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1. 发明申请

WO2006121505A8 MULTI-AXIAL LAMINATE COMPOSITE STRUCTURES AND METHODS OF FORMING THE SAME 审中-公开
标题翻译：多轴层压复合结构及其形成方法
公开(公告)号：WO2006121505A8
公开(公告)日：2007-01-25
申请号：PCT/US2006009730
申请日：2006-03-16
申请人： BOEING CO , KISMARTON MAX U
发明人： KISMARTON MAX U
IPC分类号： B29C70/08 , B29C70/20 , B29C70/22 , B29C70/24 , B64C1/00
CPC分类号： B29C70/083 , B29C70/202 , B29C70/207 , B29C70/226 , B29C70/228 , B29C70/24 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , Y02T50/433 , Y10T428/24994
摘要： Composite laminate structures and methods of forming the same are disclosed. In one embodiment, the structure includes a first bidirectional layer (112) having a first portion (117) that includes parallel reinforcement fibers oriented at a first angle relative to a first direction and a second portion (114) that includes parallel reinforcement fibers oriented at a second angle relative to the first direction. The structure further includes a second bidirectional layer (118) having a first portion (119) that includes parallel reinforcement fibers oriented at a third angle relative to the first direction and a second portion (120) that includes parallel reinforcement fibers oriented at a fourth angle relative to the first direction. At least one unidirectional (116) layer having a plurality of parallel reinforcement fibers is coupled to at least one of the first bidirectional layer and the second bidirectional layer.
摘要翻译：公开了复合层压结构及其形成方法。在一个实施例中，该结构包括具有第一部分（117）的第一双向层（112），该第一部分包括相对于第一方向以第一角度定向的平行增强纤维和包括平行增强纤维的第二部分，相对于第一方向的第二角度。该结构还包括具有第一部分（119）的第二双向层（118），该第一部分包括相对于第一方向以第三角度定向的平行增强纤维和包括以第四角度定向的平行增强纤维的第二部分（120）相对于第一个方向。具有多个平行增强纤维的至少一个单向（116）层被耦合到第一双向层和第二双向层中的至少一个。

2. 发明申请

WO2006118691A3 COMPOSITE SKIN AND STRINGER STRUCTURES AND METHODS FOR FORMING THE SAME 审中-公开
标题翻译：复合皮肤和晶体结构及其形成方法
公开(公告)号：WO2006118691A3
公开(公告)日：2007-03-08
申请号：PCT/US2006010703
申请日：2006-03-22
申请人： BOEING CO , KISMARTON MAX U
发明人： KISMARTON MAX U
IPC分类号： B64C1/12 , B29C70/30 , B29K101/00 , B29K105/10 , B29K307/04 , B29L9/00 , B29L31/00
CPC分类号： B64C1/064 , B29C65/562 , B29C66/112 , B29C66/1122 , B29C66/131 , B29C66/474 , B29C66/524 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C70/228 , B29C70/30 , B29K2101/00 , B29K2307/00 , B29L2031/3076 , B64C1/12 , B64C3/182 , B64C3/26 , Y02T50/433 , Y10T428/24124 , B29K2307/04
摘要： Composite stringer and skin structures (10) and methods for forming the same are disclosed. In one embodiment, a composite stringer and skin structure includes a polymer-based elongated stringer portion having reinforcing fibers positioned in a plurality of adjacent plies, a first portion of the reinforcing fibers being oriented at a relatively shallow angle relative to a selected reference direction, and a second portion of the reinforcing fibers being oriented at a relatively broad angle relative to the selected reference direction. A polymer-based and fiber reinforced skin member adjoins the stringer portion, and an adhesive material is interposed between the stringer portion and the skin member.
摘要翻译：公开了复合纵梁和表皮结构（10）及其形成方法。在一个实施例中，复合纵梁和表层结构包括基于聚合物的细长纵梁部分，其具有定位在多个相邻层中的增强纤维，所述增强纤维的第一部分相对于所选择的参考方向以相对较小的角度定向，并且所述增强纤维的第二部分相对于所选择的参考方向以相对较宽的角度定向。聚合物基和纤维增强表层构件邻接纵梁部分，并且粘合材料插入在纵梁部分和皮肤构件之间。

3. 发明申请

WO2008054351A3 ROTOR APPARATUS AND METHODS FOR VERTICAL LIFT AIRCRAFT 审中-公开
标题翻译：用于垂直升降飞机的转子装置和方法
公开(公告)号：WO2008054351A3
公开(公告)日：2008-11-27
申请号：PCT/US2006029133
申请日：2006-07-26
申请人： BOEING CO , KISMARTON MAX U
发明人： KISMARTON MAX U
IPC分类号： B64C27/32
CPC分类号： B64C27/32 , B64C27/48 , B64C27/51
摘要： Rotor apparatus and methods for vertical lift aircraft are disclosed. In one embodiment, a bearing assembly (130) adapted for rotatably coupling a rotor blade to a support member includes an inner housing (138) annularly disposed about a portion of the support member, an outer housing (136) annularly disposed about at least part of the inner housing and is rotatably coupled to the inner housing by an annular bearing device, and a flexible member (140) adapted to be coupled to the support member and including an engagement portion adapted to engage the outer housing and to at least partially relax a side force exerted on the annular bearing device by a bending of at least one of the rotor blade and the support member.
摘要翻译：公开了用于垂直升降飞机的转子装置和方法。在一个实施例中，适于将转子叶片可旋转地联接到支撑构件的轴承组件（130）包括围绕所述支撑构件的一部分环形地设置的内壳体（138），外壳体（136），其围绕至少部分并且通过环形轴承装置可旋转地联接到所述内壳体，以及柔性构件（140），其适于联接到所述支撑构件并且包括接合部分，所述接合部分适于接合所述外壳体并且至少部分地松弛通过转子叶片和支撑构件中的至少一个的弯曲施加在环形轴承装置上的侧向力。

4. 发明申请

WO2008057064A3 CONDUCTING-FIBER DEICING SYSTEMS AND METHODS 审中-公开
标题翻译：导电纤维检测系统和方法
公开(公告)号：WO2008057064A3
公开(公告)日：2008-10-02
申请号：PCT/US2006028943
申请日：2006-07-26
申请人： BOEING CO , KISMARTON MAX U
发明人： KISMARTON MAX U
IPC分类号： B64D15/12 , B64D15/14
CPC分类号： H05B3/28 , B64D15/14
摘要： Conducting- fiber deicing systems and methods are disclosed. In one embodiment, an assembly includes a surface (128) subject to an accumulation of ice, the surface (128) at least partially including a heating portion (152) having a layer (154) of multi-directional electrically-conductive fibers formed between first and second non-electrically conductive layers (156, 158). The layer of electrically-conductive fibers is coupled to a power supply member (160) and is adapted to conduct an electrical current such that the layer (154) of electrically-conductive fibers, and at least one of the first and second non-electrically conductive layers (156, 158) of the heating portion (152), are raised to an elevated temperature to at least partially inhibit the, accumulation of ice on the surface.
摘要翻译：公开了导电纤维除冰系统和方法。在一个实施例中，组件包括经受冰积聚的表面（128），所述表面（128）至少部分地包括加热部分（152），所述加热部分具有多向导电纤维层（154）第一和第二非导电层（156,158）。导电纤维层被耦合到电源构件（160），并且适于传导电流，使得导电纤维的层（154）以及第一和第二非电加热部分（152）的导电层（156,158）被升高到升高的温度以至少部分地抑制冰在表面上的积聚。

5. 发明申请

WO2006104954A3 HYBRID FIBERGLASS COMPOSITE STRUCTURES AND METHODS OF FORMING THE SAME 审中-公开
标题翻译：混合玻璃纤维复合材料结构及其成形方法
公开(公告)号：WO2006104954A3
公开(公告)日：2006-11-30
申请号：PCT/US2006010974
申请日：2006-03-24
申请人： BOEING CO , KISMARTON MAX U
发明人： KISMARTON MAX U
IPC分类号： B32B5/00
CPC分类号： B32B3/12 , B29D99/0021 , B29K2709/08 , B32B5/024 , B32B5/26 , B32B5/28 , B32B17/04 , B32B27/08 , B32B27/12 , B32B27/32 , B32B27/36 , B32B27/38 , B32B37/146 , B32B2250/05 , B32B2250/40 , B32B2262/0253 , B32B2262/101 , B32B2305/076 , B32B2307/558 , B32B2307/704 , B32B2307/712 , B32B2307/718 , B32B2315/085 , B32B2363/00 , B32B2605/08 , B32B2605/12 , B32B2605/18 , Y10T428/249924
摘要： Hybrid fiberglass composite structures and methods for forming the same are disclosed. In one embodiment, a hybrid fiberglass composite structure includes a first laminate substrate and a second opposing laminate substrate. At least one of the first laminate substrate and the second laminate substrate includes at least one polymer fiber layer and at least one glass fiber layer. A cellular core structure is interposed between the first laminate substrate and the second laminate substrate and fixedly coupled to the first laminate substrate and the second laminate substrate.
摘要翻译：公开了混合玻璃纤维复合结构及其形成方法。在一个实施例中，混合玻璃纤维复合结构包括第一层压基底和第二相对层压基底。第一层压基板和第二层压基板中的至少一个包括至少一个聚合物纤维层和至少一个玻璃纤维层。多孔芯结构插入在第一层压基底和第二层压基底之间并固定地连接到第一层压基底和第二层压基底。

6. 发明申请

WO2008054499A3 COMPOSITE WING-BODY JOINT 审中-公开
标题翻译：复合机身接头
公开(公告)号：WO2008054499A3
公开(公告)日：2008-11-27
申请号：PCT/US2007008695
申请日：2007-04-06
申请人： BOEING CO , KISMARTON MAX U , WESTRE WILLARD N
发明人： KISMARTON MAX U , WESTRE WILLARD N
IPC分类号： B64C1/26 , B64C3/18 , B64C3/26
CPC分类号： B64C1/26 , B64C3/182 , B64C3/26 , Y10T428/19
摘要： Embodiments of integral composite panels and joints for composite structures are described In one implementation, an integrated panel (104) spanning substantially the entire wingspan of an aircraft, includes at least a center portion (110) and a pair of outwardly projecting wing portions (106, 108). The portions may include a skin formed from successive layers or plies of composite material which overlap and offset at the joint between respective sections creating a pad-up area to carry loads between the portions. In a particular implementation, the skin is laid over one or more structural stringers (112) which are transitioned into the joints (116, 118) between sections such as by tapering of the thickness and/or stiffness of the stringer.
摘要翻译：在一个实施方案中，跨越飞行器的基本上整个翼展的集成面板（104）包括至少一个中心部分（110）和一对向外突出的翼部分（106），108）。这些部分可以包括由复合材料的连续层或层组成的表皮，其在相应部分之间的接合处重叠和偏移，形成用于在部分之间承载载荷的垫区。在一个具体的实施方式中，将皮肤放置在一个或多个结构纵梁（112）上，这些结构纵梁（112）在部分之间转变成接头（116,118），例如通过使纵梁的厚度和/或刚度变细。

7. 发明申请

WO2007053362A3 SINGLE PIECE FUSELAGE BARREL 审中-公开
标题翻译：单条FUSELAGE BARREL
公开(公告)号：WO2007053362A3
公开(公告)日：2008-07-24
申请号：PCT/US2006041372
申请日：2006-10-24
申请人： BOEING CO , KISMARTON MAX U , ANDREWS FRANCIS E , KOCH WILLIAM J
发明人： KISMARTON MAX U , ANDREWS FRANCIS E , KOCH WILLIAM J
IPC分类号： B64C1/00 , B29C70/44
CPC分类号： B64C1/06 , B29C70/202 , B29C70/30 , B29C70/44 , B29K2105/108 , B29K2105/246 , B29K2105/253 , B29K2307/04 , B29K2309/08 , B29K2995/0089 , B29L2031/3082 , B64C1/068 , B64C1/12 , B64C2001/0072 , B64F5/10 , Y02T50/433
摘要： In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.
摘要翻译：根据本发明，提供了一种飞机无脊椎机身结构，其包括具有多个树脂浸渍的皮肤纤维的冲击兼容外皮，其形成外皮表面，内无脊髓皮肤表面和皮肤厚度。包括多个加强件，每个加强件均包括多个树脂浸渍的加强纤维，其集成到内部无脊椎皮肤结构中。多个树脂浸渍的皮肤纤维不与多个树脂浸渍的加强纤维对准。

8. 发明申请

WO2007136578A3 LIGHTWEIGHT AIRCRAFT PASSENGER SEAT WITH COMPOSITE CONSTRUCTION 审中-公开
标题翻译：轻型飞机乘客座椅与复合结构
公开(公告)号：WO2007136578A3
公开(公告)日：2008-03-13
申请号：PCT/US2007011396
申请日：2007-05-10
申请人： BOEING CO , BOREN KELLY L , KISMARTON MAX U , RETZ KEVIN M
发明人： BOREN KELLY L , KISMARTON MAX U , RETZ KEVIN M
IPC分类号： B64D11/06 , B60N2/68 , B60N2/90
CPC分类号： B64D11/06 , B60N2/4415 , B60N2/4495 , B60N2/682 , B60N2/686 , B64D11/0649 , Y02T50/46
摘要： An aircraft seat assembly (100) configured in accordance with an example embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat assembly includes a lightweight composite support structure (102), a lightweight composite seat base (104), and a seat back assembly (108) that employs a lightweight inner frame (602). The seat cushion (500) and the seat back cushion (604) may utilize a sealed pneumatic element that self-inflates to provide increased air cushioning during flight. The seat assembly can leverage inexpensive manufacturing techniques such that the seat assembly can be economically produced for use as an economy class seat.
摘要翻译：根据本发明的示例性实施例构造的飞行器座椅组件（100）利用复合材料相对于传统座椅设计实现显着的重量节省。座椅组件包括轻质复合支撑结构（102），轻型复合座椅基座（104）和采用轻质内框架（602）的座椅靠背组件（108）。座垫（500）和座椅靠背垫（604）可以利用密封的气动元件，其自动充气以在飞行期间提供增加的空气缓冲。座椅组件可以利用廉价的制造技术，使得座椅组件可经济地生产用作经济舱座椅。

9. 发明申请

WO2014074201A2 PASSIVE LOAD ALLEVIATION FOR AERODYNAMIC LIFT STRUCTURES 审中-公开
标题翻译：用于空气动力结构的被动负载评估
公开(公告)号：WO2014074201A2
公开(公告)日：2014-05-15
申请号：PCT/US2013055871
申请日：2013-08-20
申请人： BOEING CO
发明人： KISMARTON MAX U
IPC分类号： B64C3/44
CPC分类号： B64C3/26 , B64C3/18 , B64C3/20 , B64C2003/445 , Y02T50/145
摘要： An aerodynamic lift structure comprises unbalanced composite skin that couples twist and bending.
摘要翻译：气动提升结构包括不平衡的复合皮肤，其耦合扭曲和弯曲。

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