公开(公告)号：US06205633B1

公开(公告)日：2001-03-27

申请号：US09322355

申请日：1999-05-28

Applicant: David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

Inventor： David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

IPC: B21K2116

CPC classification number: F16D55/36 ,  F16D65/0006 ,  F16D65/126 ,  F16D65/40 ,  F16D2055/0058 ,  F16D2055/0091 ,  F16D2200/0004 ,  F16D2200/0052 ,  Y10T29/49716 ,  Y10T29/49815 ,  Y10T29/49826

Abstract: A convertible aircraft brake assembly (10, 60, 77, 78, 83, 85, 96, 120, 130) designed as original equipment to have heat sinks comprising a steel heat sink (20, 70, 80, 90, 91, 100, 110, 122) aircraft brake assembly and a carbon—carbon composite heat sink (40) aircraft brake assembly. When the aircraft brake assembly is converted from one type of heat sink to the other, the conversion is accomplished with minimal changes in component parts. The conversion can be accomplished without any changes in the piston housing (14), torque tube (12), and wheel (30) because the heat sinks include therein respective components which enable each heat sink to be utilized with the commonly used piston housing (14), torque tube (12), and wheel (30).

Abstract translation: 设计为原始设备的敞篷式飞机制动器组件（10,60,77,78,83,85,96,120,130）具有散热器，所述散热器包括钢散热片（20,70,80,90,91,100,130， 飞机制动组件和碳 - 碳复合散热器（40）飞机制动组件。 当飞机制动组件从一种类型的散热器转换到另一种类型的散热器时，转换是通过零部件的最小变化来实现的。 转换可以在活塞壳体（14），扭矩管（12）和轮子（30）中没有任何变化的情况下实现，因为散热片包括其中各个部件，其使每个散热器能够与常用的活塞壳体一起使用 14），扭矩管（12）和轮（30）。

公开(公告)号：US06327765B2

公开(公告)日：2001-12-11

申请号：US09769790

申请日：2001-01-25

Applicant: David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

Inventor： David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

IPC: B21K2116

CPC classification number: F16D55/36 ,  F16D65/0006 ,  F16D65/126 ,  F16D65/40 ,  F16D2055/0058 ,  F16D2055/0091 ,  F16D2200/0004 ,  F16D2200/0052 ,  Y10T29/49716 ,  Y10T29/49815 ,  Y10T29/49826

Abstract: A convertible aircraft brake assembly (10, 60, 77, 78, 83, 85, 96, 120, 130) designed as original equipment to have heat sinks comprising a steel heat sink (20, 70, 80, 90, 91, 100, 110, 122) aircraft brake assembly and a carbon-carbon composite heat sink (40) aircraft brake assembly. When the aircraft brake assembly is converted from one type of heat sink to the other, the conversion is accomplished with minimal changes in component parts. The conversion can be accomplished without any changes in the piston housing (14), torque tube (12), and wheel (30) because the heat sinks include therein respective components which enable each heat sink to be utilized with the commonly used piston housing (14), torque tube (12), and wheel (30).

公开(公告)号：USRE36622E

公开(公告)日：2000-03-21

申请号：US743102

申请日：1996-11-04

Applicant: Brian G. Harker

Inventor： Brian G. Harker

IPC: F16B13/00 ,  F16B13/04 ,  F16B13/12 ,  F16B21/08

CPC classification number: F16B13/04 ,  F16B13/002 ,  F16B13/124 ,  F16B21/08 ,  Y10T403/4651

Abstract: A drive-in expansion fastener is provided having a generally cylindrical, hollow body with a tapered end formed from an angular truncation of the body. The body is reinforced by at least one longitudinal rib so as to permit drive-in penetration from the tapered end even if the fastener is formed from plastic materials. The fastener is retained within the wall by at least one pair of hinged flanges which expand .Iadd.or move .Iaddend.circumferentially .Iadd.apart .Iaddend.in response to the threaded insertion of an ordinary screw within the hollow portion of the body. That screw engages an inclined surface within the body to cam the flanges outwardly. The flanges engage the back surface of the wall while a longitudinally .[.slit portion.]. .Iadd.split length .Iaddend.of the body expands within the hole created by drive-in penetration.

Abstract translation: 提供了一种推入式膨胀紧固件，其具有大致圆柱形的中空本体，其具有由主体的角度截断形成的锥形端。 身体通过至少一个纵向肋条加强，以便即使紧固件由塑料材料形成，也允许从锥形端部进入内部。 紧固件通过至少一对铰链凸缘保持在壁内，所述铰接凸缘响应于普通螺钉在主体的中空部分中的螺纹插入而沿周向延伸或移动。 该螺钉与主体内的倾斜表面接合以使凸缘向外凸轮。 凸缘接合壁的后表面，而主体的纵向（狭缝部分）分割长度在通过穿透穿透产生的孔内膨胀。

公开(公告)号：US5926932A

公开(公告)日：1999-07-27

申请号：US870923

申请日：1997-06-06

Applicant: David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

Inventor： David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

IPC: F16D55/40 ,  F16D55/00 ,  F16D55/36 ,  F16D65/00 ,  F16D65/12 ,  F16D65/40 ,  F16D65/84 ,  F16D65/847 ,  B21K21/16 ,  B60T1/06

CPC classification number: F16D55/36 ,  F16D65/0006 ,  F16D65/40 ,  F16D2055/0058 ,  F16D2055/0091 ,  F16D2200/0004 ,  F16D2200/0052 ,  F16D65/126 ,  Y10T29/49716 ,  Y10T29/49815 ,  Y10T29/49826

Abstract: A convertible aircraft brake assembly (10, 60, 77, 78, 83, 85, 96, 120, 130) designed as original equipment to have heat sinks comprising a steel heat sink (20, 70, 80, 90, 91, 100, 110, 122) aircraft brake assembly and a carbon--carbon composite heat sink (40) aircraft brake assembly. When the aircraft brake assembly is converted from one type of heat sink to the other, the conversion is accomplished with minimal changes in component parts. The conversion can be accomplished without any changes in the piston housing (14), torque tube (12), and wheel (30) because the heat sinks include therein respective components which enable each heat sink to be utilized with the commonly used piston housing (14), torque tube (12), and wheel (30).

Abstract translation: 设计为原始设备的敞篷式飞机制动器组件（10,60,77,78,83,85,96,120,130）具有散热器，所述散热器包括钢散热片（20,70,80,90,91,100,130， 飞机制动组件和碳 - 碳复合散热器（40）飞机制动组件。 当飞机制动组件从一种类型的散热器转换到另一种类型的散热器时，转换是通过零部件的最小变化来实现的。 转换可以在活塞壳体（14），扭矩管（12）和轮子（30）中没有任何变化的情况下实现，因为散热片包括其中各个部件，其使每个散热器能够与常用的活塞壳体一起使用 14），扭矩管（12）和轮（30）。

公开(公告)号：US06286634B1

公开(公告)日：2001-09-11

申请号：US09769895

申请日：2001-01-25

Applicant: David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

Inventor： David A. Niespodziany ,  Stanley W. May ,  Esaw Harris ,  Andrew S. Haynes ,  Joseph M. Patko ,  Brian G. Harker

IPC: F16D5536

Abstract: A convertible aircraft brake assembly (10, 60, 77, 78, 83, 85, 96, 120, 130) designed as original equipment to have heat sinks comprising a steel heat sink (20, 70, 80, 90, 91, 100, 110, 122) aircraft brake assembly and a carbon-carbon composite heat sink (40) aircraft brake assembly. When the aircraft brake assembly is converted from one type of heat sink to the other, the conversion is accomplished with minimal changes in component parts. The conversion can be accomplished without any changes in the piston housing (14), torque tube (12), and wheel (30) because the heat sinks include therein respective components which enable each heat sink to be utilized with the commonly used piston housing (14), torque tube (12), and wheel (30).

公开(公告)号：US5489178A

公开(公告)日：1996-02-06

申请号：US163288

申请日：1993-12-08

Applicant: Brian G. Harker

Inventor： Brian G. Harker

IPC: F16B19/00 ,  F16B15/00 ,  F16B15/08

CPC classification number: F16B19/004

Abstract: An anchor bolt is provided having a shank which is retained within a recess via peak to peak reaction forces rather than a plurality of peak to base arrangements. This is accomplished through the use of one or more continuous "S" bends or undulations intermediate the shank ends. The "S" bends each create two peaks which extend outwardly from the shank surface with a continuous curve therebetween. That curve includes an inflection point, preferably on the longitudinal axis of the shank, but the slope of the curve at the inflection point is not parallel to that longitudinal axis. Thus, when the shank is inserted within the recess compressive pressure applied to one such peak is directly opposed by such forces applied to the other peak. These peaks can be disposed on opposite sides of the shank or, for example, disposed in a helical or other such pattern about three or more sides of the shank. Serration and/or an abrasive surface can also be provided on the shank to increase retention.

Abstract translation: 提供了一种锚定螺栓，其具有通过峰到峰反作用力而不是多个峰到底布置而保持在凹部内的柄。 这是通过在柄端部之间使用一个或多个连续的“S”弯曲或起伏来实现的。 “S”形弯曲形成两个从柄表面向外延伸的峰，其间具有连续的曲线。 该曲线包括优选地在柄的纵向轴线上的拐点，但是拐点处的曲线的斜率不平行于该纵向轴线。 因此，当柄部插入凹部内时，施加到一个这样的峰的压缩压力直接与施加到另一个峰的这种力相反。 这些峰可以设置在柄的相对侧上，或者例如以螺钉或其它这样的图案设置在柄的三个或更多个侧面上。 锯齿和/或研磨表面也可以设置在柄上以增加保持力。

公开(公告)号：US5476128A

公开(公告)日：1995-12-19

申请号：US133723

申请日：1993-10-07

Applicant: Richard B. Jankowski ,  Brian G. Harker

Inventor： Richard B. Jankowski ,  Brian G. Harker

IPC: B60B25/04 ,  B60B25/14 ,  B64C25/36

CPC classification number: B60B25/14 ,  Y10S152/10

Abstract: A wheel rim assembly (10) includes a first bead flange, and a separable second bead flange (16), the separable second bead flange (16) maintained on a wheel rim (12) of the wheel rim assembly (10) by a retaining ring assembly (20). The retaining ring assembly (20) includes an outboard portion (22) which is partially disposed within an axial opening (18) between the second bead flange (16) and wheel rim (12). The second bead flange (16) and the wheel rim (12) each include an oppositely disposed complementary shaped lobe groove (13, 17) communicating with the axial opening (18). Disposed within the axial opening (18) is a flexible composite corrosion seal (30) comprising a generally rectangularly shaped central flexible member (32) joined with a radially extending flexible base member (35) having a plurality of axially extending protrusions (40) and oppositely disposed, spaced apart flexible lobe members (38, 39) each received within a respective lobe groove (13, 17). The seal (30) is flexible and when installed the lobe members (38, 39) extend radially outwardly to be received within the lobe grooves (13, 17) such that the seal (30) is captured within the axial opening (18) and prevents contaminants from entering into an area (50) between the second bead flange (16) and wheel rim (12) wherein the retaining ring assembly (20) is housed.

Abstract translation: 轮辋组件（10）包括第一胎圈凸缘和可分离的第二胎圈凸缘（16），所述可分离的第二胎圈凸缘（16）通过保持件保持在所述轮辋组件（10）的轮辋（12）上 环组件（20）。 保持环组件（20）包括外侧部分（22），其部分地设置在第二胎圈凸缘（16）和轮缘（12）之间的轴向开口（18）内。 第二胎圈凸缘（16）和轮辋（12）各自包括与轴向开口（18）连通的相对设置的互补形状的凸缘槽（13,17）。 在轴向开口（18）内设置有柔性复合腐蚀密封（30），其包括与径向延伸的柔性基部构件（35）连接的大致矩形的中心柔性构件（32），所述柔性基部构件具有多个轴向延伸的突出部（40）和 相对设置的间隔开的柔性叶片构件（38,39）各自容纳在相应的波纹槽（13,17）内。 密封件（30）是柔性的，并且当安装时，凸角构件（38,39）径向向外延伸以容纳在凸起槽（13,17）内，使得密封件（30）被捕获在轴向开口（18）内，并且 防止污染物进入第二胎圈凸缘（16）和容纳保持环组件（20）的轮缘（12）之间的区域（50）。

公开(公告)号：US5437352A

公开(公告)日：1995-08-01

申请号：US86214

申请日：1993-07-01

Applicant: Brian G. Harker

Inventor： Brian G. Harker

IPC: F16D55/00 ,  F16D55/36

CPC classification number: F16D55/36 ,  F16D2055/0058

Abstract: The aircraft brake torque transfer assembly comprises an aircraft axle (10) having at one axial location an axle flange (18) which includes a plurality of radially extending slots (19, 119) about the circumference thereof, and at an opposite axial location a nut assembly (14) which engages the inner cone of a tapered roller bearing assembly (15) for an associated aircraft wheel (20). The aircraft wheel (20) engages another tapered roller bearing assembly (17) maintains in axial position a bushing assembly (21) and a foot (25) of a torque tube (24) which abuts against the axle flange (18). The aircraft brake (30) includes a piston housing (35) attached to the torque tube (24), and the torque tube (24) includes a plurality of openings (27) receiving key members (60) bolted to the torque tube (24). The key members (60) extend axially to be received in the respective slots (19) of the axle flange (18). The nut assembly (14) holds the wheel (20) and a bearing assembly mechanism (15, 17, 21) axially in place against the torque tube (24) which abuts the axle flange (18) so that the key member (60) transfers braking torque from the torque tube (24) to the axle flange (18) during brake operation. Alternatively, the key member (160) may comprise an integral key part (162) extending axially from the foot (25) of the torque tube (24) and received within a respective slot (119) in the axle flange (18) . The key members (60, 160) may be attached to or integral with the axle flange (18) and be received in complementary shaped openings in the torque tube (24).

Abstract translation: 飞机制动扭矩传递组件包括飞行器轴（10），其在一个轴向位置处具有轴凸缘（18），轴凸缘（18）围绕其圆周包括多个径向延伸的狭槽（19,119），并且在相对的轴向位置处具有螺母 组件（14），其接合用于相关飞行器轮（20）的锥形滚子轴承组件（15）的内锥。 飞机轮（20）接合另一个圆锥滚子轴承组件（17），其保持轴向位置，与轴凸缘（18）抵接的扭矩管（24）的衬套组件（21）和脚部（25）。 飞行器制动器（30）包括附接到扭矩管（24）的活塞壳体（35），并且扭矩管（24）包括多个开口（27），其接收螺栓连接到扭矩管（24）的键构件 ）。 键构件（60）轴向延伸以容纳在轴凸缘（18）的相应狭槽（19）中。 螺母组件（14）将轴（20）和轴承组件机构（15,17,21）轴向固定在抵靠轴凸缘（18）的扭矩管（24）上，使得键构件（60） 在制动操作期间将制动力矩从转矩管（24）传递到轴凸缘（18）。 或者，键构件（160）可以包括从扭矩管（24）的脚部（25）轴向延伸并被接收在轴法兰（18）中的相应狭槽（119）内的整体式键部件（162）。 键构件（60,160）可以与轴凸缘（18）连接或一体地并被接收在扭矩管（24）中的互补形状的开口中。

公开(公告)号：US5147166A

公开(公告)日：1992-09-15

申请号：US601308

申请日：1990-10-22

Applicant: Brian G. Harker

Inventor： Brian G. Harker

IPC: F16B13/00 ,  F16B13/06 ,  F16B13/08 ,  F16B13/13

CPC classification number: F16B13/0808 ,  F16B13/001 ,  F16B13/003 ,  F16B13/061

Abstract: An expansion-type wall anchor having a generally hollow body, a nut element, at least one, and preferably two, retention elements and an actuating element. The retention elements are pivotally connected to the nut element and transition from an orientation substantially parallel to the body to an extended position substantially perpendicular to the body once positioned behind a wall in a rearward cavity. At the end of the body opposite the nut element, the body includes an anchor head which is of greater dimension than the remainder of the hollow body. The anchor head is positioned generally transverse to the longitudinal axis of the body and secures the body to the exterior surface of the wall. The actuating element is positioned in an opening in the anchor head and extends within the length of the body to engage the nut element. Flanges extending from the anchor head preclude rotation of the anchor once it is embedded in the exterior surface of the wall. In some preferred embodiments, rotation of the actuating element creates a force which is exerted on deformable legs to cause the retention elements to transition from an orientation substantially parallel to the body to an extended position substantially perpendicular to the body. Continued rotation of the actuating element draws the retention elements into contact with the interior surface of the wall. Once the body is in place, the actuating element can be removed and the anchor body will remain in place.

Abstract translation: 一种具有大致中空体的膨胀型壁锚固件，螺母元件，至少一个，优选两个保持元件和致动元件。 保持元件枢转地连接到螺母元件并且从基本上平行于主体的取向转移到基本上垂直于身体的延伸位置，其一旦位于后腔中的壁后面。 在与螺母元件相对的本体的端部处，主体包括具有比中空体的其余部分更大的尺寸的锚头。 锚头通常横向于主体的纵向轴线定位，并将主体固定到壁的外表面。 致动元件定位在锚头中的开口中并且在主体的长度内延伸以接合螺母元件。 从锚头延伸的法兰一旦嵌入壁的外表面就排除锚固件的旋转。 在一些优选实施例中，致动元件的旋转产生施加在可变形腿上的力，以使保持元件从基本上平行于本体的取向转变到基本上垂直于主体的延伸位置。 致动元件的继续旋转使保持元件与壁的内表面接触。 一旦本体就位，致动元件就可以被移除并且锚固体将保持在适当的位置。

公开(公告)号：US5402865A

公开(公告)日：1995-04-04

申请号：US86213

申请日：1993-07-01

Applicant: Brian G. Harker

Inventor： Brian G. Harker

IPC: B60T1/06 ,  F16D55/00 ,  F16D55/40 ,  F16D55/36

CPC classification number: B60T1/065 ,  F16D55/40 ,  F16D2055/0058

Abstract: The aircraft brake retention mechanism (40) comprises a retractable mechanism (41) having an enlarged circular head (42) , and a threaded shaft (43) received threadedly in an end part (50) biased by a resilient mechanism (60). The head (42), shaft (43), end part (50) and resilient mechanism (60) are received within a radial opening (33) of a piston housing (30), with the end part (50) extending through the radial opening (33) and into abutting engagement with a flange (13A) of the axle (13) . The piston housing (30) is connected fixedly with a torque tube (20) so that the piston housing (30)/torque tube (20) and associated brake discs (34, 36) are retained axially by the axle flange (13A) which is captured axially between the end part (50) and torque tube (20) . The retractable mechanism (41) may be retracted manually and rotated to engage a surface (37A) of the piston housing (30) and be retained in the; retracted position, so that the brake assembly (10) may be disengaged from the axle (13).

Abstract translation: 飞行器制动器保持机构（40）包括具有扩大的圆形头部（42）的可伸缩机构（41）和螺纹轴（43），螺纹轴（43）被螺纹接纳在由弹性机构（60）偏置的端部（50）中。 头部（42），轴（43），端部（50）和弹性机构（60）被容纳在活塞壳体（30）的径向开口（33）内，端部（50）延伸穿过径向 开口（33）并与所述轴（13）的凸缘（13A）邻接。 活塞壳体（30）固定地连接有扭矩管（20），使得活塞壳体（30）/扭矩管（20）和相关联的制动盘（34,36）由轴凸缘（13A）沿轴向保持， 在端部（50）和扭矩管（20）之间轴向地被捕获。 可缩回机构（41）可以手动缩回并旋转以与活塞壳体（30）的表面（37A）接合并保持在活塞壳体（30）中。 缩回位置，使得制动组件（10）可以与轴（13）脱离。