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1.发明申请WING UNIT, IN PARTICULAR SPAR BOX, FOR FORMING AERODYNAMICALLY ACTIVE SURFACES OF AN AIRCRAFT, IN PARTICULAR AIRFOILS, HORIZONTAL TAIL UNITS OR RUDDER UNITS OF A PLANE 有权用于形成航空器，特别是空中飞行器，水平尾翼单元或平面设备的空中活动表面的特殊弹簧箱公开(公告)号：US20100006708A1
公开(公告)日：2010-01-14
申请号：US12560679
申请日：2009-09-16
申请人： Barnaby Law
发明人： Barnaby Law
摘要： The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane.Aerodynamic improvements can be obtained due to a surface geometry of the aerodynamically active surfaces, which surface geometry is adapted to the respective operating state of the plane by using the actuating members and/or weight savings due to minimizing of structural mechanical loads of the wing unit.
摘要翻译： 本发明涉及一种机翼单元，特别是用于形成飞行器，特别是平面的翼型，水平尾翼单元或舵单元的空气动力学活动表面的翼梁箱。 由于空气动力学活动表面的表面几何形状，可以获得空气动力学改进，该表面几何形状通过使用致动构件适应于平面的相应操作状态和/或由于机翼单元的结构机械负载的最小化而导致的重量节省 。
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2.发明授权Wing unit, in particular spar box, for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units or rudder units of a plane 失效翼单元，特别是翼梁箱，用于形成飞机的空气动力学活动表面，特别是飞机的翼型，水平尾翼单元或舵单元公开(公告)号：US07607617B2
公开(公告)日：2009-10-27
申请号：US11316126
申请日：2005-12-22
申请人： Barnaby Law
发明人： Barnaby Law
IPC分类号： B64C3/44
摘要： The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane.Aerodynamic improvements can be obtained due to a surface geometry of the aerodynamically active surfaces, which surface geometry is adapted to the respective operating state of the plane by using the actuating members and/or weight savings due to minimizing of structural mechanical loads of the wing unit.
摘要翻译： 本发明涉及一种机翼单元，特别是用于形成飞行器，特别是平面的翼型，水平尾翼单元或舵单元的空气动力学活动表面的翼梁箱。 由于空气动力学活动表面的表面几何形状，可以获得空气动力学改进，该表面几何形状通过使用致动构件适应于平面的相应操作状态和/或由于机翼单元的结构机械负载的最小化而导致的重量节省 。
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3.发明授权Wing unit, in particular spar box, for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units or rudder units of a plane 有权翼单元，特别是翼梁箱，用于形成飞机的空气动力学活动表面，特别是飞机的翼型，水平尾翼单元或舵单元公开(公告)号：US07909292B2
公开(公告)日：2011-03-22
申请号：US12560679
申请日：2009-09-16
申请人： Barnaby Law
发明人： Barnaby Law
IPC分类号： B64C3/44
摘要： The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane.Aerodynamic improvements can be obtained due to a surface geometry of the aerodynamically active surfaces, which surface geometry is adapted to the respective operating state of the plane by using the actuating members and/or weight savings due to minimizing of structural mechanical loads of the wing unit.
摘要翻译： 本发明涉及一种机翼单元，特别是用于形成飞行器，特别是平面的翼型，水平尾翼单元或舵单元的空气动力学活动表面的翼梁箱。 由于空气动力学活动表面的表面几何形状，可以获得空气动力学改进，该表面几何形状通过使用致动构件适应于平面的相应操作状态和/或由于机翼单元的结构机械负载的最小化而导致的重量节省 。
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公开(公告)号：US08580170B2
公开(公告)日：2013-11-12
申请号：US11922940
申请日：2006-06-30
IPC分类号： B29C47/76
CPC分类号： B64C1/12 , B29C70/44 , B29C70/84 , B29L2031/3082 , B29L2031/3085 , Y02T50/43
摘要： Disclosed is a process for producing a substantially shell-shaped component, from substantially carbon-fiber-reinforced synthetic material having at least one local reinforcing zone and at least one stiffening element, in particular a fuselage shell, a wing shell, a vertical stabilizer shell or horizontal stabilizer shell of an aircraft or the like. The process according to the invention comprises the following steps: arranging at least one doubler which has already been cured, on an at most partially cured shell skin to form the local reinforcing zone, applying at least one stiffening element which has already been cured, and placing at least one at most partially cured connecting angle bracket against the at least one stiffening element at least in the region of the at least one doubler, and curing the shell skin and the connecting angle bracket.
摘要翻译： 公开了一种从基本上由碳纤维增强的合成材料制成的基本上壳形的部件的方法，所述合成材料具有至少一个局部增强区域和至少一个加强元件，特别是机身壳体，机翼壳体，垂直稳定器壳体 或水平稳定器壳体等。 根据本发明的方法包括以下步骤：将已经固化的至少一个倍增器布置在至多部分固化的壳皮肤上以形成局部加强区域，施加至少一个已经固化的加强元件，以及 至少在所述至少一个倍增器的区域中至少布置至少部分固化的连接角支架抵靠所述至少一个加强元件，并且固化所述外壳皮肤和所述连接角支架。
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5.发明授权Adhesive joint for joining components of transport craft, in particular of aircraft, and method for determining minimum mechanical load capacity and/or mechanical strength of an adhesive joint 失效用于连接运输工具，特别是飞机的部件的粘合接头以及用于确定粘合接头的最小机械负载能力和/或机械强度的方法公开(公告)号：US07669467B2
公开(公告)日：2010-03-02
申请号：US11316306
申请日：2005-12-22
申请人： Ulf Breuer , Barnaby Law
发明人： Ulf Breuer , Barnaby Law
IPC分类号： G01B21/08
CPC分类号： F16B11/006 , G01L1/16 , Y10T403/20
摘要： This invention relates to an adhesive joint for joining components of transport craft, in particular of aircraft, wherein the adhesive joint is formed by an adhesive means. According to the invention, the adhesive means has several functional elements with actuatory and/or sensory properties, in particular for enabling a minimum mechanical load capacity of the adhesive joint and/or detecting a mechanical loading state in the adhesive joint. Due to the presence of functional elements integrated in the adhesive joint direct and simple testing of the mechanical load capacity of the adhesive joint is possible without costly external test structures, e.g. in the form of measuring and testing systems for conducting tensile load tests or the like. Moreover, mechanical stress states in the adhesive joint can be detected. Moreover, the invention relates to a method for determining a minimum mechanical load capacity and/or mechanical strength of an adhesive joint.
摘要翻译： 本发明涉及一种用于连接运输工具，特别是飞机的部件的粘合剂接头，其中粘合接头由粘合装置形成。 根据本发明，粘合剂装置具有若干具有致动和/或感官特性的功能元件，特别是使粘合剂接头的最小机械载荷能力和/或检测粘合剂接头中的机械加载状态。 由于集成在粘合剂接头中的功能元件的存在，可以在没有昂贵的外部测试结构的情况下直接和简单地测试粘合剂接头的机械负载能力。 以用于进行拉伸载荷试验等的测量和测试系统的形式。 此外，可以检测粘合剂接头中的机械应力状态。 此外，本发明涉及一种用于确定粘合剂接头的最小机械负载能力和/或机械强度的方法。
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公开(公告)号：US20090115088A1
公开(公告)日：2009-05-07
申请号：US11922940
申请日：2006-06-30
CPC分类号： B64C1/12 , B29C70/44 , B29C70/84 , B29L2031/3082 , B29L2031/3085 , Y02T50/43
摘要： Disclosed is a process for producing a substantially shell-shaped component, from substantially carbon-fiber-reinforced synthetic material having at least one local reinforcing zone and at least one stiffening element, in particular a fuselage shell, a wing shell, a vertical stabilizer shell or horizontal stabilizer shell of an aircraft or the like. The process according to the invention comprises the following steps: arranging at least one doubler which has already been cured, on an at most partially cured shell skin to form the local reinforcing zone, applying at least one stiffening element which has already been cured, and placing at least one at most partially cured connecting angle bracket against the at least one stiffening element at least in the region of the at least one doubler, and curing the shell skin and the connecting angle bracket.
摘要翻译： 公开了一种从基本上由碳纤维增强的合成材料制成的基本上壳形的部件的方法，所述合成材料具有至少一个局部增强区域和至少一个加强元件，特别是机身壳体，机翼壳体，垂直稳定器壳体 或水平稳定器壳体等。 根据本发明的方法包括以下步骤：将已经固化的至少一个倍增器布置在至多部分固化的壳皮肤上以形成局部加强区域，施加至少一个已经固化的加强元件，以及 至少在所述至少一个倍增器的区域中至少布置至少部分固化的连接角支架抵靠所述至少一个加强元件，并且固化所述外壳皮肤和所述连接角支架。
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公开(公告)号：US20060226291A1
公开(公告)日：2006-10-12
申请号：US11316126
申请日：2005-12-22
申请人： Barnaby Law
发明人： Barnaby Law
IPC分类号： B64C3/00
摘要： The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane. Aerodynamic improvements can be obtained due to a surface geometry of the aerodynamically active surfaces, which surface geometry is adapted to the respective operating state of the plane by using the actuating members and/or weight savings due to minimizing of structural mechanical loads of the wing unit.
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公开(公告)号：US08911580B2
公开(公告)日：2014-12-16
申请号：US12528887
申请日：2008-03-26
申请人： Barnaby Law , Hauke Lengsfeld
发明人： Barnaby Law , Hauke Lengsfeld
IPC分类号： B29C70/02 , B29C70/30 , B29C70/54 , B29C70/34 , B29K709/08 , B29K707/04 , B29K105/24 , B29K63/00
CPC分类号： B29C70/342 , B29C70/543 , B29K2063/00 , B29K2105/24 , B29K2105/243 , B29K2105/246 , B29K2707/04 , B29K2709/08 , Y02T50/43 , Y10T156/1002
摘要： This invention provides a method for producing a structural component, particularly in the aerospace sector. An unhardened prepreg fabric is formed from a composite fiber material, hardenable at a first hardening temperature, into a predetermined shape. The unhardened prepreg fabric is then connected to at least one hardening part of a composite fiber material partially hardened at a second hardening temperature for holding the unhardened prepreg fabric in the predetermined shape, wherein the second hardening temperature is lower than the first hardening temperature. In a further method step the unhardened prepreg fabric connected to the at least one holding part is hardened at the first hardening temperature to form the structural component. The idea on which this invention is based consists in replacing expensive tools of special steel previously used for holding dimensionally unstable prepreg fabrics with at least one holding part of composite fiber materials, wherein the at least one holding part has a lower hardening temperature than the prepreg fabric, and can therefore be produced with a lower cost tool.
摘要翻译： 本发明提供了一种用于制造结构部件的方法，特别是在航天领域。 未硬化的预浸物织物由在第一硬化温度下可硬化的复合纤维材料形成为预定形状。 然后将未硬化的预浸渍织物连接到在第二硬化温度下部分硬化的复合纤维材料的至少一个硬化部分，以将未硬化的预浸料坯料保持在预定形状，其中第二固化温度低于第一硬化温度。 在另一方法步骤中，连接到至少一个保持部分的未硬化的预浸渍织物在第一硬化温度下硬化以形成结构组分。 本发明所依据的思想在于，用具有至少一个复合纤维材料的保持部分的先前用于保持尺寸不稳定的预浸料坯料的特殊钢的更换昂贵的工具，其中至少一个保持部件具有比预浸料坯更低的硬化温度 织物，因此可以用较低成本的工具生产。
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公开(公告)号：US20100139847A1
公开(公告)日：2010-06-10
申请号：US12528887
申请日：2008-03-26
申请人： Barnaby Law , Hauke Lengsfeld
发明人： Barnaby Law , Hauke Lengsfeld
IPC分类号： B32B37/16
CPC分类号： B29C70/342 , B29C70/543 , B29K2063/00 , B29K2105/24 , B29K2105/243 , B29K2105/246 , B29K2707/04 , B29K2709/08 , Y02T50/43 , Y10T156/1002
摘要： This invention provides a method for producing a structural component, particularly in the aerospace sector. An unhardened prepreg fabric is formed from a composite fibre material, hardenable at a first hardening temperature, into a predetermined shape. The unhardened prepreg fabric is then connected to at least one hardening part of a composite fibre material partially hardened at a second hardening temperature for holding the unhardened prepreg fabric in the predetermined shape, wherein the second hardening temperature is lower than the first hardening temperature. In a further method step the unhardened prepreg fabric connected to the at least one holding part is hardened at the first hardening temperature to form the structural component. The idea on which this invention is based consists in replacing expensive tools of special steel previously used for holding dimensionally unstable prepreg fabrics with at least one holding part of composite fibre materials, wherein the at least one holding part has a lower hardening temperature than the prepreg fabric, and can therefore be produced with a lower cost tool.
摘要翻译： 本发明提供了一种用于制造结构部件的方法，特别是在航天领域。 未硬化的预浸物织物由在第一硬化温度下可硬化的复合纤维材料形成为预定形状。 然后将未硬化的预浸渍织物连接到在第二硬化温度下部分硬化的复合纤维材料的至少一个硬化部分，以将未硬化的预浸料坯料保持在预定形状，其中第二固化温度低于第一硬化温度。 在另一方法步骤中，连接到至少一个保持部分的未硬化的预浸渍织物在第一硬化温度下硬化以形成结构组分。 本发明所依据的思想在于，用具有至少一个复合纤维材料的保持部分的先前用于保持尺寸不稳定的预浸料坯料的特殊钢的更换昂贵的工具，其中至少一个保持部件具有比预浸料坯更低的硬化温度 织物，因此可以用较低成本的工具生产。
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10.发明申请Adhesive joint for joining components of transport craft, in particular of aircraft, and method for determining minimum mechanical load capacity and/or mechanical strength of an adhesive joint 失效用于连接运输工具，特别是飞机的部件的粘合接头以及用于确定粘合接头的最小机械负载能力和/或机械强度的方法公开(公告)号：US20060159513A1
公开(公告)日：2006-07-20
申请号：US11316306
申请日：2005-12-22
申请人： Ulf Breuer , Barnaby Law
发明人： Ulf Breuer , Barnaby Law
IPC分类号： G01B7/16
CPC分类号： F16B11/006 , G01L1/16 , Y10T403/20
摘要： This invention relates to an adhesive joint for joining components of transport craft, in particular of aircraft, wherein the adhesive joint is formed by an adhesive means. According to the invention, the adhesive means has several functional elements with actuatory and/or sensory properties, in particular for enabling a minimum mechanical load capacity of the adhesive joint and/or detecting a mechanical loading state in the adhesive joint. Due to the presence of functional elements integrated in the adhesive joint direct and simple testing of the mechanical load capacity of the adhesive joint is possible without costly external test structures, e.g. in the form of measuring and testing systems for conducting tensile load tests or the like. Moreover, mechanical stress states in the adhesive joint can be detected. Moreover, the invention relates to a method for determining a minimum mechanical load capacity and/or mechanical strength of an adhesive joint.
摘要翻译： 本发明涉及一种用于连接运输工具，特别是飞机的部件的粘合剂接头，其中粘合接头由粘合装置形成。 根据本发明，粘合剂装置具有若干具有致动和/或感官特性的功能元件，特别是使粘合剂接头的最小机械载荷能力和/或检测粘合剂接头中的机械加载状态。 由于集成在粘合剂接头中的功能元件的存在，可以在没有昂贵的外部测试结构的情况下直接和简单地测试粘合剂接头的机械负载能力。 以用于进行拉伸载荷试验等的测量和测试系统的形式。 此外，可以检测粘合剂接头中的机械应力状态。 此外，本发明涉及一种用于确定粘合剂接头的最小机械负载能力和/或机械强度的方法。
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