Apparatus and methods for making rotorcraft rotor blades

Patent metadata

Field	Value
Publication number	US-10569906-B2
Application number	US-201615198933-A
Country	US
Kind code	B2
Filing date	Jun 30, 2016
Priority date	Jun 30, 2016
Publication date	Feb 25, 2020
Grant date	Feb 25, 2020

Abstract

A method of making a rotor blade assembly includes receiving a sheath assembly and a blade body at a blade assembly tool. The sheath assembly is spread by applying force to an interior surface of the sheath assembly. The blade body is inserted within the interior of the sheath assembly, registered with the sheath assembly, and the force removed from the interior surface of the sheath assembly such that the sheath assembly collapses on the blade body.

First claim

What is claimed is:

1. A blade assembly apparatus, comprising:
a base structure;
a sheath-cradling fixture fixed relative to the base structure;
a blade-positioning fixture disposed on a side of a sheath assembly opposite the base structure and movable relative to the sheath assembly; and
a spreader jig movable relative to the sheath-cradling fixture, wherein the spreader jig includes a plurality of pull handles movable between an unspread position and a spread position relative to the sheath-cradling fixture to spread a sheath assembly for seating a blade body therein, and wherein the spreader jig further includes a spreader bar with a lip configured to engage an inner surface of the sheath assembly.

2. The blade assembly apparatus as recited in claim 1 , further comprising a blade body clamping mechanism operably connected to the blade-positioning fixture to fix the blade body relative to the sheath-cradling fixture.

3. The blade assembly apparatus as recited in claim 1 , further comprising a laser positioner fixed relative to the sheath-cradling fixture to register the blade body relative to the sheath assembly.

4. The blade assembly apparatus as recited in claim 1 , further comprising a coarse positioning mechanism and a fine positioning mechanism operably connected to the blade-positioning fixture to register the blade body relative to the sheath assembly.

5. The blade assembly apparatus as recited in claim 1 , further comprising a locking mechanism operably connected to the spreader jig to fix a width of the sheath assembly supported by the sheath assembly cradle.

6. The blade assembly apparatus as recited in claim 5 , wherein the locking mechanism includes a rack with a plurality of ratchet teeth pivotably fixed to the spreader jig and a locking member with a locking tooth pivotable relative to the rack to spread the sheath assembly and lock the sheath assembly in the spread position.

7. A blade assembly apparatus, comprising:
a base structure;
a sheath-cradling fixture fixed relative to the base structure;
a blade-positioning fixture disposed on a side of a sheath assembly opposite the base structure and movable relative to the sheath assembly; and
a spreader jig movable relative to the sheath-cradling fixture, wherein the spreader jig includes a plurality of pull handles movable between an unspread position and a spread position relative to the sheath-cradling fixture to spread a sheath assembly for seating a blade body therein, wherein the spreader jig further includes a spreader bar with a lip configured to engage an inner surface of the sheath assembly, wherein the spreader jig transforms from the unspread position to the spread position in response to application of a force thereto, a blade body being insertable into the sheath assembly when the spreader jig is in the spread position, and the spreader jig is configured to collapse onto the blade body upon removal of the force.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Littlejohn David
• Lofstrom Sven Roy
• Boyle Eric C

Classifications

• B64F5/10 Primary

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C2027/4736

  from composite materials · CPC title

• B64C27/473

  Constructional features · CPC title