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61. 发明授权

US06293496B1 Strain compatible attachment for metallic thermal protection system for a space vehicle 有权
标题翻译：用于空间车辆的金属热保护系统的应变兼容附件
公开(公告)号：US06293496B1
公开(公告)日：2001-09-25
申请号：US09433534
申请日：1999-11-03
申请人： Jeffrey W. Moe
发明人： Jeffrey W. Moe
IPC分类号： B64C100
CPC分类号： F16B37/043 , B64G1/503 , B64G1/58 , B64G1/64 , F16B5/0241
摘要： A strain compatible attachment arrangement for releasably securing a plurality of metallic thermal protection system (TPS) panels to a space vehicle substructure to provide an outer mold line of the aeroshell of the vehicle. The TPS panels are spaced from the substructure to support aerodynamic loading on the TPS outer panel surface while isolating the outer panel surface from strains in the substructure and to isolate the vehicle substructure from direct thermal energy conductance though the outer TPS panel surface of the space vehicle. The attachment arrangement provides for a stand-off leg member to be secured at an inner end to the substructure and at its outer end to be releasably secured to a corner of a TPS panel, such panels being arranged in an edge abutting relationship. The outer end of each leg member includes a nutplate that is attached to such leg member by a clip and which has a locking portion that interlocks with a complementarily shaped locking insert positioned in a corner of a TPS panel to preclude rotation between the nutplate and the TPS panel when a bolt is inserted through the insert into locking engagement with the nutplate. Since each TPS panel is secured to each stand-off leg member from a position external to each panel, an individual TPS panel may be removed easily, as desired, for repair or replacement.
摘要翻译：一种应变兼容附接装置，用于将多个金属热保护系统（TPS）面板可释放地固定到空间车辆子结构，以提供车辆的气囊的外部模制线。 TPS面板与子结构间隔开以支持TPS外板表面上的空气动力学载荷，同时将外板表面与底层结构中的应力隔离，并且通过空间车辆的外TPS面板表面将车辆底座与直接热能传导隔离。附接装置提供了一个支撑腿构件，其固定在底部结构的内端，并且在其外端被可释放地固定到TPS面板的角部，这些面板以边缘邻接关系布置。每个腿部构件的外端包括螺母板，该螺母板通过夹子附接到该腿部构件上，该螺母板具有锁定部分，该锁定部分与定位在TPS面板的角部中的互补形状的锁定插件互锁，以阻止螺母板和当螺栓穿过插入件插入与螺母板锁定接合时，TPS面板。由于每个TPS面板从每个面板外部的位置固定到每个支撑腿构件，所以可以根据需要容易地移除单独的TPS面板用于修理或更换。

62. 发明授权

US06273367B1 Cover-skin structure 失效
标题翻译：覆盖层结构
公开(公告)号：US06273367B1
公开(公告)日：2001-08-14
申请号：US09465775
申请日：1999-12-17
申请人： Dietmar Mueller
发明人： Dietmar Mueller
IPC分类号： B64C100
CPC分类号： B64C3/26 , B63B3/16 , B63B3/26 , B63B5/00 , B63B2231/02 , B63B2231/52
摘要： A cover-skin web structure for use in flow profiles, in particular aerofoils or their components, comprising a cover skin on the pressure side and a cover skin on the suction side, connected by webs essentially comprising fiber reinforced material. The webs are aligned in the direction of the span and essentially have one or several web cutouts which extend from the cover skin on the suction side to the cover skin on the pressure side. The webs are made of metal in the area of the web cutouts.
摘要翻译：用于流动剖面，特别是翼型或其部件的覆盖层网状结构，其包括压力侧上的覆盖皮肤和在吸力侧上的覆盖皮肤，其基本上包括纤维增强材料。腹板在跨度方向上对准，并且基本上具有一个或多个腹板切口，其从吸力侧的覆盖皮肤延伸到压力侧的覆盖皮肤。网在金属切口的区域中由金属制成。

63. 发明授权

US06237873B1 Composite material wing structure 失效
标题翻译：复合材料翼结构
公开(公告)号：US06237873B1
公开(公告)日：2001-05-29
申请号：US09338551
申请日：1999-06-23
申请人： Kazuaki Amaoka , Hideyuki Sano , Naoya Takizawa
发明人： Kazuaki Amaoka , Hideyuki Sano , Naoya Takizawa
IPC分类号： B64C100
CPC分类号： B64C3/00
摘要： A composite material wing structure is disclosed, comprising a plurality of composite material multi-spar structures, each including a plurality of spar extending in a span direction, placed in the span direction. A wing structure of an airplane is also disclosed, comprising wing structures divided into plural parts in a span direction, a rib connected to an end of the wing structure to assemble adjacent wing structures, and a coupling material for coupling spars of the adjacent wing structures.
摘要翻译：公开了一种复合材料翼结构，其包括多个复合材料多翼梁结构，每个复合材料多翼梁结构包括沿跨度方向延伸的多个翼梁。还公开了一种飞机的翼结构，其包括在跨度方向上分成多个部分的翼结构，连接到翼结构的端部以组装相邻翼结构的肋，以及用于联接相邻机翼结构的翼梁的联接材料。

64. 发明授权

US06213428B1 Aircraft fore structure 有权
标题翻译：飞机前部结构
公开(公告)号：US06213428B1
公开(公告)日：2001-04-10
申请号：US09245842
申请日：1999-02-08
申请人： Pascal Chaumel , Francis Dazet
发明人： Pascal Chaumel , Francis Dazet
IPC分类号： B64C100
CPC分类号： B64C25/14 , B64C1/068 , B64C1/10 , B64C1/36
摘要： An aircraft fore-structure for wide- and very-wide body freight aircraft that is characterized by the presence of a unpressurized landing gear compartment in the lower fore end section. The landing gear compartment is formed by a ceiling at the top, that is preferably domed, and by a partition towards the rear. A door that is provided in the partition provides access through the landing gear compartment to the pressurized compartment located behind said partition. An opening in the fore of the landing gear compartment also provides access to the radar chamber without requiring the radome to be dismantled. The original layout of the landing gear compartment enables fore landing gear to be installed that is larger than that in existing aircraft.
摘要翻译：一种用于广泛和非常宽的机身货运飞机的飞机前部结构，其特征在于在下部前端部分存在未加压的起落架舱。起落架室由顶部的天花板形成，优选地是圆顶形，并且由朝向后方的隔板形成。设置在隔板中的门提供通过起落架舱到位于所述隔板后面的加压室的通路。起落架舱前部的开口还可以进入雷达舱，而不需要拆除天线罩。起落架舱的原始布局使得能够安装比现有飞机更大的起落架。

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