inside a cockpit 3 by manipulating a knob on a first hinge device 40. When rapid decompression occurs in the cockpit, a mechanical pressure-sensitive device of the first hinge device 40 operates to release a bolt from a catch. By the difference in pressure between the cabin and the cockpit, the door body 10 opens in the direction of arrow R1 to thereby reduce pressure difference. When rapid decompression occurs in cabin 4, a second latch device 60 detects this pressure difference and operates mechanically to rotate a link lever 62 to release a stopper 64 from a catch 66. Flaps 30 and 32 are opened toward cabin 4 in the direction of arrow R2 by the difference in pressure between the cockpit and cabin to thereby reduce pressure difference.

3. 发明授权

US07896290B2 Latch device of cockpit door of an aircraft 有权
标题翻译：飞机驾驶舱门的锁定装置
公开(公告)号：US07896290B2
公开(公告)日：2011-03-01
申请号：US11905519
申请日：2007-10-02
申请人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
发明人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
IPC分类号： B64C1/14
CPC分类号： B64C1/1469 , B64C2001/009 , B64D45/0015 , E05B51/023
摘要： A latch device for detecting pressure reduction of a cockpit in an aircraft and releasing a bolt and a stopper device are provided so as to prevent a cockpit door from unexpectedly opening by an impact. A main latch device 100 of the cockpit door has a frame 112 fixed to a door panel, and a latch base 120 is mounted to the frame 112 capable of pivotal rotation with a pin 122 as a fulcrum. A bolt 132 is inserted into a catch in conjunction with a door handle 130. A holding/releasing portion 150 holds the latch base 120. When a pressure difference occurs between a cockpit 4 and a cabin 5, a pressure-sensing piston 160 is pushed in, a trigger 170 and a flapper 180 are rotated and the latch base 120 is released. A stopper device 190 regulates movement of the trigger 170 by movement of an inertial piston 192 when an impact force is applied from the cabin 5 side.
摘要翻译：用于检测飞行器中的驾驶舱的减压并释放螺栓和止动装置的闩锁装置被设置成防止驾驶舱门被冲击意外地打开。驾驶舱门的主闩锁装置100具有固定到门板的框架112，并且闩锁基座120安装到能够以销122作为支点枢转旋转的框架112。螺栓132与门把手130一起插入锁扣中。保持/释放部分150保持闩锁基座120.当驾驶舱4和驾驶舱5之间出现压力差时，压力传感活塞160被推动触发器170和挡板180旋转并且闩锁底座120被释放。止动装置190通过惯性活塞192的移动来调节触发器170的运动，当从机舱5侧施加冲击力时。

4. 发明授权

US06945497B2 Cockpit door of aircraft 有权
标题翻译：飞机的驾驶舱门
公开(公告)号：US06945497B2
公开(公告)日：2005-09-20
申请号：US10759252
申请日：2004-01-20
申请人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
发明人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
IPC分类号： E06B7/32 , B64C1/14 , B64D45/00 , E06B5/00
CPC分类号： B64C1/1469 , B64C2001/009 , B64D45/0015
摘要： A cockpit door body 10 can be opened toward a cockpit in a direction shown by arrow R1 by a crew inside a cockpit 3 by manipulating a knob on a first hinge device 40. When rapid decompression occurs in the cockpit, a mechanical pressure-sensitive device of the first hinge device 40 operates to release a bolt from a catch. By the difference in pressure between the cabin and the cockpit, the door body 10 opens in the direction of arrow R1 to thereby reduce pressure difference. When rapid decompression occurs in cabin 4, a second latch device 60 detects this pressure difference and operates mechanically to rotate a link lever 62 to release a stopper 64 from a catch 66. Flaps 30 and 32 are opened toward cabin 4 in the direction of arrow R2 by the difference in pressure between the cockpit and cabin to thereby reduce pressure difference.
摘要翻译：驾驶舱门体10可以通过操纵第一铰链装置40上的旋钮，由驾驶舱3内的乘务员沿着箭头R 1所示的方向朝驾驶舱打开。当快速减压发生在驾驶舱，第一铰链装置40的机械压敏装置操作以从卡扣释放螺栓。通过驾驶舱和驾驶舱之间的压力差，门体10沿箭头R 1 1的方向打开，从而减小压力差。当在机舱4中发生快速减压时，第二闩锁装置60检测该压力差并机械地操作以使连杆62旋转以从止动件66释放止动件64.挡板30和32沿箭头方向朝向驾驶室4打开 R 2通过驾驶舱和驾驶室之间的压力差来降低压力差。

5. 发明申请

US20080111025A1 Latch device of cockpit door of an aircraft 有权
标题翻译：飞机驾驶舱门的锁定装置
公开(公告)号：US20080111025A1
公开(公告)日：2008-05-15
申请号：US11905519
申请日：2007-10-02
申请人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
发明人： Fumiaki Saku , Tadashi Watanabe , Yasuo Sekikawa
IPC分类号： B64C1/14
CPC分类号： B64C1/1469 , B64C2001/009 , B64D45/0015 , E05B51/023
摘要： A latch device for detecting pressure reduction of a cockpit in an aircraft and releasing a bolt and a stopper device are provided so as to prevent a cockpit door from unexpectedly opening by an impact. A main latch device 100 of the cockpit door has a frame 112 fixed to a door panel, and a latch base 120 is mounted to the frame 112 capable of pivotal rotation with a pin 122 as a fulcrum. A bolt 132 is inserted into a catch in conjunction with a door handle 130. A holding/releasing portion 150 holds the latch base 120. When a pressure difference occurs between a cockpit 4 and a cabin 5, a pressure-sensing piston 160 is pushed in, a trigger 170 and a flapper 180 are rotated and the latch base 120 is released. A stopper device 190 regulates movement of the trigger 170 by movement of an inertial piston 192 when an impact force is applied from the cabin 5 side.
摘要翻译：用于检测飞行器中的驾驶舱的减压并释放螺栓和止动装置的闩锁装置被设置成防止驾驶舱门被冲击意外地打开。驾驶舱门的主闩锁装置100具有固定到门板的框架112，并且闩锁基座120安装到能够以销122作为支点枢转旋转的框架112。螺栓132与门把手130一起插入到卡扣中。保持/释放部分150保持闩锁基座120。当驾驶舱4和驾驶舱5之间发生压力差时，压力传感活塞160被推入，触发器170和挡板180旋转并且闩锁底座120被释放。止动装置190通过惯性活塞192的移动来调节触发器170的运动，当从机舱5侧施加冲击力时。

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