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1. 发明申请

US20100090068A1 AIRCRAFT WITH WINGS WHOSE MAXIMUM LIFT CAN BE ALTERED BY CONTROLLABLE WING COMPONENTS 审中-公开
标题翻译：具有最大提升能力的飞机可由可控制的组件改变
公开(公告)号：US20100090068A1
公开(公告)日：2010-04-15
申请号：US12640559
申请日：2009-12-17
申请人： Alexander van der Velden , Roland Kelm , Josef Mertens
发明人： Alexander van der Velden , Roland Kelm , Josef Mertens
IPC分类号： B64C13/16 , G05D1/00
CPC分类号： G05D1/0066 , B64C13/16 , Y02T50/44
摘要： The present invention relates to an aircraft with wings whose maximum lift can be altered by controllable wing components. By means of a regulating device, depending on flight state parameters and the actually measured load on the wings, wing components are acted upon such that, as a precautionary measure, the maximum possible aerodynamic lift does not exceed a desired upper limit value.
摘要翻译：本发明涉及具有机翼的飞行器，其最大升程可以由可控翼部件改变。通过调节装置，取决于飞行状态参数和实际测量的机翼上的负载，机翼部件的作用是使得作为预防措施，最大可能的空气动力升程不超过期望的上限值。

2. 发明申请

US20090134547A1 Process for the production of an extruded plastic film and use of the plastic film 审中-公开
标题翻译：挤出塑料薄膜的生产工艺和塑料薄膜的使用
公开(公告)号：US20090134547A1
公开(公告)日：2009-05-28
申请号：US12315717
申请日：2008-12-05
申请人： Michael Bauer , Roland Kelm , Josef Mueller
发明人： Michael Bauer , Roland Kelm , Josef Mueller
IPC分类号： B29C47/00
CPC分类号： B29C59/007 , B29C43/222 , B32B3/30 , B32B15/08 , B32B15/20 , B32B27/06 , B32B27/32 , B32B27/36 , C08J5/18
摘要： Process for the production of an extruded mono- or multilayer plastic film, where at least sections of the plastic film are provided with a pattern during or after extrusion, and use of a film produced by this process for packaging purposes.
摘要翻译：用于生产挤出的单层或多层塑料膜的方法，其中塑料膜的至少部分在挤出期间或之后设置有图案，以及使用通过该方法制造的膜用于包装目的。

3. 发明授权

US09545997B2 Wingtip extension for reducing wake vortices of aircraft 有权
标题翻译： Wingtip扩展用于减少飞机的尾流涡流
公开(公告)号：US09545997B2
公开(公告)日：2017-01-17
申请号：US12746806
申请日：2008-12-08
申请人： Roland Kelm
发明人： Roland Kelm
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.
摘要翻译：本发明涉及一种翼尖延伸部，其包括前缘和后缘，所述翼尖延伸部可固定到翼的外端，其中至少在一些部分中的前缘基本上是直的，并且直线部分前缘包括超过翼的前缘扫掠角的前缘扫掠角，并且翼尖延伸的局部深度在用于连接到翼的连接区域和翼尖延伸部的外端之间逐渐减小。通过根据本发明的翼尖延伸，在三角翼中，涡流爆发区域位于翼尖之后，因此翼尖旋涡的岩心爆发并最终变得不稳定，结果是涡流爆裂区域，结果这样可以减少飞机的尾流涡流。本发明还涉及一种翼，包括根据本发明的翼尖延伸部，以及包括这种翼的飞机。

4. 发明授权

US08136757B2 Wing and method for reducing effects of propeller airflow on lift distribution 有权
标题翻译：翼和减少螺旋桨气流对升力分布的影响的方法
公开(公告)号：US08136757B2
公开(公告)日：2012-03-20
申请号：US12316254
申请日：2008-12-10
申请人： Roland Kelm
发明人： Roland Kelm
IPC分类号： B64C23/00
CPC分类号： B64C3/50 , B64C11/00 , Y02T50/14
摘要： A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and/or reduced local twist, and a second region with an increased local wing camber and/or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.
摘要翻译：飞机的机翼包括不平衡的升力梯度，因为由于至少一个螺旋桨滑流流到机翼上，机翼的诱导阻力增加。为了减小增加的诱导阻力，机翼包括具有减小的局部翼弧和/或减小的局部扭曲的第一区域和具有增加的局部翼弯和/或增加的局部扭转的第二区域。第一区域被定义为位于螺旋桨滑流下游的机翼表面，螺旋桨叶片向上的翼面上游。第二区域被定义为位于螺旋桨滑流下游的机翼表面，其中螺旋桨的叶片向下移动的翼表面的上游。

5. 发明申请

US20100294891A1 WINGTIP EXTENSION FOR REDUCTION OF VORTEX DRAG IN AIRCRAFT 有权
标题翻译：用于减少飞机上的VORTEX DRAG的WINGTIP扩展
公开(公告)号：US20100294891A1
公开(公告)日：2010-11-25
申请号：US12746806
申请日：2008-12-08
申请人： Roland Kelm
发明人： Roland Kelm
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.
摘要翻译：本发明涉及一种翼尖延伸部，其包括前缘和后缘，所述翼尖延伸部可固定到翼的外端，其中至少在一些部分中的前缘基本上是直的，并且直线部分前缘包括超过翼的前缘扫掠角的前缘扫掠角，并且翼尖延伸的局部深度在用于连接到翼的连接区域和翼尖延伸部的外端之间逐渐减小。通过根据本发明的翼尖延伸，在三角翼中，涡流爆发区域位于翼尖之后，因此翼尖旋涡的岩心爆发并最终变得不稳定，结果是涡流爆裂区域，结果这样可以减少飞机的尾流涡流。本发明还涉及一种翼，包括根据本发明的翼尖延伸部，以及包括这种翼的飞机。

6. 发明申请

US20140335293A1 Multiple Layer Film Capable of Linear Tear Propagation 审中-公开
标题翻译：线性撕裂传播的多层膜
公开(公告)号：US20140335293A1
公开(公告)日：2014-11-13
申请号：US14240268
申请日：2012-08-15
申请人： Michael Schuhmann , Henrik Hummel , Roland Kelm
发明人： Michael Schuhmann , Henrik Hummel , Roland Kelm
IPC分类号： B32B27/32 , B32B27/08 , B32B7/06 , B32B7/02 , B32B1/02
CPC分类号： B32B27/32 , B32B1/02 , B32B7/02 , B32B7/06 , B32B27/08 , B32B27/325 , B32B2250/03 , B32B2250/04 , B32B2250/242 , B32B2250/40 , B32B2270/00 , B32B2307/516 , B32B2307/518 , B32B2307/558 , B32B2307/582 , B32B2307/708 , B32B2307/72 , B32B2323/046 , B32B2439/00 , C08L23/06 , C08L23/18 , Y10T428/1334 , Y10T428/1352 , Y10T428/24612 , Y10T428/24802 , Y10T428/24975
摘要： A multilayer film is provided, including a layer sequence of a layer (a) of at least one low density polyethylene (LDPE) having a density in the range 0.915-0.930 g/cm3 or a mixture of LDPE with at least one other acyclic C2-C6 olefin polymer or copolymer, a layer (b) of a mixture of at least one low density polyethylene (LDPE) having a density in the range 0.915-0.930 g/cm3 and at least one cyclic olefin copolymer, and a layer (c) of at least one low density polyethylene having a density in the range 0.915-0.930 g/cm3 or a mixture of LDPE with at least one other acyclic C2-C6 olefin polymer or copolymer, such that the film's tear propagation force in both the machine direction and transverse to the machine direction is at most 1000 mN, per the Elmendorf test (per DIN EN ISO 6383-2).
摘要翻译：提供了一种多层膜，其包括层密度为0.915-0.930g / cm3的至少一种低密度聚乙烯（LDPE）的层（a）的层序列，或LDPE与至少一种其它无环C2 -C 6烯烃聚合物或共聚物，至少一种密度为0.915-0.930g / cm3的低密度聚乙烯（LDPE）和至少一种环烯烃共聚物的混合物层（b）和一层（c ）至少一种密度为0.915-0.930g / cm3的低密度聚乙烯或LDPE与至少一种其它非环状C 2 -C 6烯烃聚合物或共聚物的混合物，使得该膜在两台机器中的撕裂传播力方向和横向于机器方向最大为1000mN，根据Elmendorf测试（根据DIN EN ISO 6383-2）。

7. 发明申请

US20090152405A1 Wing and method for reducing effects of propeller airflow on lift distribution 有权
标题翻译：翼和减少螺旋桨气流对升力分布的影响的方法
公开(公告)号：US20090152405A1
公开(公告)日：2009-06-18
申请号：US12316254
申请日：2008-12-10
申请人： Roland Kelm
发明人： Roland Kelm
IPC分类号： B64C3/44 , B64C3/50
CPC分类号： B64C3/50 , B64C11/00 , Y02T50/14
摘要： A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and/or reduced local twist, and a second region with an increased local wing camber and/or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.
摘要翻译：飞机的机翼包括不平衡的升力梯度，因为由于至少一个螺旋桨滑流流到机翼上，机翼的诱导阻力增加。为了减小增加的诱导阻力，机翼包括具有减小的局部翼弧和/或减小的局部扭曲的第一区域和具有增加的局部翼弯和/或增加的局部扭转的第二区域。第一区域被定义为位于螺旋桨滑流下游的机翼表面，螺旋桨叶片向上的翼面上游。第二区域被定义为位于螺旋桨滑流下游的机翼表面，其中螺旋桨的叶片向下移动的翼表面的上游。

8. 发明申请

US20080116320A1 Aircraft With Wings Whose Maximum Lift Can Be Altered By Controllable Wing Components 审中-公开
标题翻译：飞行器与最大提升可以由可控翼组件改变的翅膀
公开(公告)号：US20080116320A1
公开(公告)日：2008-05-22
申请号：US11663055
申请日：2005-09-21
申请人： Alexender Van Der Velden , Roland Kelm , Josef Mertens
发明人： Alexender Van Der Velden , Roland Kelm , Josef Mertens
IPC分类号： B64C13/16 , G05D1/08
CPC分类号： G05D1/0066 , B64C13/16 , Y02T50/44
摘要： The present invention relates to an aircraft with wings whose maximum lift can be altered by controllable wing components. By means of a regulating device (20), depending on flight state parameters and the actually measured load on the wings (10), wing components (11, 12) are acted upon such that the maximum possible aerodynamic lift does not exceed a desired upper limit value.
摘要翻译：本发明涉及具有机翼的飞行器，其最大升程可以由可控翼部件改变。通过调节装置（20），取决于飞行状态参数和机翼（10）上的实际测量的载荷，翼部件（11,12）的作用是使得最大可能的空气动力升程不超过所需的上限极限值。

9. 发明授权

US6161801A Method of reducing wind gust loads acting on an aircraft 有权
标题翻译：降低作用在飞机上的阵风负荷的方法
公开(公告)号：US6161801A
公开(公告)日：2000-12-19
申请号：US303264
申请日：1999-04-30
申请人： Roland Kelm , Michael Grabietz
发明人： Roland Kelm , Michael Grabietz
IPC分类号： B64C13/16 , G05D1/00 , G05D1/04
CPC分类号： B64C13/16 , G05D1/0066 , Y02T50/44
摘要： A method of reducing the bending moment effect of wind gust loads acting on the wing of an aircraft involves adjusting the aerodynamic configuration of the wing so as to alter the distribution of lift generated by the wing during phases of flight in which critical wind gusts are expected to occur. Particularly, during climb and descent phases of flight below cruise altitude, the lift generated by outboard portions of the wings is reduced while the lift generated by inboard portions of the wings is increased. Thereby, the 1 g basis load acting on the outboard portions of the wings is reduced, and consequently the total load applied to the outboard portions of the wings, resulting from the 1 g basis load plus the additional wind gust load, is correspondingly reduced. This leads to a reduction of the bending moments effective on the wings, and of any rolling moment effective on the aircraft. The required adjustment of the lift distribution is preferably achieved by deflecting the ailerons of both wings symmetrically upward and/or deflecting the flaps of both wings symmetrically downward during climb and descent. The adjustment of the wing configuration is carried out dependent only on flight parameters such as the altitude, speed and gross weight, and does not require rapid sensing of the occurrence of a wind gust and rapid actuation of control surfaces to try to instantaneously counteract a wind gust as it occurs.
摘要翻译：一种降低作用在飞机机翼上的阵风负荷的弯矩效应的方法包括调整机翼的空气动力学结构，以改变机翼在飞行期间产生的升力分布，其中预计发生关键阵风发生。特别地，在高于巡航高度的飞行爬升和下降阶段期间，由翼的外侧部分产生的升力增加，由翼的外侧部分产生的升力减小。因此，作用在翼的外侧部分上的1g基础载荷减小，因此相应地减小了由1g基础载荷加上另外的阵风载荷引起的翼的外侧部分的总载荷。这导致在翼上有效的弯矩的减少以及在飞机上有效的任何滚动力矩。升降机分配的所需调整优选通过在爬升和下降期间将两翼的副翼对称地向上偏转和/或偏转两个翼的翼片对称地实现。机翼结构的调整仅依赖于诸如高度，速度和总重等飞行参数，并且不需要快速检测风阵发的情况并快速致动控制表面以试图瞬间抵消风阵风发生时。

10. 发明授权

US08846202B2 Film arrangement 有权
标题翻译：电影安排
公开(公告)号：US08846202B2
公开(公告)日：2014-09-30
申请号：US12704826
申请日：2010-02-12
申请人： Kurt Stark , Karl Mauser , Roland Kelm
发明人： Kurt Stark , Karl Mauser , Roland Kelm
IPC分类号： B32B7/00 , B32B27/18 , B32B27/36 , B32B37/15
CPC分类号： B32B27/36 , B32B27/08 , B32B2307/7163 , Y10S428/91 , Y10T428/1352 , Y10T428/24802 , Y10T428/24942 , Y10T428/31786
摘要： A transparent multi-layered film arrangement comprising at least three layers, wherein the film arrangement comprises one layer is made of a biodegradable polylactic acid (PLA) and a polyglycol as plasticizer, said polyglycol having a molecular weight of between 35,000 and 4,000,000, and at least two outer layers, each of said two outer layers being made of PLA.
摘要翻译：一种透明的多层膜装置，其包括至少三层，其中所述膜装置包括一层由可生物降解的聚乳酸（PLA）和作为增塑剂的聚乙二醇制成，所述聚乙二醇的分子量为35,000至4,000,000，至少两个外层，所述两个外层中的每一个均由PLA制成。

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