公开(公告)号：US4629644A

公开(公告)日：1986-12-16

申请号：US781605

申请日：1985-09-30

申请人： David G. Matuska

发明人： David G. Matuska

IPC分类号： B29C70/16 ,  B29C53/56 ,  B29C53/60 ,  B29C70/06 ,  B29C70/34 ,  B29D99/00 ,  B29K105/08 ,  B29L31/08 ,  B32B1/00 ,  B64C27/32 ,  B64C27/48 ,  F16D3/72 ,  B64C27/52

CPC分类号： B29C53/564 ,  B29C53/602 ,  B29C70/347 ,  B64C27/32 ,  B29L2031/08 ,  Y10S428/902 ,  Y10T428/218 ,  Y10T428/24322 ,  Y10T428/30 ,  Y10T428/3162

摘要： A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm, a rim, rim reinforcement fibers and at least one fiber reinforcement ring. The diaphragm has a central attachment means for receiving a shaft and the rim has an attachment means. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a connecting rim, rim reinforcement fibers and at least one fiber reinforcing ring for each diaphragm side. The sides have centrally located attachment means. The structure comprises a resin matrix, fibers wound substantially tangentially to the central attachment means with sufficient tension in a multiple circuit pattern to form the structure, fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure and fibers wound substantially circularly to form rings for reinforcing the diaphragm. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. In addition, the structure does not buckle under heavy torque loading. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

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。

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).

公开(公告)号：US4666753A

公开(公告)日：1987-05-19

申请号：US734982

申请日：1985-05-16

申请人： David G. Matuska ,  Evan A. Fradenburgh

发明人： David G. Matuska ,  Evan A. Fradenburgh

IPC分类号： F16D3/74 ,  B29C53/56 ,  B29C70/06 ,  B29C70/16 ,  B29D99/00 ,  B29L31/00 ,  B64C27/35 ,  B64C27/41 ,  B64C27/48 ,  F16D3/72 ,  B64C27/52

CPC分类号： B29C53/564 ,  B64C27/41 ,  F16D3/725 ,  Y10S428/902 ,  Y10T428/24322 ,  Y10T428/30 ,  Y10T428/3162

摘要： A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm and a rim. The diaphragm has a central hole therethrough for receiving a shaft and the rim has an inward turning flange for attachment. The diaphragm has an attachment means surrounding the central hole. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a rim. The sides have concentric central holes therethrough and attachment means surrounding the holes. The structure comprises a resin matrix, fibers wound substantially tangentially to the central hole with sufficient tension in a multiple circuit pattern to form the structure, and fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

摘要翻译： 长丝缠绕纤维增强树脂基复合结构。 该结构特别适合用作旋转翼飞行器枢轴中的扭矩驱动隔膜。 该结构包括基本平坦的隔膜和轮辋。 隔膜具有穿过其中的中心孔，用于容纳轴，并且边缘具有用于附接的向内转动凸缘。 隔膜具有围绕中心孔的附接装置。 该结构的替代实施例是具有带边缘的第一和第二基本上平坦的隔膜侧的中空盘。 这些侧面具有穿过的中心孔和围绕孔的附接装置。 该结构包括树脂基体，基本上与中心孔切线缠绕的纤维，具有多重电路图案中的足够张力以形成结构，并且纤维以基本圆周方式以足够的张力缠绕以加强结构的边缘。 该结构通过在受控固化循环中具有足够的热和温度的模制而固化。 该结构不显示“油罐”，因为当受到变化的温度时，平面膜片或膜片侧面不会从基本平坦的单面模式移位。 当作为扭矩驱动器约束时，结构的弹簧特性保持大致线性，并且在操作期间消除了弯曲和卡通。

公开(公告)号：US07751976B2

公开(公告)日：2010-07-06

申请号：US11213110

申请日：2005-08-26

申请人： David G. Matuska ,  Vineet Sahasrabudhe ,  Donald S. Anttila

发明人： David G. Matuska ,  Vineet Sahasrabudhe ,  Donald S. Anttila

IPC分类号： G01C5/00

CPC分类号： G05D1/0858 ,  G01S13/9303 ,  G01S17/933 ,  G08G5/0021 ,  G08G5/045

摘要： A method of obstacle avoidance for a rotary wing aircraft includes detecting an obstacle proximate to the aircraft and commanding a servo to generate a force to an input control device in a direction that tends to preclude the aircraft from contacting the detected obstacle, the command having lesser authority than a pilot input command.

摘要翻译： 一种用于旋转翼飞机的避障方法包括检测靠近飞行器的障碍物，并且命令伺服器在倾向于阻止飞行器接触检测到的障碍物的方向上向输入控制装置产生力，该命令具有较小的 权限比导频输入命令。

公开(公告)号：USD401898S

公开(公告)日：1998-12-01

申请号：US64119

申请日：1996-12-23

申请人： Timothy F. Lauder ,  David G. Matuska

设计人： Timothy F. Lauder ,  David G. Matuska

公开(公告)号：US5735670A

公开(公告)日：1998-04-07

申请号：US569390

申请日：1995-12-11

申请人： Robert C. Moffitt ,  David G. Matuska ,  Evan A. Fradenburgh

发明人： Robert C. Moffitt ,  David G. Matuska ,  Evan A. Fradenburgh

IPC分类号： B64C11/00 ,  B64C27/46 ,  B64C11/28

CPC分类号： B64C11/003 ,  B64C27/46

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 means (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 means (70) includes a centrifugal restraint assembly (80) disposed within each internal chamber (64) of the rotor blade assemblies (O.sub.b, E.sub.b), a stop surface (64s) formed internally of each internal chamber (64), and an actuation means (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 means (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).

摘要翻译： 具有伸缩奇数和偶数叶片组件（Ob，Eb）的可变直径转子（VDR）系统（4），其中奇数刀片组件限定径向长度RO，并且均匀叶片组件限定径向长度RE。 每个叶片组件（Ob，Eb）限定内腔（64），用于接受定位装置（70），该定位装置（70）可操作以实现叶片组件（Ob，Eb）的伸缩平移，使得均匀叶片组件 ）等于第一操作模式中奇数刀片组件（Ob）的径向长度RO，并且使得径向长度RE在第二操作模式中在长度RO的约70％至约95％之间。 定位装置（70）包括设置在转子叶片组件（Ob，Eb）的每个内室（64）内的离心约束组件（80），在每个内室（64）内部形成的止动表面（64s），以及 驱动装置（90），其可操作用于将离心约束装置（80）在内部腔室（64）内转位，使得在一种操作模式中离心约束装置（80）被设置成与止动表面（64s）邻接接合， 并且在另一操作模式中，致动装置（90）设置成与至少一个叶片组件（Ob，Eb）的离心约束组件（80）邻接接合。

公开(公告)号：US4874292A

公开(公告)日：1989-10-17

申请号：US272967

申请日：1988-11-18

申请人： David G. Matuska ,  Donald L. Ferris

发明人： David G. Matuska ,  Donald L. Ferris

IPC分类号： B64C27/51

CPC分类号： B64C27/51

摘要： A major design consideration in helicopters is that of compensating for ssses on blades resulting from air forces during blade revolutions. Spinning rotor blades are severely stressed. To some degree conventional articulated helicopter rotor hubs overcome vibration difficulties, but high maintenance is a problem. Hingeless helicopter rotor assemblies, generally employing composite materials, were developed to overcome these obstacles. Such hingeless helicopter rotor assemblies usually include a rigid central hub member, and radial flexbeams rigidly attached to the hub member. Flexbeam rotors do not completely eliminate the dynamic instability difficulty. Even using these designs energy must be absorbed by damping means. The shear principle of damping is utilized in this invention.

摘要翻译： 直升机的主要设计考虑是补偿叶片转速期间由空气引起的叶片上的应力。 旋转叶片受到严重压力。 在某种程度上，传统的铰接式直升机转子毂克服了振动的困难，但高维护是一个问题。 通常使用复合材料的无绳直升机转子组件被开发以克服这些障碍。 这种无铰链式直升机转子组件通常包括刚性中心轮毂构件和刚性地附接到轮毂构件的径向挠性梁。 Flexbeam转子不能完全消除动态不稳定性难度。 即使使用这些设计，能量必须被阻尼装置吸收。 在本发明中使用了阻尼的剪切原理。

公开(公告)号：US4695341A

公开(公告)日：1987-09-22

申请号：US869551

申请日：1986-06-02

申请人： David G. Matuska ,  Evan A. Fredenburgh

发明人： David G. Matuska ,  Evan A. Fredenburgh

IPC分类号： B29C53/56 ,  B64C27/41 ,  F16D3/72 ,  B65H81/00

CPC分类号： F16D3/725 ,  B29C53/564 ,  B64C27/41

摘要： A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm and a rim. The diaphragm has a central hole therethrough for receiving a shaft and the rim has an inward turning flange for attachment. The diaphragm has an attachment means surrounding the central hole. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a rim. The sides have concentric central holes therethrough and attachment means surround the holes. The structure comprises a resin matrix, fibers wound substantially tangentially to the central hole with sufficient tension in a multiple circuit pattern to form the structure, and fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

摘要翻译： 长丝缠绕纤维增强树脂基复合结构。 该结构特别适合用作旋转翼飞行器枢轴中的扭矩驱动隔膜。 该结构包括基本平坦的隔膜和轮辋。 隔膜具有穿过其的中心孔用于容纳轴，并且边缘具有用于附接的向内转动凸缘。 隔膜具有围绕中心孔的附接装置。 该结构的替代实施例是具有带边缘的第一和第二基本上平坦的隔膜侧的中空盘。 这些侧面具有穿过其的同心中心孔，围绕孔的附接装置。 该结构包括树脂基体，基本上与中心孔切线缠绕的纤维，多重电路图案中具有足够的张力以形成结构，并且纤维以基本圆周方式以足够的张力缠绕以加强结构的边缘。 该结构通过在受控固化循环中具有足够的热和温度的模制而固化。 该结构不显示“油罐”，因为当受到变化的温度时，平面膜片或膜片侧面不会从基本平坦的单面模式移位。 当作为扭矩驱动器约束时，结构的弹簧特性保持大致线性，并且在操作期间消除了弯曲和卡通。

公开(公告)号：US4695340A

公开(公告)日：1987-09-22

申请号：US869550

申请日：1986-06-02

申请人： David G. Matuska

发明人： David G. Matuska

IPC分类号： B29C53/56 ,  B29C53/60 ,  B29C70/34 ,  B64C27/32 ,  B65H21/00

CPC分类号： B29C70/347 ,  B29C53/564 ,  B29C53/602 ,  B64C27/32 ,  B29L2031/08

摘要： A filament wound fiber reinforced resin matrix composite structure. The structure is particularly adapted for use as a torque drive diaphragm in a rotary wing aircraft hub. The structure comprises a substantially flat diaphragm, a rim, rim reinforcement fibers and at least one fiber reinforcement ring. The diaphragm has a central attachment means for receiving a shaft and the rim has an attachment means. An alternative embodiment of the structure is a hollow disc having first and second substantially flat diaphragm sides with a connecting rim, rim reinforcement fibers and at least one fiber reinforcing ring for each diaphragm side. The sides have centrally located attachment means. The structure comprises a resin matrix, fibers wound substantially tangentially to the central attachment means with sufficient tension in a multiple circuit pattern to form the structure, fibers wound with sufficient tension in an essentially circumferential manner to reinforce the rim of the structure and fibers wound substantially circularly to form rings for reinforcing the diaphragm. The structure is cured by molding with sufficient heat and temperature in a controlled cure cycle. The structure does not exhibit "oil-canning" in that the flat diaphragm or diaphragm sides do not displace from the substantially flat uniplanar mode when subjected to varying temperatures. In addition, the structure does not buckle under heavy torque loading. The spring characteristics of the structure when constrained as a torque drive remain approximately linear and buckling and snap-through are eliminated during operation.

摘要翻译： 长丝缠绕纤维增强树脂基复合结构。 该结构特别适合用作旋转翼飞行器枢轴中的扭矩驱动隔膜。 该结构包括基本平坦的隔膜，边缘，边缘增强纤维和至少一个纤维增强环。 隔膜具有用于接收轴的中心附接装置，并且边缘具有附接装置。 该结构的替代实施例是具有第一和第二基本平坦的隔膜侧面的中空盘，其具有连接边缘，边缘加强纤维和用于每个隔膜侧的至少一个纤维加强环。 侧面具有中心位置的附接手段。 该结构包括树脂基体，基本上与中心连接装置相切地缠绕的纤维，以多重电路图案的足够的张力形成结构，以基本圆周方式缠绕足够的张力的纤维，以加强结构的边缘和基本上缠绕的纤维 圆形地形成用于加强隔膜的环。 该结构通过在受控固化循环中具有足够的热和温度的模制而固化。 该结构不显示“油罐”，因为当受到变化的温度时，平面膜片或膜片侧面不会从基本平坦的单面模式移位。 此外，该结构在重力矩负载下不会弯曲。 当作为扭矩驱动器约束时，结构的弹簧特性保持大致线性，并且在操作期间消除了弯曲和卡通。