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1. 发明授权

US5636969A Torque tube/spar assembly for variable diameter helicopter rotors 失效
公开(公告)号：US5636969A
公开(公告)日：1997-06-10
申请号：US412175
申请日：1995-03-28
申请人： David G. Matuska , Edward W. Gronenthal , W. Donald Jepson
发明人： David G. Matuska , Edward W. Gronenthal , W. Donald Jepson
IPC分类号： B64C11/00 , B64C27/473 , B64C29/00 , B64C11/28
CPC分类号： B64C11/003 , B64C29/0033
摘要： A torque tube/spar assembly (100) for transferring operational loads of a Variable Diameter Rotor blade assembly (16) to a rotor hub assembly (18) and includes a torque tube member (24), a spar member (30) and a bearing assembly (40a, 40b) for telescopically mounting the spar member (30) to the torque tube member (24) and furthermore defines an internal channel (62) for housing a retraction/extension mechanism (64) which mounts to an internally formed restraint surface (86) of the spar member (30) and is operative to vary the length of the rotor blade assembly (18). The torque tube member (30) has a substantially constant external geometry along the length of bearing assembly engagement and defines a root end region (102), a tip end region (106) and an intermediate transition region (104) disposed therebetween. The spar member (30) has a substantially constant internal geometry and defines a root end region (110), a first transition (112), an intermediate region (114), a second transition region (116), a restraint region (118) and a tip end region (120). Each of the various regions of the torque tube and spar members (24, 30) have a characteristic stiffness value wherein the characteristic values (104m, 106m) of the intermediate transition and tip end regions (104,106) of the torque tube member (24) are less than the characteristic stiffness value (102m) of the root end region (102) thereof, and wherein the characteristic stiffness value (118m) of the restraint region (118) of the spar member (30) is greater than said characteristic stiffness values (114m, 120m) of the intermediate and tip end regions (114, 120) thereof, and wherein the characteristic stiffness value (114m) of the intermediate region (114) is less than the characteristic stiffness values (110m, 112m, 116m, 118m) of the root end, first transition, second transition and restraint regions (110, 112, 116, 118).

2. 发明授权

US5642982A Retraction/extension mechanism for variable diameter rotors 失效
标题翻译：可变直径转子的伸缩机构
公开(公告)号：US5642982A
公开(公告)日：1997-07-01
申请号：US570579
申请日：1995-12-11
申请人： David G. Matuska , Edward W. Gronenthal
发明人： David G. Matuska , Edward W. Gronenthal
IPC分类号： B64C11/00 , B64C29/00 , F04D29/18
CPC分类号： B64C29/0033 , B64C11/003
摘要： A retraction/extension mechanism (70) for a Variable Diameter Rotor system (10), the Variable Diameter Rotor system (10) having a plurality of rotor blade assemblies (16) mounted to and rotating with a rotor hub assembly (18) about an axis of rotation (20), each rotor blade assembly (16) having inboard and outboard blade sections (24, 22) wherein the outboard blade section (22) telescopically mounts to the inboard blade section (24). The retraction/extension mechanism (70) includes a reeling assembly (80) disposed in combination with the outboard blade section (22) of each rotor blade assembly (16) and an epicyclic gear train (100) disposed in combination 7ith the rotor hub assembly (18) and the reeling assembly (80). The epicylic gea2 train is, furthermore, operative for driving the reeling assembly (80) so as to effect telescopic transition of the outboard blade sections (22) with respect to the inboard blade sections (24).
摘要翻译：一种用于可变直径转子系统（10）的缩回/延伸机构（70），所述可变直径转子系统（10）具有多个转子叶片组件（16），所述多个转子叶片组件（16）安装到转子轮毂组件旋转轴线（20），每个转子叶片组件（16）具有内侧和外侧叶片部分（24,22），其中外侧叶片部分（22）可伸缩地安装到内侧叶片部分（24）。缩回/延伸机构（70）包括与每个转子叶片组件（16）的外侧叶片部分（22）组合设置的卷取组件（80）和一个行星齿轮系（100），其组合在转子轮毂组件（18）和卷取组件（80）。此外，上述的epaylic gea2列可操作用于驱动卷取组件（80），以便实现外侧叶片部分（22）相对于内侧叶片部分（24）的伸缩转变。

3. 发明授权

US5620304A Rotor system having alternating length rotor blades and positioning means therefor for reducing blade-vortex interaction (BVI) noise 失效
公开(公告)号：US5620304A
公开(公告)日：1997-04-15
申请号：US570581
申请日：1995-12-11
申请人： David G. Matsuka , Edward W. Gronenthal , Robert C. Moffitt
发明人： David G. Matsuka , Edward W. Gronenthal , Robert C. Moffitt
IPC分类号： B64C11/28
CPC分类号： B64C11/28
摘要： A Variable Diameter Rotor (VDR) system (4) having telescoping odd and even blade assemblies (O.sub.b, E.sub.b) wherein the odd blade assemblies define a radial length R.sub.O and the even blade assemblies define a radial length R.sub.E. Each blade assembly (O.sub.b, E.sub.b) defines an internal chamber (64) for accepting a positioning mechanism (70) operative to effect telescopic translation of the blade assemblies (O.sub.b, E.sub.b) such that the radial length R.sub.E of the even blade assemblies (E.sub.b) is equal to the radial length R.sub.O of the odd blade assemblies (O.sub.b) in a first operating mode, and such that the radial length R.sub.E is between about 70% to about 95% of the length R.sub.O in a second operating mode. The positioning mechanism (70) includes a centrifugal restraint assembly (80) disposed within each internal chamber (64), a stop surface (64s) formed internally of each internal chamber (64), and an actuation mechanism (90) operative for transpositioning the centrifugal restraint assemblies (80) within the internal chambers (64) such that, in one operating mode, the centrifugal restraint assemblies (80)are disposed in abutting engagement with the stop surfaces (64s) and, in another operating mode, the actuation mechanism (90) is disposed in abutting engagement with the centrifugal restraint assemblies (80) of at least one of the blade assemblies (O.sub.b, E.sub.b). The actuation mechanism includes a reeling assembly (110) having a cylindrical drum (112) disposed internally of the rotor assembly (8), end fixities (114) disposed internally of the chambers (64) and operative for engaging and disengaging the centrifugal restraint assembly (80), straps (116) for mechanically coupling the end fixities (114) to the cylindrical drum (112), and a drive mechanism (120) for effecting rotation of the cylindrical drum (112).

4. 发明授权

US07243881B2 Multi-function trailing edge devices and associated methods 有权
标题翻译：多功能后缘设备及相关方法
公开(公告)号：US07243881B2
公开(公告)日：2007-07-17
申请号：US10860438
申请日：2004-06-03
申请人： Seiya Sakurai , Stephen J. Fox , Kevin W. Beyer , Douglas S. Lacy , Paul L. Johnson , Stephen L. Wells , Jack S. Noble , Paul T. Meredith , Neal V. Huynh , Russell R. Christianson , Paul M. Vijgen , Michael F. Fitzpatrick , Clayton A. Prow , Edward W. Gronenthal
发明人： Seiya Sakurai , Stephen J. Fox , Kevin W. Beyer , Douglas S. Lacy , Paul L. Johnson , Stephen L. Wells , Jack S. Noble , Paul T. Meredith , Neal V. Huynh , Russell R. Christianson , Paul M. Vijgen , Michael F. Fitzpatrick , Clayton A. Prow , Edward W. Gronenthal
IPC分类号： B64C9/22
CPC分类号： B64C9/20 , B64C9/16 , Y02T50/32 , Y02T50/44
摘要： Trailing edge devices configured to carry out multiple functions, and associated methods of use and manufacture are disclosed. An external fluid flow body (e.g., an airfoil) configured in accordance with an embodiment of the invention includes a first portion and a second portion, at least a part of the second portion being positioned aft of the first portion, with the second portion being movable relative to the first portion between a neutral position, a plurality of upward positions, and a plurality of downward positions. A guide structure can be coupled between the first and second portions, and an actuator can be operatively coupled between the first and second portions to move the second portion relative to the first portion. In one embodiment, a flexible surface can track the motion of the second portion and can expose a gap at some positions. In another embodiment, a controller can be coupled to the actuator and can be configured to direct the actuator to move the second portion to a high lift setting, a high drag setting, a roll setting, and a trim setting. In yet another embodiment, trailing edge devices on an airfoil can have scaled, mechanically similar guide structures.
摘要翻译：被配置为执行多个功能的后端设备以及相关联的使用和制造方法被公开。根据本发明的实施例配置的外部流体流动体（例如，翼型）包括第一部分和第二部分，第二部分的至少一部分位于第一部分的后部，第二部分是相对于第一部分在中立位置，多个向上位置和多个向下位置之间移动。引导结构可以联接在第一和第二部分之间，并且致动器可以可操作地联接在第一和第二部分之间，以相对于第一部分移动第二部分。在一个实施例中，柔性表面可以跟踪第二部分的运动并且可以在某些位置暴露间隙。在另一个实施例中，控制器可以联接到致动器，并且可以被配置为引导致动器将第二部分移动到高提升设置，高阻力设置，滚转设置和修剪设置。在另一个实施例中，翼型件上的后缘装置可以具有缩放的机械上相似的导向结构。

5. 发明授权

US06857598B2 Integrated high-speed aircraft and associated methods of manufacture 有权
标题翻译：集成高速飞机及相关制造方法
公开(公告)号：US06857598B2
公开(公告)日：2005-02-22
申请号：US10683671
申请日：2003-10-09
申请人： Eric E. Adamson , Paul W. Dees , Edward W. Gronenthal , Walter H. Howard, Jr. , Chester P. Nelson , Mithra M. Sankrithi , Gerhard E. Seidel , V. Kenneth Stuhr
发明人： Eric E. Adamson , Paul W. Dees , Edward W. Gronenthal , Walter H. Howard, Jr. , Chester P. Nelson , Mithra M. Sankrithi , Gerhard E. Seidel , V. Kenneth Stuhr
IPC分类号： B64C1/00 , B64C1/26 , B64C25/04 , B64C25/10 , B64C30/00 , B64D9/00 , B64D11/00 , B64D27/18 , B64D37/04 , B64D27/16
CPC分类号： B64C1/0009 , B64C1/26 , B64C25/04 , B64C25/10 , B64C30/00 , B64C2001/0027 , B64C2001/0045 , B64D9/003 , B64D11/00 , B64D27/18 , B64D37/04 , Y02T50/12 , Y02T50/44 , Y02T50/46
摘要： Integrated high-speed aircraft, such as high-speed transport aircraft, and associated methods of manufacture. In one embodiment, a high-speed transport aircraft includes a fuselage having a first fuselage portion and a second fuselage portion positioned aft of the first fuselage portion. The first fuselage portion can have a first cross-sectional area and the second fuselage portion can have a second cross-sectional area that is less than the first cross-sectional area. The high-speed transport aircraft can further include a wing and a propulsion system. The wing can extend outwardly from the fuselage at least proximate to the second fuselage portion and can include a leading edge region and a trailing edge region. The propulsion system can include an engine nacelle fixedly attached to the wing and laterally aligned with the second fuselage portion. In one aspect of this embodiment, the engine nacelle can include an air inlet positioned aft of the leading edge region of the wing and an exhaust gas outlet positioned aft of the trailing edge region of the wing.
摘要翻译：集成高速飞机，如高速运输飞机及相关制造方法。在一个实施例中，高速运输飞机包括具有第一机身部分的机身和位于第一机身部分后方的第二机身部分。第一机身部分可以具有第一横截面积，并且第二机身部分可以具有小于第一横截面积的第二横截面面积。高速运输机可以进一步包括机翼和推进系统。机翼可以从机身至少靠近第二机身部分向外延伸，并且可以包括前缘区域和后缘区域。推进系统可以包括固定地附接到机翼并与第二机身部分横向对齐的发动机机舱。在该实施例的一个方面，发动机舱可以包括位于翼的前缘区域后方的空气入口和位于翼的后缘区域后方的排气出口。

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