公开(公告)号：US20130039379A1

公开(公告)日：2013-02-14

申请号：US13583654

申请日：2011-03-07

申请人： Rolf Best ,  Peter Starke ,  Andreas Schuering

发明人： Rolf Best ,  Peter Starke ,  Andreas Schuering

IPC分类号： H05B7/10

CPC分类号： H05B7/12 ,  H05B7/101

摘要： The invention relates to an electrode support arm system for metallurgical furnaces, having an electrode arm (1) having an electrode support arm head (13) implemented as an electrode support device at the front part thereof, designed as a hollow profile having a wall formed at least partially of conductive material having high conductivity, through which a coolant can be guided. According to the invention, flow guide plates and/or displacers are disposed with the electrode support arm (1) implemented as a hollow profile and within the electrode support device implemented on the electrode support arm head (13), by which the coolant flow can be channelized and affected with respect to flow speed, such that optimal flow speeds of the coolant are present at all locations within the electrode support arm (1) and the electrode support arm head (13), wherein highly thermally loaded regions, such as the contact surfaces on the electrode support arm head (13), can be intensively cooled than other, less intensely thermally loaded regions of the electrode support arm (1).

摘要翻译： 本发明涉及一种用于冶金炉的电极支撑臂系统，具有电极臂（1），电极臂（1）具有在其前部被实现为电极支撑装置的电极支撑臂头（13），被设计为具有壁的中空型材 至少部分地具有高导电性的导电材料，通过该导电材料可以引导冷却剂。 根据本发明，流动引导板和/或置换器设置有电极支撑臂（1）实现为空心轮廓并且在实施在电极支撑臂头部（13）上的电极支撑装置内，冷却剂流可以 相对于流速被通道化和影响，使得冷却剂的最佳流速存在于电极支撑臂（1）和电极支撑臂头（13）内的所有位置处，其中高度热负荷的区域，例如 电极支撑臂头部（13）上的接触表面可以比电极支撑臂（1）的其他较不强烈热负载的区域强烈地冷却。

公开(公告)号：US09340274B2

公开(公告)日：2016-05-17

申请号：US13469325

申请日：2012-05-11

申请人： Peter Starke ,  Michael Fischer ,  Martha Wachinger

发明人： Peter Starke ,  Michael Fischer ,  Martha Wachinger

IPC分类号： B64C1/12

CPC分类号： B64C1/12

摘要： An impact protection plate is provided for mounting on the structure of an aircraft. The impact protection plate includes a first layer, close to the aircraft, made of a fiber-reinforced plastic having a wave-shaped pattern of alternating elevations and depressions, the transverse tensile strength of the fiber-reinforced plastic being greater than 50 MPa. The impact protection plate includes a second layer situated on the first layer, remote from the aircraft, and is made of a fiber-reinforced plastic, the elongation at break of the reinforcement fibers being greater than 3%.

摘要翻译： 提供了一种用于安装在飞行器结构上的冲击保护板。 冲击保护板包括靠近飞行器的第一层，由具有交替升降凹凸图形的纤维增强塑料制成，纤维增强塑料的横向拉伸强度大于50MPa。 冲击保护板包括位于第一层上的远离飞行器的第二层，并且由纤维增强塑料制成，增强纤维的断裂伸长率大于3％。

公开(公告)号：US07566489B2

公开(公告)日：2009-07-28

申请号：US11154470

申请日：2005-06-17

申请人： Peter Starke

发明人： Peter Starke

IPC分类号： B32B1/00 ,  B32B3/28 ,  E04C2/32 ,  B64D7/00 ,  B64C1/00

CPC分类号： B32B7/02 ,  B32B3/28 ,  B32B2307/56 ,  B32B2605/18 ,  B64C3/28 ,  F16F3/10 ,  F16F7/121 ,  Y10S428/911 ,  Y10T428/234 ,  Y10T428/24661 ,  Y10T428/24678 ,  Y10T428/24694

摘要： A shock-absorbing structure component has two cover layers and an intermediate layer that is arranged between them. The intermediate layer extends in an alternating form between the cover layers, with the material of the intermediate layer being selected such that it has a higher capacity elongation prior to breaking than that of the outer cover layer. The energy of an impact can thus be absorbed as the intermediate layer is stretched into a bag shape and the inner cover layer breaks off progressively.

摘要翻译： 减震结构部件具有两个覆盖层和布置在它们之间的中间层。 中间层在覆盖层之间以交替的形式延伸，中间层的材料被选择为使得其在断裂之前具有比外覆层更高的容量伸长率。 因此，当中间层被拉伸成袋状并且内覆层逐渐断裂时，冲击的能量可以被吸收。

公开(公告)号：US06660219B1

公开(公告)日：2003-12-09

申请号：US09980245

申请日：2002-02-28

申请人： Manfred Schubert ,  Peter Starke

发明人： Manfred Schubert ,  Peter Starke

IPC分类号： F27D2300

CPC分类号： F27B3/08 ,  F27B3/065 ,  F27B3/19

摘要： The invention relates to the emptying of melting vessels (1) by tipping. According to the invention, the melting vessel (1) is placed on column-shaped bases (6). During the tipping process, the melting vessel (1) is raised at the side and the base supports (7) of the opposite side are used as the pivot or axis of rotation. This ensures that the discharge opening (4) and the slag overflow edge (5) are not moved very far from their original position.

摘要翻译： 本发明涉及通过倾翻排空熔化容器（1）。 根据本发明，将熔融容器（1）放置在柱状基底（6）上。 在倾翻过程中，熔化容器（1）在侧面升高，并且相对侧的基部支撑件（7）用作枢转或旋转轴线。 这确保排出口（4）和渣溢出边缘（5）不会离开它们的初始位置非常远。

公开(公告)号：US20130112811A1

公开(公告)日：2013-05-09

申请号：US13640495

申请日：2011-04-09

申请人： Franziskus Mayer ,  Christoph Meisner ,  Peter Starke

发明人： Franziskus Mayer ,  Christoph Meisner ,  Peter Starke

IPC分类号： B64C1/00 ,  B64C1/06

CPC分类号： B64C1/062

摘要： An aircraft fuselage has an integrated energy-absorbing deformation structure. The fuselage includes annular frames, longitudinal fuselage beams interconnecting the annular frames, and a covering forming a fuselage skin. A lower floor structure is disposed in an interior of the fuselage. The lower floor structure includes a plurality of transverse beams connected to an assigned frame and longitudinal floor beams which interconnect said transverse beams. The deformation structure is formed in a lower fuselage region disposed below the lower floor structure. The deformation structure includes a first inelastically deformable central region and, on a left-hand side and a right-hand side, respective second inelastically deformable regions of greater stiffness in the vertical direction than the central region.

摘要翻译： 飞机机身具有集成的能量吸收变形结构。 机身包括环形框架，连接环形框架的纵向机身梁和形成机身皮肤的覆盖物。 较低的底板结构设置在机身的内部。 下层结构包括连接到分配框架的多个横梁和连接所述横梁的纵向地板梁。 变形结构形成在设置在下层结构下方的下部机身区域中。 变形结构包括第一非易弹性中心区域，并且在左侧和右侧具有比中心区域在竖直方向上更大刚度的相应的第二非弹性变形区域。

公开(公告)号：US06728291B1

公开(公告)日：2004-04-27

申请号：US09980159

申请日：2002-02-28

申请人： Manfred Schubert ,  Peter Starke

发明人： Manfred Schubert ,  Peter Starke

IPC分类号： F27D100

CPC分类号： F27B3/24 ,  F27B3/085 ,  F27B3/10 ,  H05B3/03 ,  H05B7/06 ,  H05B7/12

摘要： The aim of the invention is to improve the cooling of the bottom electrodes (1) of metallurgical melting vessels. To this end, a cooling plate (5) is situated beneath the support plate (2) on which the contact elements (3) are supported. The cooling plate is set apart from the support plate. This forms a cooling chamber (4) through which a cooling medium flows, the cooling effect of said medium being reinforced by cooling ribs (6). Said cooling ribs are situated in the cooling chamber (4) and are welded to the support plate (2) and preferably, also to the cooling plate (5).

摘要翻译： 本发明的目的是改善冶金熔化容器的底部电极（1）的冷却。 为此，冷却板（5）位于其上支撑接触元件（3）的支撑板（2）的下方。 冷却板与支撑板分开。 这形成冷却室（4），冷却介质通过冷却室流动，所述介质的冷却效果由冷却肋（6）加强。 所述冷却肋位于冷却室（4）中并且焊接到支撑板（2）上，优选地也被焊接到冷却板（5）。

公开(公告)号：US07923096B2

公开(公告)日：2011-04-12

申请号：US12191753

申请日：2008-08-14

申请人： Peter Starke

发明人： Peter Starke

IPC分类号： B32B3/28 ,  B64D7/00 ,  B64C5/00

CPC分类号： B32B27/08 ,  B32B3/28 ,  B32B7/02 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2305/08 ,  B32B2307/56 ,  B32B2605/18 ,  B64C3/28 ,  F41H5/04 ,  Y10S428/911 ,  Y10T428/234 ,  Y10T428/24661 ,  Y10T428/24694 ,  Y10T428/24942

摘要： An impulse-absorbing structural component, particularly for an aircraft, has an impulse-absorbing layer and a covering layer applied thereto. The impulse-absorbing layer is made of a material that has a higher capacity for elongation at its breaking point than does the covering layer, and has a regular pattern of elevations and depressions. If a mass impacts on the covering layer, an intercept bag forms in the impulse-absorbing layer, and absorbs the kinetic energy of the mass. Viewed in the direction of the spread of the intercept bag, the structural component has structure beyond the impulse-absorbing layer, such that the formation of the intercept bag can take place without further interaction with the structural component.

摘要翻译： 特别是用于飞行器的脉冲吸收结构部件具有施加到其上的脉冲吸收层和覆盖层。 脉冲吸收层由在断裂点具有比覆盖层更高的伸长能力的材料制成，并且具有规则的高度和凹陷图案。 如果质量影响覆盖层，则在脉冲吸收层中形成拦截袋，并吸收物质的动能。 沿着拦截袋的扩展方向观察，结构部件具有超出脉冲吸收层的结构，使得拦截袋的形成可以在不与结构部件进一步相互作用的情况下进行。

公开(公告)号：US06693949B1

公开(公告)日：2004-02-17

申请号：US09980160

申请日：2002-02-28

申请人： Manfred Schubert ,  Peter Starke

发明人： Manfred Schubert ,  Peter Starke

IPC分类号： F27D900

CPC分类号： F27B3/24 ,  F27D19/00 ,  F27D2009/0008

摘要： The aim of the invention is to provide a means of also cooling the lower part of electric arc furnaces and/or resistance furnaces. To this end, said lower part—the actual melting vessel (4)—is surrounded with a jacket (9) at a certain distance, forming a shell, and the resulting intermediate space is configured as a cooling device (10) and subjected to the action of a cooling medium (14).

摘要翻译： 本发明的目的是提供一种还冷却电弧炉和/或电阻炉的下部的装置。 为此，所述下部 - 实际的熔化容器（4） - 以一定的距离用夹套（9）围绕，形成壳体，并且所得到的中间空间被配置为冷却装置（10）并经受 冷却介质（14）的作用。

公开(公告)号：US09162745B2

公开(公告)日：2015-10-20

申请号：US13640495

申请日：2011-04-09

申请人： Franziskus Mayer ,  Christoph Meisner ,  Peter Starke

发明人： Franziskus Mayer ,  Christoph Meisner ,  Peter Starke

IPC分类号： B64C1/06

CPC分类号： B64C1/062

摘要： An aircraft fuselage has an integrated energy-absorbing deformation structure. The fuselage includes annular frames, longitudinal fuselage beams interconnecting the annular frames, and a covering forming a fuselage skin. A lower floor structure is disposed in an interior of the fuselage. The lower floor structure includes a plurality of transverse beams connected to an assigned frame and longitudinal floor beams which interconnect said transverse beams. The deformation structure is formed in a lower fuselage region disposed below the lower floor structure. The deformation structure includes a first inelastically deformable central region and, on a left-hand side and a right-hand side, respective second inelastically deformable regions of greater stiffness in the vertical direction than the central region.

摘要翻译： 飞机机身具有集成的能量吸收变形结构。 机身包括环形框架，连接环形框架的纵向机身梁和形成机身皮肤的覆盖物。 较低的底板结构设置在机身的内部。 下层结构包括连接到分配框架的多个横梁和连接所述横梁的纵向地板梁。 变形结构形成在设置在下层结构下方的下部机身区域中。 变形结构包括第一非易弹性中心区域，并且在左侧和右侧具有比中心区域在竖直方向上更大刚度的相应的第二非弹性变形区域。