Apparatus for installing a leading-edge sheath onto a helicopter main rotor blade subassembly

• US 5,862,576 A
• Filed: 04/16/1997
• Issued: 01/26/1999
• Est. Priority Date: 04/16/1997
• Status: Expired due to Term

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Kovalsky, David A., Leahy, Kevin P., Jones, Corey D.
• Primary Examiner(s): Cuda, Irene
• Application Number:
  US08/838,214
• Time in Patent Office: 650 Days
• Field of Search: 29/23.51, 29/889.6, 29/889.61, 29/822, 29/823, 29/824, 29/706, 29/707, 29/700, 100/211, 100/269.06, 100/269.03
• US Class Current: 29/23.51
• CPC Class Codes: B29D 99/0028 hollow blades
• CPC Class Codes: B29L 2031/082 Blades, e.g. for helicopters
• CPC Class Codes: B64F 5/10 Manufacturing or assembling aircraft, e.g. jigs therefor
• CPC Class Codes: Y10T 29/37 Impeller making apparatus
• CPC Class Codes: Y10T 29/49332 Propeller making
• CPC Class Codes: Y10T 29/53026 with randomly actuated stopping or disabling means
• CPC Class Codes: Y10T 29/53539 including work conveyor

Abstract

An apparatus for installing a leading-edge sheath onto a helicopter main rotor blade subassembly, including a lower assembly having a leading-edge sheath contour nest configured for supporting the leading-edge sheath, opposed carriage members connected to a base, wherein each of the opposed carriage members supports a plurality of suction cups and is capable of synchronized translational movement relative to the leading-edge sheath contour nest between an engaged position wherein the plurality of suction cups are in abutting engagement with the leading-edge sheath, and a disengaged position where the plurality of suction cups are disengaged from the leading-edge sheath. A vacuum system is connected in fluid communication with the plurality of suction cups and is capable of providing vacuum pressure to the plurality of suction cups, whereby the vacuum pressure generates suction forces between the plurality of suction cups and the leading-edge sheath when the opposed carriage members are in the engaged position. An upper assembly is disposed in combination with the lower assembly, and comprises a plurality of stanchions connected to the base of the lower assembly, and a contour clamp connected to each of the stanchions capable of translational movement relative to the leading-edge sheath contour nest. The contour clamps are configured for supporting the helicopter main rotor blade subassembly and function to facilitate insertion of the helicopter main rotor blade subassembly into the leading-edge sheath.

Claims

1. An apparatus for installing a leading-edge sheath onto a helicopter main rotor blade subassembly, said apparatus comprising:

(a) a lower assembly comprising

a base,

a leading-edge sheath contour nest connected to said base, said leading-edge sheath contour nest being configured for supporting said leading-edge sheath,

opposed carriage members connected to said base, each of said opposed carriage members supporting a plurality of suction cups, said opposed carriage members being capable of synchronized translational movement relative to said leading-edge sheath contour nest between an engaged position wherein said plurality of suction cups are in abutting engagement with said leading-edge sheath, and a disengaged position where said plurality of suction cups are disengaged from said leading-edge sheath, and

a vacuum system connected in fluid communication with said plurality of suction cups, said vacuum system being capable of providing vacuum pressure to said plurality of suction cups, whereby said vacuum pressure generates suction forces between said plurality of suction cups and said leading-edge sheath when said opposed carriage members are in said engaged position; and

(b) an upper assembly disposed in combination with said lower assembly, said upper assembly comprising

a plurality of stanchions connected to said base of said lower assembly,

a contour clamp connected to each of said stanchions such that each said contour clamp is capable of translational movement relative to said leading-edge sheath contour nest, said contour clamps being configured for supporting said helicopter main rotor blade subassembly, whereby said contour clamps function to facilitate insertion of said helicopter main rotor blade subassembly into said leading-edge sheath.

2. The apparatus of claim 1, wherein said vacuum system comprises a vacuum source connected to a vacuum accumulator, whereby said vacuum source and said vacuum accumulator function in combination to provide said vacuum pressure to said plurality of suction cups.

3. The apparatus of claim 1, wherein said lower assembly further comprises pneumatic cylinders interposed between said base and said opposed carriage members, and a pressure source connected in fluid communication with said pneumatic cylinders, whereby said pneumatic cylinders operate in response to inputs from said pressure source to provide said synchronized translational movement of said opposed carriage members relative to said leading-edge sheath contour nest.

4. The apparatus of claim 1, further comprising a rotational wheel and differential assembly disposed in combination with said base, said plurality of stanchions, and said plurality of contour clamps, whereby said rotational wheel and differential assembly function to mechanically urge said contour clamps into said translational movement relative to said leading-edge sheath contour nest in response to manual inputs to said rotational wheel.

5. The apparatus of claim 1, wherein each of said contour clamps has a contour surface and a hinged securing member, whereby each of said contour clamps is capable of assuming an open configuration wherein said hinged securing member is positioned distal from said contour surface, and a closed configuration wherein said hinged securing