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1. 发明申请

WO2007064481A1 ECCENTRIC FASTENING DEVICE 审中-公开
标题翻译： ECCENTRIC紧固装置
公开(公告)号：WO2007064481A1
公开(公告)日：2007-06-07
申请号：PCT/US2006/044417
申请日：2006-11-15
申请人： THE BOEING COMPANY , HARPER ENGINEERING COMPANY , LACONTE, Richard, J. , NEBEKER, Michael, O.
发明人： LACONTE, Richard, J. , NEBEKER, Michael, O.
IPC分类号： F16B21/02 , F16B5/06 , F16B5/02 , B64D11/06
CPC分类号： F16B21/02 , B64D11/0696 , F16B2/18 , F16B5/02 , F16B5/0642 , Y10T29/49947 , Y10T29/49948 , Y10T29/49963
摘要： The eccentric fastening device (20) includes a first threaded fastener (30), a base (22) and a rotary lug (24) providing a non-fastened pre-assembled position. The base includes a top (41), a bottom (38), a stem (36) and a hole (37), where the stem axially extends from the bottom of the base, and the hole axially extends from the top through the stem of the base. The rotary lug is releasably retained in the hole of the base by the first threaded fastener. The rotary lug includes a cylindrical portion (48) having a thread (59) and a head (50), wherein the head is offset from the cylindrical portion. The cylindrical portion is substantially axially concentric with the hole of the base, allowing the head to be eccentrically rotated on or off of the stem, whereby a selective structure may be variably clamped and releasably retained between said head and said base. An aircraft having an eccentric fastening device is also provided. A method of installing the same is also provided.
摘要翻译：偏心紧固装置（20）包括提供未紧固的预组装位置的第一螺纹紧固件（30），基座（22）和旋转凸耳（24）。底座包括顶部（41），底部（38），杆（36）和孔（37），其中杆从基部的底部轴向延伸，并且孔从顶部轴向延伸穿过杆的基地。旋转凸耳通过第一螺纹紧固件可释放地保持在基座的孔中。旋转凸耳包括具有螺纹（59）和头部（50）的圆柱形部分（48），其中头部与圆柱形部分偏移。圆柱形部分与基座的孔基本上轴向同心，允许头部与阀杆偏心旋转，从而选择性结构可以可变地夹紧并可释放地保持在所述头部和所述底座之间。还提供了具有偏心紧固装置的飞机。还提供了一种安装方法。

2. 发明申请

WO2019195058A1 AIRCRAFT LATCH APPARATUS AND METHODS TO USE THE SAME 审中-公开
公开(公告)号：WO2019195058A1
公开(公告)日：2019-10-10
申请号：PCT/US2019/024393
申请日：2019-03-27
申请人： HARPER ENGINEERING COMPANY
发明人： LACONTE, Richard, J.
IPC分类号： E05C3/24 , B64D11/00 , E05B47/00
摘要： A latch apparatus coupled to an aircraft component can comprise a latch assembly moveable between unlatched and latched configurations, an actuation system coupled to the latch assembly and operable to move the latch assembly from the latched configuration to the unlatched configuration, the actuation system including an electromagnet assembly magnetically coupled to the latch assembly, and a control system operably coupled to the electromagnet assembly. The control system can be configured to magnetically uncouple the electromagnet assembly from the latch assembly to cause the latch assembly to move from the latched configuration to the unlatched configuration. Related methods are also provided.

3. 发明申请

WO2019018300A1 INTEGRATED STOWAGE BIN ASSEMBLY 审中-公开
公开(公告)号：WO2019018300A1
公开(公告)日：2019-01-24
申请号：PCT/US2018/042321
申请日：2018-07-16
申请人： HARPER ENGINEERING COMPANY
发明人： CHADWELL, David , LACONTE, Richard, J.
IPC分类号： B64D11/00
摘要： A stowage bin assembly includes a bin bucket assembly (12) having a bin bucket which includes at least one sidewall (15), the at least one sidewall (15) including a notch (20) and the at least one sidewall having an interior surface. The stowage bin assembly also includes at least one hinge assembly (14A; 14B). The at least one hinge assembly (14A; 14B) includes a housing (22) which is received in the notch (20), the housing having an interior surface, wherein the interior surface of the housing is substantially flush with the interior surface of the at least one sidewall when the housing of the at least one hinge assembly is received in the notch (20). The stowage bin assembly also includes a stowage bin door (13) pivotably coupled to the bin bucket assembly via the at least one hinge assembly (14A; 14B), the stowage bin door (13) moveable between an open position and a closed position. Related components, assemblies, and devices are also provided.

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