公开(公告)号：WO1996006775A1

公开(公告)日：1996-03-07

申请号：PCT/US1995010070

申请日：1995-08-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  REINFELDER, William, C. ,  LEAHY, Kevin, P. ,  JONES, Corey, D. ,  KOVALSKY, David, A.

IPC: B64C27/00

CPC classification number: B64C27/008 ,  G01M1/12

Abstract: The rotor blades of a helicopter are balanced both in the chordal direction and in the spanwise direction in a static balancing assembly. The assembly includes a support surface (4) on which there are four weighing scales (8). The scales (8) are positioned in close proximity with the four corners of the rotor blade (2). The scales (8) provide four cooperating pairs of blade spanwise and chordwise balancing reference data. The scales (8) are operably connected to a microprocessor which is preprogrammed with desired balance data for the blades being tested. Deviations from the desired balance data detected by the scales and the microprocessor are corrected by selectively adding or subtracting weight on the blades at appropriate locations of the surfaces thereof.

Abstract translation: 直升机的转子叶片在静平衡组件中在弦方向和翼展方向上平衡。 组件包括支撑表面（4），其上有四个称重秤（8）。 秤（8）定位成紧邻转子叶片（2）的四个角。 标尺（8）提供了四个协作的叶片翼展和对平衡参考数据对。 秤（8）可操作地连接到微处理器，该微处理器对所测试的刀片的所需平衡数据进行预编程。 通过在其表面的适当位置选择性地增加或减少叶片上的重量来校正由秤和微处理器检测到的期望平衡数据的偏差。

公开(公告)号：WO1996002417A2

公开(公告)日：1996-02-01

申请号：PCT/US1995007935

申请日：1995-06-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  LEAHY, Kevin, Patrick ,  JONES, Corey, D.

IPC: B64C27/473

CPC classification number: B29D99/0028 ,  B29C70/446 ,  B29C70/78 ,  B29C70/86 ,  B29L2031/082 ,  B64C27/473 ,  B64C2027/4736 ,  Y10T29/37 ,  Y10T29/49332 ,  Y10T29/53026 ,  Y10T29/53539 ,  Y10T29/5397

Abstract: Apparatus and methods for fabricating a helicopter main rotor blade (100) include a compaction fixture (10) for assembling and compacting blade subassembly components and a sheath spreading/insertion apparatus (50) for spreading and inserting a leading-edge sheath (120) onto the blade subassembly during the compaction process. The compaction fixture includes a lower assembly (12) having a contoured upper airfoil nest (14) mounted in combination with a support structure and an upper assembly (30) having a pressure bag (32) affixed in sealed combination to a contoured backplate affixed in combination to a structural support truss (36). With the upper and lower assemblies in locked combination, the pressure bag is pressurized to compact the assembled blade subassembly components. The sheath spreading/insertion apparatus (50) includes a movable stanchion (52), upper (60U) and lower (60L) elongate carriage members mounted in synchronized movable combination with the stanchion, and a row of suction cups (66) mounted in combination with each carriage member. A vacuum source (68) is pneumatically interconnected to the suction cups (66) to generate suction forces to cause the leading-edge sheath to be spread apart. Movement of the movable stanchion causes the spread-apart leading-edge sheath to be inserted onto the blade subassembly during compaction thereof.

Abstract translation: 用于制造直升机主转子叶片（100）的装置和方法包括用于组装和压实叶片子组件部件的压实夹具（10）和用于将前缘护套（120）扩展和插入到其中的护套扩展/插入装置（50） 在压实过程中刀片子组件。 压实夹具包括下部组件（12），其具有与支撑结构组合安装的轮廓上部翼型套筒（14）和具有与密封组合固定到轮廓背板上的压力袋（32）的上部组件（30） 组合到结构支撑桁架（36）。 通过将上部和下部组件锁定组合，压力袋被加压以压缩组装的叶片子组件部件。 护套扩展/插入装置（50）包括可移动支柱（52），与支柱同步移动的组合安装的上部（60U）和下部（60L）细长的托架构件，以及一排安装在一起的吸盘（66） 与每个托架成员。 真空源（68）被气动地互连到吸盘（66）以产生吸力，以使前缘护套分开。 活动支柱的运动导致扩展的前缘护套在其压实期间插入到叶片子组件上。

公开(公告)号：WO1996002416A1

公开(公告)日：1996-02-01

申请号：PCT/US1995007813

申请日：1995-06-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SUCIC, Steve ,  JONES, Corey, D.

IPC: B64C27/473

CPC classification number: B64C27/473 ,  B23Q35/102 ,  B64C2027/4736 ,  Y10T29/49332 ,  Y10T83/0341 ,  Y10T83/0363

Abstract: The described embodiment of an edge-of-part (EOP) scribe device (10) is operative to simultaneously scribe trim lines in an oversized, cured leading-edge sheath (120) mounted on a sheath mold assembly (160) so that the scribed, cured leading-edge sheath may be cut along the scribed trim lines to form a prefabricated leading-edge sheath having finished edges for a helicopter main rotor blade (100). Trim line templates (168) having profile edges (170) defining the profiles of the finished edges of the prefabricated leading-edge sheath are affixed to the sheath mold assembly. The EOP scribe device includes a primary carriage assembly (12) having V-groove rollers (14) secured thereto wherein the primary carriage assembly is translatable in a spanwise direction along side rails (166) secured to the sheath mold assembly, handles (16) for mounting and dismounting the EOP scribe (10) device in combination with the sheath mold assembly, opposed pairs of guide rails (18) affixed to the primary carriage assembly, and a secondary carriage assembly (20) mounted in movable combination with each pair of guide rails. Each secondary carriage assembly includes a spring-loaded scribe head (22) mounted in movable combination therewith, a positioning knob (24) secured in rigid combination with the scribe head and operative to allow the scribe head to be moved between a disengaged position for mounting/dismounting of the EOP scribe device and a scribe position for inscribing a trim line in the cured leading-edge sheath, a rigid follower linkage (26) secured to the secondary carriage assembly, and a follower slide roller (26) mounted in rotatable combination with the rigid follower linkage. The spring-loaded scribe head (22) includes a hardened scriber (30) for scribing the trim line and a tolerance roller (32) that interacts with the cured leading-edge sheath during the scribing operation to define the depth of the scribed trim line. With the EOP scribe device mounted in combination with the sheath mold assembly and the spring-loaded scribe heads in the scribe position, each follower slide roller interacts with the respective profiled edge (170). As the primary carriage assembly is subjected to spanwise translation along the sheath mold assembly, dimensional changes in the profiled edges induce vertical displacements in the follower slide rollers, the induced vertical displacements being coupled through the rigid follower linkages to cause corresponding vertical displacements in the secondary carriage assemblies and concomitantly, in the scribe heads. The vertical displacement of the hardened scribers matches the respective profiled edges such that the scribed trim lines correspond to the profiles of the finished edges of the prefabricated leading-edge sheath.

Abstract translation: 部分边缘（EOP）划线装置（10）的所描述的实施例可操作以在安装在护套模具组件（160）上的尺寸过大的固化前缘护套（120）中同时刻划修剪线，使得划线 可以沿着划线的修剪线切割固化的前缘护套，以形成具有用于直升机主转子叶片（100）的成品边缘的预制前缘护套。 具有限定预制前缘护套的成品边缘的轮廓的轮廓边缘（170）的修剪线模板（168）被固定到护套模具组件。 EOP划线装置包括具有固定到其上的V形槽辊（14）的主托架组件（12），其中主支架组件可沿着固定到护套模具组件的侧轨（166）在翼展方向上平移，手柄（16） 用于将EOP划片（10）装置与护套模具组件组合安装和拆卸，固定到主支架组件上的相对的导轨对（18）和与每一对可移动组合安装的辅助滑架组件（20） 导轨。 每个辅助托架组件包括安装成与其可移动组合的弹簧加载划线头（22），定位旋钮（24），其与划线头刚性组合固定并且可操作以允许划线头在分离位置之间移动以用于安装 EOP划片装置的拆卸和用于在固化的前缘护套中刻划修剪线的划线位置，固定到第二托架组件的刚性从动件联动装置（26）和安装成可旋转组合的从动滑动辊（26） 与刚性从动联动。 弹簧加载的划线头（22）包括用于划线修剪线的硬化划线机（30）和在划线操作期间与固化的前缘护套相互作用的公差辊（32），以限定划线的修剪线的深度 。 通过将EOP划片装置与护套模具组件和在划片位置上的弹簧加载划线头组合安装，每个从动滑动辊与相应的成形边缘（170）相互作用。 当主滑架组件沿着护套模具组件进行横向平移时，成型边缘中的尺寸变化引起从动滑动辊中的垂直位移，感应的垂直位移通过刚性从动联轴器联接，从而在次级 支架组件，伴随着，在划痕头。 硬化划线机的垂直位移与相应的成型边缘相匹配，使得划线的修剪线对应于预制的前缘护套的成品边缘的轮廓。

公开(公告)号：WO1996004125A1

公开(公告)日：1996-02-15

申请号：PCT/US1995009106

申请日：1995-07-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  REINFELDER, William, C. ,  KOVALSKY, David, A. ,  JONES, Corey, D.

IPC: B29C70/86

CPC classification number: B29D99/0025 ,  B29C70/44 ,  B29L2031/08 ,  Y10S425/044 ,  Y10T156/1028 ,  Y10T156/103

Abstract: A fiberglass or other material skin is applied to a composite airfoil structure (2) in a mold assembly (22) having a partially compliant caul plate component which defines the shape of the lower surface of the airfoil. The caul plate component includes a first portion (34) which is essentially rigid and which covers the leading edge (16) of the airfoil. The rigid portion of the caul plate component provides improved conformation of the airfoil skin to the leading edge of the airfoil. The caul plate component also includes a compliant portion (36) which covers and defines the shape of the trailing edge of the lower surface of the airfoil. The stiffness of the caul plate component also has a variable stiffness zone (38) which interconnects the rigid and compliant portions thereof. The use of rigid and compliant portions on the caul plate provides for a controlled conformance of the skin to the leading edge of the airfoil, while allowing the skin to accurately conform to the remainder of the airfoil in spite of variations in the dimensions of internal operating components of the airfoil.

Abstract translation: 将玻璃纤维或其它材料表皮施加到具有限定翼型件的下表面的形状的部分柔性挡板部件的模具组件（22）中的复合翼型结构（2）上。 刮板部件包括基本刚性并且覆盖翼型件的前缘（16）的第一部分（34）。 挡板部件的刚性部分提供了翼型皮肤到翼型的前缘的改进构造。 挡板部件还包括覆盖并限定翼型件的下表面的后缘的形状的柔顺部分（36）。 止动板部件的刚度还具有可变刚度区域38，其将刚性部分和柔性部分互连。 在挡板上使用刚性和柔顺部分提供了皮肤对翼型前缘的受控一致性，同时允许皮肤准确地符合翼型的其余部分，尽管内部操作的尺寸有变化 机翼的部件。

公开(公告)号：EP0771283B1

公开(公告)日：1998-09-09

申请号：EP95923998.9

申请日：1995-06-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIC, Steve ,  JONES, Corey, D.

IPC: B64C27/473 ,  B23Q35/10

CPC classification number: B64C27/473 ,  B23Q35/102 ,  B64C2027/4736 ,  Y10T29/49332 ,  Y10T83/0341 ,  Y10T83/0363

Abstract: The described embodiment of an edge-of-part (EOP) scribe device (10) is operative to simultaneously scribe trim lines in an oversized, cured leading-edge sheath (120) mounted on a sheath mold assembly (160) so that the scribed, cured leading-edge sheath may be cut along the scribed trim lines to form a prefabricated leading-edge sheath having finished edges for a helicopter main rotor blade (100). Trim line templates (168) having profile edges (170) defining the profiles of the finished edges of the prefabricated leading-edge sheath are affixed to the sheath mold assembly. The EOP scribe device includes a primary carriage assembly (12) having V-groove rollers (14) secured thereto wherein the primary carriage assembly is translatable in a spanwise direction along side rails (166) secured to the sheath mold assembly, handles (16) for mounting and dismounting the EOP scribe (10) device in combination with the sheath mold assembly, opposed pairs of guide rails (18) affixed to the primary carriage assembly, and a secondary carriage assembly (20) mounted in movable combination with each pair of guide rails. Each secondary carriage assembly includes a spring-loaded scribe head (22) mounted in movable combination therewith, a positioning knob (24) secured in rigid combination with the scribe head and operative to allow the scribe head to be moved between a disengaged position for mounting/dismounting of the EOP scribe device and a scribe position for inscribing a trim line in the cured leading-edge sheath, a rigid follower linkage (26) secured to the secondary carriage assembly, and a follower slide roller (26) mounted in rotatable combination with the rigid follower linkage. The spring-loaded scribe head (22) includes a hardened scriber (30) for scribing the trim line and a tolerance roller (32) that interacts with the cured leading-edge sheath during the scribing operation to define the depth of the scribed trim line. With the EOP scribe device mounted in combination with the sheath mold assembly and the spring-loaded scribe heads in the scribe position, each follower slide roller interacts with the respective profiled edge (170). As the primary carriage assembly is subjected to spanwise translation along the sheath mold assembly, dimensional changes in the profiled edges induce vertical displacements in the follower slide rollers, the induced vertical displacements being coupled through the rigid follower linkages to cause corresponding vertical displacements in the secondary carriage assemblies and concomitantly, in the scribe heads. The vertical displacement of the hardened scribers matches the respective profiled edges such that the scribed trim lines correspond to the profiles of the finished edges of the prefabricated leading-edge sheath.

公开(公告)号：EP0783431A1

公开(公告)日：1997-07-16

申请号：EP95914672.0

申请日：1994-08-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： REINFELDER, William, C. ,  JONES, Corey, D. ,  DEGNAN, William ,  KOVALSKY, David, A. ,  PURSE, Jeffry, C.

IPC: B64C27 ,  B29C70 ,  B29D99 ,  B32B5

CPC classification number: B64C27/473 ,  B29C70/446 ,  B29D99/0025 ,  B29L2031/082 ,  B64C2027/4736 ,  Y10T29/49336

Abstract: A composite spar for a helicopter rotor blade includes upper and lower sidewall regions (40, 42) and forward and aft conic regions (45, 47) wherein the conic regions further define transition and closure subregions (50, 52). Constant width crossplies (62) and unidirectional plies (72) are stacked and arranged to form crossply and unidirectional laminates (60, 70). The crossply laminates (60) form the upper and lower sidewall regions (40, 42) and end portions thereof extend into the forward and aft conic regions (45, 47) to form a staggered distribution of structural joints (68) and slip plane interfaces (66) therein. The crossply laminates are comprised of high modulus fibers which are oriented within a range of +/- 42° to about +/- 38 ° relative to the longitudinal axis (25) of the composite spar (10). The unidirectional laminates (70) form the upper and lower sidewall regions (40, 42) and have end portions (72e) extending into the transition subregions (50). The unidirectional laminates (70) are interposed between the crossply laminates (60) and comprised of a mix of high and low modulus fibers which are oriented substantially parallel to the longitudinal axis (25). Furthermore, plies of reinforcing fabric (80) having low modulus fibers oriented above about 80° relative to the longitudinal axis (25) may be disposed between the unidirectional plies (72) of the unidirectional laminate (70). The composite spar is manufactured in molds.

公开(公告)号：EP0771284B1

公开(公告)日：2000-01-05

申请号：EP95924044.1

申请日：1995-06-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： LEAHY, Kevin, Patrick ,  JONES, Corey, D.

IPC: B64C27/473 ,  B29D31/00 ,  B29C70/44 ,  B29C70/78 ,  B29C70/86

CPC classification number: B29D99/0028 ,  B29C70/446 ,  B29C70/78 ,  B29C70/86 ,  B29L2031/082 ,  B64C27/473 ,  B64C2027/4736 ,  Y10T29/37 ,  Y10T29/49332 ,  Y10T29/53026 ,  Y10T29/53539 ,  Y10T29/5397

Abstract: Apparatus and methods for fabricating a helicopter main rotor blade (100) include a compaction fixture (10) for assembling and compacting blade subassembly components and a sheath spreading/insertion apparatus (50) for spreading and inserting a leading-edge sheath (120) onto the blade subassembly during the compaction process. The compaction fixture includes a lower assembly (12) having a contoured upper airfoil nest (14) mounted in combination with a support structure and an upper assembly (30) having a pressure bag (32) affixed in sealed combination to a contoured backplate affixed in combination to a structural support truss (36). With the upper and lower assemblies in locked combination, the pressure bag is pressurized to compact the assembled blade subassembly components. The sheath spreading/insertion apparatus (50) includes a movable stanchion (52), upper (60U) and lower (60L) elongate carriage members mounted in synchronized movable combination with the stanchion, and a row of suction cups (66) mounted in combination with each carriage member. A vacuum source (68) is pneumatically interconnected to the suction cups (66) to generate suction forces to cause the leading-edge sheath to be spread apart. Movement of the movable stanchion causes the spread-apart leading-edge sheath to be inserted onto the blade subassembly during compaction thereof.

公开(公告)号：EP0777601B1

公开(公告)日：1998-10-28

申请号：EP95933711.4

申请日：1995-08-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： REINFELDER, William, C. ,  LEAHY, Kevin, P. ,  JONES, Corey, D. ,  KOVALSKY, David, A.

IPC: B64C27/00 ,  G01M1/12

CPC classification number: B64C27/008 ,  G01M1/12

公开(公告)号：EP0771284A2

公开(公告)日：1997-05-07

申请号：EP95924044.0

申请日：1995-06-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： LEAHY, Kevin, Patrick ,  JONES, Corey, D.

IPC: B64C27 ,  B29C70 ,  B29D99 ,  B64F5

CPC classification number: B29D99/0028 ,  B29C70/446 ,  B29C70/78 ,  B29C70/86 ,  B29L2031/082 ,  B64C27/473 ,  B64C2027/4736 ,  Y10T29/37 ,  Y10T29/49332 ,  Y10T29/53026 ,  Y10T29/53539 ,  Y10T29/5397

Abstract: Apparatus and methods for fabricating a helicopter main rotor blade (100) include a compaction fixture (10) for assembling and compacting blade subassembly components and a sheath spreading/insertion apparatus (50) for spreading and inserting a leading-edge sheath (120) onto the blade subassembly during the compaction process. The compaction fixture includes a lower assembly (12) having a contoured upper airfoil nest (14) mounted in combination with a support structure and an upper assembly (30) having a pressure bag (32) affixed in sealed combination to a contoured backplate affixed in combination to a structural support truss (36). With the upper and lower assemblies in locked combination, the pressure bag is pressurized to compact the assembled blade subassembly components. The sheath spreading/insertion apparatus (50) includes a movable stanchion (52), upper (60U) and lower (60L) elongate carriage members mounted in synchronized movable combination with the stanchion, and a row of suction cups (66) mounted in combination with each carriage member. A vacuum source (68) is pneumatically interconnected to the suction cups (66) to generate suction forces to cause the leading-edge sheath to be spread apart. Movement of the movable stanchion causes the spread-apart leading-edge sheath to be inserted onto the blade subassembly during compaction thereof.

公开(公告)号：EP0783431B1

公开(公告)日：2000-01-19

申请号：EP95914672.1

申请日：1994-08-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： REINFELDER, William, C. ,  JONES, Corey, D. ,  DEGNAN, William ,  KOVALSKY, David, A. ,  PURSE, Jeffry, C.

IPC: B64C27/473 ,  B29D31/00

CPC classification number: B64C27/473 ,  B29C70/446 ,  B29D99/0025 ,  B29L2031/082 ,  B64C2027/4736 ,  Y10T29/49336

Abstract: A composite spar for a helicopter rotor blade includes upper and lower sidewall regions (40, 42) and forward and aft conic regions (45, 47) wherein the conic regions further define transition and closure subregions (50, 52). Constant width crossplies (62) and unidirectional plies (72) are stacked and arranged to form crossply and unidirectional laminates (60, 70). The crossply laminates (60) form the upper and lower sidewall regions (40, 42) and end portions thereof extend into the forward and aft conic regions (45, 47) to form a staggered distribution of structural joints (68) and slip plane interfaces (66) therein. The crossply laminates are comprised of high modulus fibers which are oriented within a range of +/- 42° to about +/- 38 ° relative to the longitudinal axis (25) of the composite spar (10). The unidirectional laminates (70) form the upper and lower sidewall regions (40, 42) and have end portions (72e) extending into the transition subregions (50). The unidirectional laminates (70) are interposed between the crossply laminates (60) and comprised of a mix of high and low modulus fibers which are oriented substantially parallel to the longitudinal axis (25). Furthermore, plies of reinforcing fabric (80) having low modulus fibers oriented above about 80° relative to the longitudinal axis (25) may be disposed between the unidirectional plies (72) of the unidirectional laminate (70). The composite spar is manufactured in molds.