公开(公告)号：US4635881A

公开(公告)日：1987-01-13

申请号：US764314

申请日：1985-08-09

申请人： Bernd Brieseck ,  Peter Kreuzer

发明人： Bernd Brieseck ,  Peter Kreuzer

IPC分类号： F42B10/14 ,  B64C3/56

CPC分类号： F42B10/14

摘要： A foldable wing or airfoil, which is especially but not exclusively adapted for a projectile, and which incorporates interengaging telescopable fin sections. A nose in the foldable wing, which is hingable in the region of one end through a pivot in a longitudinal groove, has a chamber opening facing away from its leading edge and which is located between the wing part surfaces for receiving the interlocking fin sections, which sections are profiled in U-shaped configuration. The chamber also receives a base or root spar which is hinged in the region of its leading end in the chamber, and wherein the front ends of the fin sections straddle the root spar and are each hinged along the root spar offset relative to each other.

摘要翻译： 可折叠翼或翼型，其特别但不排他地适用于抛射体，并且其包括相互接合的可伸缩翼片部分。 可折叠翼中的鼻部可以在纵向凹槽中通过枢轴在一端的区域中铰接，具有一个朝向前缘的腔室开口，该腔室位于翼部件表面之间，用于接收联锁翅片部分， 哪些部分是U形配置的。 该腔室还容纳基部或根部翼梁，其底部或根部翼梁铰接在其前端的腔室的区域中，并且其中翅片部分的前端跨越根梁，并且各自沿着相对于彼此偏离的根翼梁铰接。

公开(公告)号：US20070235269A1

公开(公告)日：2007-10-11

申请号：US11709418

申请日：2007-02-22

申请人： Andreas Ganghofer ,  Peter Kreuzer ,  Roland Muller

发明人： Andreas Ganghofer ,  Peter Kreuzer ,  Roland Muller

IPC分类号： F16F3/00

CPC分类号： F41H11/08 ,  G08B15/007

摘要： A motion-restraint arrangement (48) with elongate lines of elements (10), wherein each line of elements (10) has a number of individual elements (12) which can be erected by spring elements (20) from a small-volume thin storage condition into a large-volume active condition. Each respective individual element (12) has flexible lateral edge elements (16, 18), which in the active condition define a parallelepiped. The spring elements (20) extend in spatially diagonal relationship between the corners (22) of the respective parallelepiped (14). A motion-restraint arrangement (48) which is easy and inexpensive to produce and which has optimum restraint properties is obtained in that the spatially diagonal spring elements (20) are formed by spring wires (24), which extend in a zigzag shape in the longitudinal direction of the respective line of elements (10).

摘要翻译： 一种具有细长线元件（10）的运动约束装置（48），其中每条线元件（10）具有多个单独的元件（12），其可以由弹簧元件（20）从小体积薄 存储条件变成大容量的活动状态。 每个相应的单个元件（12）具有柔性侧向边缘元件（16,18），其在活动状态中限定平行六面体。 弹簧元件（20）在相应平行六面体（14）的拐角（22）之间的空间对角关系中延伸。 获得容易制造且具有最佳约束特性的运动约束装置（48），其中空间对角弹簧元件（20）由弹簧线（24）形成，弹簧线（24）在Z形 元件（10）的相应线的纵向方向。

公开(公告)号：US09038950B2

公开(公告)日：2015-05-26

申请号：US13588276

申请日：2012-08-17

申请人： Peter Kreuzer ,  Sven Schaber ,  Iris Goldhahn

发明人： Peter Kreuzer ,  Sven Schaber ,  Iris Goldhahn

IPC分类号： B64C1/38 ,  B64C23/06 ,  B64C21/10

CPC分类号： B64C23/06 ,  B64C21/10 ,  Y02T50/162

摘要： An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

摘要翻译： 空气动力辅助表面的布置被配置为布置在飞行器的下侧，并且还包括纵向轴线和至少一个空气动力学辅助表面，其中空气动力辅助表面以纵向轴线横向偏移，并且其中空气动力辅助 表面被配置为在受到迎面而来的气流时产生涡流。 这使得可以补偿由飞行器的形状引起的旋涡，从而可以提高飞机的方向稳定性并且可以减小空气动力学阻力。

公开(公告)号：US06722615B2

公开(公告)日：2004-04-20

申请号：US10116875

申请日：2002-04-05

申请人： Gerd Heller ,  Manfred Maisel ,  Peter Kreuzer

发明人： Gerd Heller ,  Manfred Maisel ,  Peter Kreuzer

IPC分类号： B64C508

CPC分类号： B64C3/10 ,  B64C23/069 ,  Y02T50/12 ,  Y02T50/164

摘要： The present invention relates to a wing tip extension (7) for a wing, having an upper and a lower surface (10 and 11) and a leading edge and a trailing edge (12 and 13), the geometries of which are such that between a connection region (8), for connection with a wing, and the tip (9) of the wing tip extension (7) there is provided a continuous increase of the local dihedral, a continuous increase both of the sweepback angle of the leading edge (12) and also of the trailing edge (13), and a continuous decrease of the chord of the wing tip extension (7), and in that the wing tip extension (7) in the connection region (8) carries on from the wing in substance continuously. The wing tip extension (7) in accordance with the invention thereby ensures a significant reduction of the overall drag.

摘要翻译： 本发明涉及一种用于机翼的翼尖延伸部（7），其具有上和下表面（10和11）以及前缘和后缘（12和13），其几何形状使得在 用于与翼连接的连接区域（8）和翼尖延伸部（7）的尖端（9）提供局部二面体的连续增加，连续增加前缘的回扫角 （12）以及后缘（13）的延伸，并且翼尖延伸部（7）的弦的连续减小，并且连接区域（8）中的翼尖延伸部（7）从 翼在物质上不断。 因此，根据本发明的翼尖延伸部（7）从而确保整体阻力的显着减小。

公开(公告)号：US07793921B2

公开(公告)日：2010-09-14

申请号：US11709418

申请日：2007-02-22

申请人： Andreas Ganghofer ,  Peter Kreuzer ,  Roland Müller

发明人： Andreas Ganghofer ,  Peter Kreuzer ,  Roland Müller

IPC分类号： E04H17/02

CPC分类号： F41H11/08 ,  G08B15/007

摘要： A motion-restraint arrangement (48) with elongate lines of elements (10), wherein each line of elements (10) has a number of individual elements (12) which can be erected by spring elements (20) from a small-volume thin storage condition into a large-volume active condition. Each respective individual element (12) has flexible lateral edge elements (16, 18), which in the active condition define a parallelepiped. The spring elements (20) extend in spatially diagonal relationship between the corners (22) of the respective parallelepiped (14). A motion-restraint arrangement (48) which is easy and inexpensive to produce and which has optimum restraint properties is obtained in that the spatially diagonal spring elements (20) are formed by spring wires (24), which extend in a zigzag shape in the longitudinal direction of the respective line of elements (10).

摘要翻译： 一种具有细长线元件（10）的运动约束装置（48），其中每条线元件（10）具有多个单独的元件（12），其可以由弹簧元件（20）从小体积薄 存储条件变成大容量的活动状态。 每个相应的单个元件（12）具有柔性侧向边缘元件（16,18），其在活动状态中限定平行六面体。 弹簧元件（20）在相应平行六面体（14）的拐角（22）之间的空间对角关系中延伸。 获得容易制造且具有最佳约束特性的运动约束装置（48），其中空间对角弹簧元件（20）由弹簧线（24）形成，弹簧线（24）在Z形 元件（10）的相应线的纵向方向。

公开(公告)号：US20130001362A1

公开(公告)日：2013-01-03

申请号：US13588276

申请日：2012-08-17

申请人： Peter Kreuzer ,  Sven Schaber ,  Iris Goldhahn

发明人： Peter Kreuzer ,  Sven Schaber ,  Iris Goldhahn

IPC分类号： B64C23/06

CPC分类号： B64C23/06 ,  B64C21/10 ,  Y02T50/162

摘要： An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

摘要翻译： 空气动力辅助表面的布置被配置为布置在飞行器的下侧，并且还包括纵向轴线和至少一个空气动力学辅助表面，其中空气动力辅助表面以纵向轴线横向偏移，并且其中空气动力辅助 表面被配置为在受到迎面而来的气流时产生涡流。 这使得可以补偿由飞行器的形状引起的旋涡，从而可以提高飞机的方向稳定性并且可以减小空气动力学阻力。