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1. 发明授权

US5738303A Mechanism for arming, disarming and activating airplane emergency slide evacuation systems 失效
标题翻译：布防，解除和激活飞机紧急滑行疏散系统的机制
公开(公告)号：US5738303A
公开(公告)日：1998-04-14
申请号：US441283
申请日：1995-05-15
申请人： Tomio Hamatani , David Brockmeyer , Katsuya Ikeda , Hisao Kondo
发明人： Tomio Hamatani , David Brockmeyer , Katsuya Ikeda , Hisao Kondo
IPC分类号： A62B1/20 , A62B99/00 , B64C1/14 , B64D25/14 , B64C1/34
CPC分类号： B64D25/14 , Y10S244/905
摘要： A mechanism(10) arms, disarms, and activates an airplane emergency evacuation system having a slide with one end connected to a girt bar (16). The mechanism includes floor fittings (18) mountable below and at each edge of the airplane door (14). Each floor fitting includes a base (32) defining a notch (40) for receiving the girt bar and a pawl (42) mounted to the base. The pawl rotates relative to the base from a locked position preventing removal of the girt bar from the notch, and to an unlocked position permitting removal of the girt bar. Support fittings (20) mountable to the door, engages the floor fittings when the door is closed and locked. A first jaw (58) extends downwardly to one side of the notch, and faces generally towards the notch from the support fitting. First and second linkage members (60) and (70) connect to one another and rotatably mount to the support fitting. A second jaw (94) extends from the second linkage member and faces generally towards the first jaw. The mechanism operates to rotate the second jaw towards the first jaw to capture the girt bar therebetween, and to rotate the pawl to the unlocked position to disarm the system and allow normal use of the door. To arm the system, the second jaw is rotated in the opposite direction which releases the girt bar and causes the pawl to securely lock the girt bar to the floor of the airplane.
摘要翻译：一种机构（10）臂，分离和激活具有滑动件的飞机紧急撤离系统，其一端连接到密封条（16）。该机构包括安装在飞机门（14）的每个边缘下方和下方的地板配件（18）。每个地板配件包括限定用于接收衬垫条的凹口（40）的底座（32）和安装到基座的棘爪（42）。棘爪相对于基座从锁定位置旋转，从而防止将缝线从凹口移除，并且到解锁位置，从而能够移除棉条。当门关闭并锁定时，可安装到门上的支撑配件（20）与地板配件接合。第一钳口（58）向下延伸到凹口的一侧，并且大致朝向来自支撑配件的凹口面对。第一和第二连杆构件（60）和（70）彼此连接并可旋转地安装到支撑配件。第二钳口（94）从第二连杆构件延伸并且大致面向第一钳口。该机构用于使第二钳口朝向第一钳口旋转，以在其间捕获间隙棒，并且将棘爪旋转到解锁位置以解除系统并允许门的正常使用。为了操纵系统，第二钳口沿相反的方向旋转，释放出细条，并使棘爪牢牢地锁定到飞机的地板上。

2. 发明授权

US5289615A Aircraft door hinge mechanism 失效
标题翻译：飞机门铰链机构
公开(公告)号：US5289615A
公开(公告)日：1994-03-01
申请号：US791663
申请日：1991-11-08
申请人： Eddie D. Banks , Tomio Hamatani , Hajime Kishi , Richard B. Odell , Takayoshi Urasawa
发明人： Eddie D. Banks , Tomio Hamatani , Hajime Kishi , Richard B. Odell , Takayoshi Urasawa
IPC分类号： B64C1/14 , E05D3/06 , E05D15/28
CPC分类号： B64C1/143 , B64C1/1407 , E05D3/12 , E05D3/122 , E05Y2900/132 , E05Y2900/502 , Y10S244/905 , Y10T16/547
摘要： A hinge assembly (14) for attaching a translating-motion-type aircraft door (10) to an aircraft fuselage (12) is disclosed. The hinge assembly (14) includes a fitting (28) that is pivotally attached to the portion of the aircraft fuselage (14) adjacent the door opening (16) in the fuselage in which the door (10) is normally seated. The door is attached to the hinge fitting (28) by way of a universal shaft (30) that is rotatably attached to the free end of the hinge fitting (28). A drivebelt (32) is anchored at one end to the aircraft fuselage (12) and is attached at the opposed end to the universal shaft (30) so as to move in unison with the shaft. When the hinge assembly (14) of this invention is opened, the hinge fitting (28) pulls on the drivebelt (32) so as to cause its movement and the subsequent movement of the universal shaft (30). The universal shaft (30) is rotated about the hinge fitting (28) so as to maintain the door (10) attached thereto in a constant angular relationship relative to the longitudinal axis of the aircraft fuselage (12).
摘要翻译：公开了一种用于将平移运动型飞机门（10）附接到飞机机身（12）的铰链组件（14）。铰链组件（14）包括一个配件（28），该配件（28）可枢转地附接到靠近门（10）正常就座的机身中与门开口（16）相邻的飞行器机身（14）的部分。门通过可旋转地附接到铰链配件（28）的自由端的通用轴（30）附接到铰链配件（28）。驱动带（32）在一端被锚定到飞行器机身（12），并且在相对的端部附接到通用轴（30），以便与轴一致地移动。当本发明的铰链组件（14）打开时，铰链配件（28）拉动驱动带（32），以使其运动和随后的万向轴（30）的移动。万向轴（30）围绕铰链配件（28）旋转，以便将门（10）相对于飞行器机身（12）的纵向轴线保持恒定的角度关系。

3. 发明授权

US5180121A Aircraft door hinge mechanism with selectively triggerable actuator 失效
标题翻译：具有选择性触发执行器的飞机门铰链机构
公开(公告)号：US5180121A
公开(公告)日：1993-01-19
申请号：US696245
申请日：1991-05-06
申请人： Eddie D. Banks , Tomio Hamatani , Chung-Wah F. Wong
发明人： Eddie D. Banks , Tomio Hamatani , Chung-Wah F. Wong
IPC分类号： B64C1/14 , E05F15/04
CPC分类号： B64C1/143 , B64C1/1407 , E05F15/54 , E05F15/72 , E05Y2900/502 , E05Y2900/531 , Y10T16/53992
摘要： A cam actuator (12) for rapidly opening an aircraft door (14) that is attached to an aircraft fuselage (18) by a hinge assembly (26). The actuator includes a piston (40), a piston rod (42) that is secured to the piston and rotating sleeve (44) that is fitted over the piston rod that functions as the hinge pin between a hinge clevis (26) on the aircraft and a hinge arm lug (54) on the hinge assembly. The piston is contained within a housing (38) adapted to receive a pressurized pneumatic gas. An annular cam (50) through which the piston rod travels and that is formed with an outer surface (104) having a helical profile is attached to the hinge clevis. A cam follower (46) is attached for the sleeve so as to rotate in unison therewith. The hinge arm lug (54) is also secured to the sleeve (44) for rotation. When the actuator of this invention is triggered, the piston rod (42) urges the cam follower (46 ) against the cam (50) so as to cause the cam follower to rotate. The cam follower (46) in turn rotates the sleeve (44) so as to simultaneously rotate the hinge arm lug (54). As a result of this rotation, the hinge is pivoted away from the hinge clevis so as to urge the aircraft door open.

4. 发明授权

US5241725A Self-aligning aircraft door stop pin assembly 失效
标题翻译：自调心飞机门挡销组装
公开(公告)号：US5241725A
公开(公告)日：1993-09-07
申请号：US905264
申请日：1992-06-26
申请人： Tomio Hamatani , John A. Meisch
发明人： Tomio Hamatani , John A. Meisch
IPC分类号： E05F5/02
CPC分类号： E05F5/025 , E05Y2900/531 , Y10T16/61 , Y10T16/6285
摘要： A self-aligning aircraft door stop pin assembly, which minimizes galling and compensates for misalignment problems. The assembly consists of a base pad containing a concave spherical recess, which is swaged onto the convex spherical head at one end of a threaded stop pin. The base pad is free to align, so as to make full face contact with the structural stop pad. The sperical interface between stop pin and base pad is provided with lubrication, on one or both parts.
摘要翻译：自动对准飞机门挡销组件，其最小化磨损并补偿不对准问题。该组件包括一个包含凹形球形凹槽的基座，该凹槽在螺纹止动销的一端被模压到凸形球形头上。基座可自由对准，以便与结构停止垫完全面接触。止动销和底座之间的精密接口在一个或两个部件上提供润滑。

5. 发明授权

US4497462A Outward opening electrically powered plug-type cargo door 失效
公开(公告)号：US4497462A
公开(公告)日：1985-02-05
申请号：US479676
申请日：1983-03-28
申请人： Tomio Hamatani
发明人： Tomio Hamatani
IPC分类号： B64C1/14
CPC分类号： B64C1/1415
摘要： An outward opening plug-type cargo door for an aircraft is movable between a closed position in which the door blocks an entry opening into the aircraft and an open position in which the door is spaced from the entry opening. The door hinges are directly driven by irreversible rotary actuators. When the door is positioned adjacent the entry opening, a latch mechanism is operable to move the door between a latched and an unlatched position. In the latched position, the door is secured from outboard movement by a plurality of stop pins spaced about the periphery of the door that are located inboard of a series of stop pads mounted at spaced locations about the periphery of the door opening. When the latch mechanism is operated, the door is lifted to free the stop pins from their location behind the stop pads and permit outboard movement of the door. The movement of the door between the latched and lifted positions is programmed by a guide mechanism comprised of guide channels mounted on first and second edges of the door opening that are cooperably engaged by rollers rotatably mounted on first and second edges of the door. The guide channels have detents formed therein and the guide rollers engage the detents when the door is in the latched position and the pressure within the aircraft is greater than the pressure exterior to the aircraft. The detents resist upward vertical movement of the door to maintain the door securely in the latched position to prevent accidental blowout of the door caused by the pressure differential. A power unit is provided to operate the latch mechanism to move the door between the latched and lifted positions and a second power unit is provided to drive the door between the closed and open position. Sensor switches are positioned about the door and entry opening to sequence application of power to the two power units to open and close and latch and unlatch the door. A primary manual drive mechanism is provided coupled to the latch mechanism and the hinge mechanism to operate the latch mechanism and the hinge mechanism in the case of failure of the power unit. A secondary manual drive system is also provided coupled to the hinge mechanism to open and close the door upon failure of the power unit or the primary manual drive.

6. 发明授权

US5687452A Hydraulic snubber for aircraft 失效
标题翻译：飞机液压缓冲器
公开(公告)号：US5687452A
公开(公告)日：1997-11-18
申请号：US432846
申请日：1995-05-02
申请人： Tomio Hamatani , Sun Gil Kim , Donald K. Franklin , Michael P. Conner
发明人： Tomio Hamatani , Sun Gil Kim , Donald K. Franklin , Michael P. Conner
IPC分类号： B64C1/14 , F16F9/18 , F16F9/20 , E05F5/02
CPC分类号： F16F9/20 , B64C1/1407 , B64C1/143 , Y10T137/7771 , Y10T16/61
摘要： A snubber is disclosed for use on an airplane translating door hinge arm (13) comprising a hydraulic device (41) and a flow regulation system (40). The hinge arm (13) includes sprockets (25, 27) placed at the ends (15, 17) of the hinge arm (13). Roller chain pieces (31) rotate partially about the sprockets (25, 27). A pneumatic actuator (33) having a through-rod (37) and housing (35) is located on one side of the hinge arm (13). The actuator housing (35) is supported by a support member (23) integral with the hinge arm (13). The ends of the actuator through-rod (43) are each coupled to first ends of each of the roller chain pieces (31). The hydraulic device (41) comprising a housing (47), a through-rod (43), a piston 45, a first compartment (49), a second compartment (51), and hydraulic fluid, is also supported by the support member (23). The ends of the hydraulic device through-rod (43) are each coupled to second ends of each of the roller chain pieces (31). The hydraulic device (41) is located on the side of the hinge arm (13) opposite the side having the actuator (33). Also provided is a snubber fluid flow regulation system (40) comprising first and second flow regulators (59, 65) and first and second high pressure relief valves (61, 67), one each for use during door opening and door closing. A compensator (71) is also provided in the fluid flow regulation system (40) to hydraulically compensate the snubber (41) during temperature changes and to supply make-up fluid in case there is external leakage.
摘要翻译：公开了一种用于在包括液压装置（41）和流量调节系统（40）的飞机平移门铰链臂（13）上使用的缓冲器。铰链臂（13）包括放置在铰链臂（13）的端部（15,17）处的链轮（25,27）。滚子链条（31）围绕链轮（25,27）部分旋转。具有通杆（37）和壳体（35）的气动致动器（33）位于铰链臂（13）的一侧。致动器壳体（35）由与铰链臂（13）成一体的支撑构件（23）支撑。致动器贯穿杆（43）的端部分别连接到每个滚子链条件（31）的第一端。包括壳体（47），通杆（43），活塞45，第一隔室（49），第二隔室（51）和液压流体的液压装置（41）也由支撑构件（23）。液压装置通杆（43）的端部分别与各滚子链条（31）的第二端相连。液压装置（41）位于与具有致动器（33）的一侧相对的铰链臂（13）侧。还提供了一种缓冲液流量调节系统（40），其包括第一和第二流量调节器（59,65）以及第一和第二高压溢流阀（61,67），每个用于在门打开和关门期间使用。在流体流量调节系统（40）中还设置补偿器（71），以在温度变化期间对缓冲器（41）进行液压补偿，并在外部泄漏的情况下提供补充液体。

7. 发明授权

US4720065A Translatable outward opening plug-type aircraft door and actuating mechanisms therefor 失效
标题翻译：可翻转向外开口插入式飞机门及其驱动机构
公开(公告)号：US4720065A
公开(公告)日：1988-01-19
申请号：US694426
申请日：1985-01-24
申请人： Tomio Hamatani
发明人： Tomio Hamatani
IPC分类号： B64C1/14
CPC分类号： B64C1/143 , B64C1/1407 , Y10S244/905
摘要： An inward/outward movable plug-type aircraft passenger door (50) including: (i) a hinge assembly (56) and programming control mechanism (100, 114, 116 and 105, 114, 119) therefor; (ii) a latch/unlatch mechanism (58, 70, 82, 88, 89, 90, 91, 92, 94 and 95) therefor; (iii) a pressure lock gate (69) and actuating mechanism (58, 75, 76, 78, 79, 80, 81, 82 and 84) therefor; and (iv), a deployable emergency evacuation system (59) and actuating linkage (60, 132, 134, 135, 136, 138, 139, 140, 141, 142 and 144); wherein the aircraft door (50) is of the type adapted to be translated between a first fully closed and latched position and a second fully opened position while being maintained essentially parallel to the plane containing the ingress/egress cutout opening (51) in the fuselage (52) at all intermediate door positions--i.e., the aircraft door (51) is not pivoted or rotated about the hinge axis (104 and/or 109) to, in effect, turn the door (51) inside-out, but, rather, is moved with translatory motion outward of the ingress/egress cutout opening (51) in the fuselage (52) to a fully open position where the door's inner skin (66) is in facing relation to the fuselage (52) outer skin.
摘要翻译：一种向内/向外可移动的插塞式飞机乘客门（50），包括：（i）铰链组件（56）和编程控制机构（100,114,116和105,114,119）; （ii）用于其的闩锁/解锁机构（58,70,82,88,89,90,91,92,94和95）; （iii）压力锁定门（69）和致动机构（58,75,76,78,77,80,81,82和84）; 和（iv），可部署的紧急撤离系统（59）和致动联动装置（60,132,134,135,136,138,139,140,141,142和144）; 其中所述飞行器门（50）具有适于在第一完全闭合位置和第二完全打开位置之间平移的形式，同时基本平行于包含机身中的入口/出口切口（51）的平面（52）在所有中间门位置 - 即，飞机门（51）不围绕铰链轴线（104和/或109）枢转或旋转，实际上使门（51）向内转出，而是以机身（52）中的入口/出口切口（51）向外的平移运动移动到门内表皮（66）面对机身（52）外皮的完全打开位置。

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