公开(公告)号：US20080142640A9

公开(公告)日：2008-06-19

申请号：US11183475

申请日：2005-07-18

申请人： Damien Lejeau ,  Petra Aumann ,  Detlev Schwetzler

发明人： Damien Lejeau ,  Petra Aumann ,  Detlev Schwetzler

IPC分类号： B64C9/00 ,  B64D39/00

CPC分类号： B64C7/00 ,  B64C5/00 ,  B64C23/00 ,  B64D39/00

摘要： The present application describes to a deflection device, for example, for a blunt stream body. The deflection device has an edge, which, for example, can be mounted to the stream body. In an advantageous manner, the deflection device allows an influencing of the slipstream in such a way that turbulences, which are connected with the slipstream and form downstream of blunt stream bodies, have as little influence as possible on the dragged object in order to avoid the formation of building-up motions of the dragged object, which lead to instabilities.

摘要翻译： 本申请描述了例如用于钝流体的偏转装置。 偏转装置具有边缘，其例如可以安装到流体。 以有利的方式，偏转装置允许影响滑流，使得与滑流连接并形成钝流体下游的湍流对拖曳物体具有尽可能小的影响，以避免湍流 形成拖延对象的建构动议，导致不稳定。

公开(公告)号：US20100176249A1

公开(公告)日：2010-07-15

申请号：US12663094

申请日：2008-06-16

申请人： Detlev Schwetzler

发明人： Detlev Schwetzler

IPC分类号： B64D29/02 ,  B64C7/02 ,  B64C23/06

CPC分类号： B64C7/02 ,  B64C23/06 ,  B64D29/02 ,  Y02T50/162

摘要： An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔.

摘要翻译： 飞机的发动机舱，其一侧的发动机舱包括若干鳍状涡流发生器，使得随着迎角的增加，为了改善最大升力，由所述涡流发生器产生的涡流场总体上延伸越过 所述第一涡旋发生器位于位于两条边界线之间的定位走廊内，其中：所述第一边界线的起始点是所述发动机舱的发动机舱的圆周点， 机舱圆周角度phi = 35度，发动机舱纵向坐标X = L / 4; 第一条边界线的终点是发动机舱周向角度phi = 25度，发动机舱纵向坐标X = L·the的发动机舱的圆周点; 第二边界线的起点是发动机舱的圆周角，发动机舱的圆周角度为= 90度，发动机舱纵向坐标X = L / 4; 第二边界线的终点是发动机机舱圆周角度phi = 55度，发动机舱纵向坐标X = L·the的发动机舱的圆周点。

公开(公告)号：US20070006645A1

公开(公告)日：2007-01-11

申请号：US11316151

申请日：2005-12-22

申请人： Detlev Schwetzler ,  Peter May

发明人： Detlev Schwetzler ,  Peter May

IPC分类号： G01P13/00

CPC分类号： G01M9/06 ,  G01M9/062

摘要： The present invention relates to a method for improving the precision of wind tunnel measurements, particularly to correct the influence of a suspension device, wherein a model, particularly an aircraft model, being introduced into a wind tunnel on the suspension device, which has multiple suspension wires, and at least one sleeve being attached to each suspension wire, having the following steps: performing at least two measurements with identical model configuration with at least one effective diameter and/or with the suspension wire diameter in each case to ascertain at least two raw measured values and ascertaining a corrected final measured value for the model from at least two measured values. According to a first embodiment variation of the method according to the present invention, for example, in the course of detecting raw measured values of the air resistance coefficient of the model, the effective diameter of the suspension wires is reduced in at least three steps by removing sleeves which have been pushed on. A final measured value of the air resistance coefficient, which has been corrected for the influence of the suspension device and the interference between model and suspension device, may be ascertained from the raw measured values through interpolation. According to a further variation, the correction is performed through difference calculation of only two raw measured values, one of the raw measured values being ascertained with the suspension wire diameter without sleeves pushed on. The method is suitable for correcting all aerodynamic characteristic variables measurable in the wind tunnel. Furthermore, the present invention relates to a device for performing the method.

摘要翻译： 本发明涉及一种用于提高风洞测量精度的方法，特别是用于校正悬挂装置的影响的方法，其中将模型，特别是飞行器模型引入到具有多个悬架的悬挂装置上的风洞中 线和至少一个套筒连接到每个悬挂线，具有以下步骤：在具有至少一个有效直径和/或每种情况下的悬挂线直径的情况下执行具有相同模型构造的至少两个测量以确定至少两个 原始测量值，并从至少两个测量值确定模型的校正最终测量值。 根据本发明的方法的第一实施方式的变形例，例如，在检测模型的空气阻力系数的原始测量值的过程中，悬挂线的有效直径在至少三个步骤中通过 去除被推上的袖子。 可以从原始测量值通过插值确定已经针对悬挂装置的影响进行校正的空气阻力系数的最终测量值和模型和悬挂装置之间的干扰。 根据进一步的变化，通过仅计算两个原始测量值的差分计算来执行校正，其中一个原始测量值用悬挂线直径确定，而没有套筒被推开。 该方法适用于校正风洞中可测量的所有空气动力学特征变量。 此外，本发明涉及一种用于执行该方法的装置。

公开(公告)号：US20060284023A1

公开(公告)日：2006-12-21

申请号：US11183475

申请日：2005-07-18

申请人： Damien Lejeau ,  Petra Aumann ,  Detlev Schwetzler

发明人： Damien Lejeau ,  Petra Aumann ,  Detlev Schwetzler

IPC分类号： B64C9/00 ,  B64D39/00

CPC分类号： B64C7/00 ,  B64C5/00 ,  B64C23/00 ,  B64D39/00

摘要： The present invention relates to a deflection device, for example, for a blunt stream body. The deflection device has an edge, which, for example, can be mounted to the stream body. In an advantageous manner, the deflection device allows an influencing of the slipstream in such a way that turbulences, which are connected with the slipstream and form downstream of blunt stream bodies, have as little influence as possible on the dragged object in order to avoid the formation of building-up motions of the dragged object, which lead to instabilities.

摘要翻译： 本发明涉及例如用于钝流体的偏转装置。 偏转装置具有边缘，其例如可以安装到流体。 以有利的方式，偏转装置允许影响滑流，使得与滑流连接并形成钝流体下游的湍流对拖曳物体具有尽可能小的影响，以避免 形成拖延对象的建构动议，导致不稳定。

公开(公告)号：US08181912B2

公开(公告)日：2012-05-22

申请号：US12454922

申请日：2009-05-26

申请人： Detlev Schwetzler

发明人： Detlev Schwetzler

IPC分类号： B64C23/06 ,  B64D29/00

CPC分类号： B64C23/06 ,  B64C7/02 ,  B64D29/02 ,  Y02T50/162

摘要： An engine pod for an aircraft has one side which features several fin-shaped vortex generators such that the overall vorticity field generated by the vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases. The first vortex generator lies within a positioning corridor that is situated between two boundary lines. The origin and end points, respectively, of the first boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and 25 degrees and the longitudinal engine pod coordinate X=L/4 and L·⅔. The origin and end points, respectively, of the second boundary line are the points on the circumference of the engine pod with the circumferential engine pod angle phi=90 degrees and 55 degrees and the longitudinal engine pod coordinate X=L/4 and L·⅔.

摘要翻译： 用于飞行器的发动机舱具有一侧，其特征在于具有若干鳍形涡流发生器，使得涡流发生器产生的整体涡度场随着迎角增加而在翼展方向上延伸越过翼型面积。 第一个涡流发生器位于两条边界线之间的定位走廊内。 第一边界线的起点和终点分别是发动机舱的圆周上的点，圆周发动机舱角度为35度和25度，纵向发动机舱座标X = L / 4和L· ⅔。 第二边界线的起点和终点分别是发动机舱的圆周上的点，圆周发动机舱角度φi= 90度和55度，纵向发动机舱座标X = L / 4和L· ⅔。

公开(公告)号：US20090289149A1

公开(公告)日：2009-11-26

申请号：US12454922

申请日：2009-05-26

申请人： Detlev Schwetzler

发明人： Detlev Schwetzler

IPC分类号： B64C23/06 ,  B64C7/02

CPC分类号： B64C23/06 ,  B64C7/02 ,  B64D29/02 ,  Y02T50/162

摘要： The invention pertains to an engine pod for an aircraft, one side of which features several fin-shaped vortex generators (3, 4, 5) such that the overall vorticity field generated by the vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases in order to improve the maximum lift, wherein the first vortex generator lies within a positioning corridor (K31) that is situated between two boundary lines (51, 52), wherein the point of origin (51a) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and the longitudinal engine pod coordinate X=L/4, the end point (51b) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=25 degrees and the longitudinal engine pod coordinate X=L·⅔, the point of origin (52a) of the second boundary line (52) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=90 degrees and the longitudinal engine pod coordinate X=L/4 and the end point (52b) of the second boundary line (52) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=55 degrees and the longitudinal engine pod coordinate X=L·⅔.

摘要翻译： 本发明涉及一种用于飞行器的发动机舱，其一侧具有若干鳍形涡流发生器（3,4,5），使得由涡流发生器产生的整体涡流场在翼展方向上延伸超过增加的翼型面积 随着迎角增加以改善最大升力，其中第一涡流发生器位于位于两个边界线（51,52）之间的定位走廊（K31）内，其中，该起点（51a） 第一边界线（51）是发动机舱的圆周上的点，圆周发动机舱角度phi = 35度，纵向发动机舱架坐标X = L / 4，第一边界线的端点（51b） 51）是发动机舱的圆周上的点，圆周发动机舱角度为phi = 25度，纵向发动机舱座标X = L.2 / 3，第二边界线（52）的起点（52a） ）是圆环上的点 e，发动机舱的周向发动机舱角度为phi = 90度，纵向发动机舱架坐标X = L / 4，第二边界线（52）的端点（52b）为发动机圆周上的点 圆周发动机舱角度phi = 55度，纵向发动机舱架坐标X = L.2 / 3。

公开(公告)号：US06641089B2

公开(公告)日：2003-11-04

申请号：US10255765

申请日：2002-09-25

申请人： Detlev Schwetzler ,  Peter May

发明人： Detlev Schwetzler ,  Peter May

IPC分类号： B64C300

CPC分类号： B64C9/18

摘要： An auxiliary flap is movably arranged on a planar trailing edge of an aerodynamic element such as a wing, rudder, stabilizer, or flap. The auxiliary flap is rotatable and/or slidable relative to the aerodynamic element, to move selectively into three positions. In a first position, a free edge of the auxiliary flap protrudes into an airflow boundary layer on one side of the aerodynamic element, to decrease lift. In a second position, a free edge of the aerodynamic element protrudes into an airflow boundary layer on the other side of the aerodynamic element, to increase lift. In a third neutral position, the auxiliary element does not protrude into either boundary layer, so as not to influence lift. The auxiliary flap is simple and rapidly acting. The flap protrudes substantially perpendicularly into the boundary layer flow. The auxiliary flap has a planar plate shape.

公开(公告)号：US08827210B2

公开(公告)日：2014-09-09

申请号：US12663094

申请日：2008-06-16

申请人： Detlev Schwetzler

发明人： Detlev Schwetzler

IPC分类号： B64C23/06 ,  B64C7/02 ,  B64D29/02

CPC分类号： B64C7/02 ,  B64C23/06 ,  B64D29/02 ,  Y02T50/162

摘要： An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔.

摘要翻译： 飞机的发动机舱，其一侧的发动机舱包括若干鳍状涡流发生器，使得随着迎角的增加，为了改善最大升力，由所述涡流发生器产生的涡流场总体上延伸越过 所述第一涡旋发生器位于位于两条边界线之间的定位走廊内，其中：所述第一边界线的起始点是所述发动机舱的发动机舱的圆周点， 机舱圆周角度phi = 35度，发动机舱纵向坐标X = L / 4; 第一条边界线的终点是发动机舱周向角度phi = 25度，发动机舱纵向坐标X = L·the的发动机舱的圆周点; 第二边界线的起点是发动机舱的圆周角，发动机舱的圆周角度为= 90度，发动机舱纵向坐标X = L / 4; 第二边界线的终点是发动机机舱圆周角度phi = 55度，发动机舱纵向坐标X = L·the的发动机舱的圆周点。

公开(公告)号：US07931236B2

公开(公告)日：2011-04-26

申请号：US11183475

申请日：2005-07-18

申请人： Damien Lejeau ,  Petra Aumann ,  Detlev Schwetzler

发明人： Damien Lejeau ,  Petra Aumann ,  Detlev Schwetzler

IPC分类号： B64D39/00

CPC分类号： B64C7/00 ,  B64C5/00 ,  B64C23/00 ,  B64D39/00

摘要： The present application describes to a deflection device, for example, for a blunt stream body. The deflection device has an edge, which, for example, can be mounted to the stream body. In an advantageous manner, the deflection device allows an influencing of the slipstream in such a way that turbulences, which are connected with the slipstream and form downstream of blunt stream bodies, have as little influence as possible on the dragged object in order to avoid the formation of building-up motions of the dragged object, which lead to instabilities.

摘要翻译： 本申请描述了例如用于钝流体的偏转装置。 偏转装置具有边缘，其例如可以安装到流体。 以有利的方式，偏转装置允许影响滑流，使得与滑流连接并形成钝流体下游的湍流对拖曳物体具有尽可能小的影响，以避免 形成拖延对象的建构动议，导致不稳定。

公开(公告)号：US07310998B2

公开(公告)日：2007-12-25

申请号：US11316151

申请日：2005-12-22

申请人： Detlev Schwetzler ,  Peter May

发明人： Detlev Schwetzler ,  Peter May

IPC分类号： G01M9/00

CPC分类号： G01M9/06 ,  G01M9/062

摘要： A method for improving the precision of wind tunnel measurements provides a correction to reduce the influence of a suspension device. A model, such as an aircraft model, is held by the suspension device in a wind tunnel and has multiple suspension wires. By attaching one or more sleeves to each suspension wire, a plurality of measurements with identical model configuration are capable of providing data for extrapolating corrected measurement values for a plurality of aerodynamic characteristic variables measurable in a wind tunnel. Examples of sleeves include a slit along the sleeve length and an inner diameter of the sleeves selected such that the sleeve is capable of being pressed onto and removed from a suspension wire or a sleeve of lesser outer diameter.

摘要翻译： 提高风洞测量精度的方法提供了一种校正，以减少悬挂装置的影响。 诸如飞机模型的模型由悬挂装置保持在风洞中并且具有多个悬挂线。 通过将一个或多个套筒连接到每个悬挂线，具有相同模型配置的多个测量能够提供用于外推经校正的测量值的数据，用于在风洞中可测量的多个空气动力特性变量。 袖子的例子包括沿着套筒长度的狭缝和套筒的内径，这样套筒的内径能够被套在一个较小外径的悬挂线或套筒上并被移除。