Methods for fabricating a helicopter main rotor blade

Abstract

A method for fabricating a helicopter main rotor blade includes a compaction fixture for assembling and compacting blade subassembly components and a sheath spreading/insertion apparatus for spreading and inserting a leading-edge sheath onto in combination with the blade subassembly during the compaction process. The compaction fixture includes a lower assembly having a contoured upper airfoil nest mounted in combination with a support structure and an upper assembly having a pressure bag affixed in sealed combination to a contoured backplate affixed in combination to a structural support truss. The contoured upper airfoil nest includes a plurality of tooling pins for locating an upper composite skin in aligned combination on the contoured upper airfoil nest and a plurality of pusher pins for chordwise alignment of a spar assembly in the contoured upper airfoil nest. Spar stanchions affixed to the support structure provide spanwise alignment of the spar assembly in the contoured upper airfoil nest. With the upper and lower assemblies in locked combination, the pressure bag is pressurized to compact the assembled blade subassembly components.

What is claimed is:  
     
       1. A method for assembling and compacting a blade subassembly that includes an upper composite skin, a lower composite skin, a honeycomb core, and a spar assembly, comprising the steps of: 
       providing a composite fixture that includes a lower assembly having a contoured upper airfoil nest mounted on a support structure and an upper assembly having a structural support truss, a contoured backplate affixed to the structural support truss, and a pressure bag fastened in sealed combination with the contoured backplate;  
       laying up the upper composite skin and the honeycomb core in combination in the contoured upper airfoil nest;  
       locating the spar assembly in chordwise and spanwise alignment in the contoured upper airfoil nest;  
       laying up said lower composite skin in combination with the spar assembly and the honeycomb core;  
       locking the upper assembly and the lower assembly in combination; and  
       pressurizing the pressure bag to compact the blade subassembly.  
     
     
       2. The method of  claim 1  further comprising the step of inserting a caul plate between the upper assembly and the lower assembly prior to said locking step. 
     
     
       3. A method for spreading and inserting  positioning a leading-edge sheath onto  in relation to a blade subassembly, comprising the steps of: 
       mounting the leading-edge sheath between upper  first and lower  second rows of suction cups;  
       imparting synchronized movement to the upper  first and lower  second rows of suction cups to an engaged position wherein the suction cups are in abutting engagement with respective OML surfaces of the leading edge sheath;  
       generating suction forces in the upper  first and lower  second rows of suction cups to cause the suction cups to hold the respective OML surfaces of the leading-edge sheath;  
       imparting synchronized movement to the upper  first and lower  second rows of suction cups to an operating position to cause the leading-edge sheath to be spread apart; and  
       insertingpositioning the spread-apart leading-edge sheath ontoin relation to the blade subassembly.