초록 ▼

A method for manufacture of a fiber reinforced composite spar for a helicopter rotor blade including upper and lower sidewall regions and forward and aft conic regions. Constant width crossplies and unidirectional plies are stacked and arranged to form crossply and unidirectional laminates. The comp

A method for manufacture of a fiber reinforced composite spar for a helicopter rotor blade including upper and lower sidewall regions and forward and aft conic regions. Constant width crossplies and unidirectional plies are stacked and arranged to form crossply and unidirectional laminates. The composite spar is manufactured via a vacuum forming technique which includes forming the composite laminates directly over an inflatable mandrel assembly. Regarding the latter method, a spar forming apparatus is used to position and manipulate the mandrel assembly as composite laminates are laid. The spar forming apparatus includes first and second pedestal supports being suitably configured so as to facilitate formation of the butt joints in the conic regions of the composite spar. The pedestal supports are movable from a first orientation to facilitate lay-up of composite laminates over the mandrel assembly, to a second orientation to facilitate transfer of the mandrel assembly from one to the other of the pedestal supports. The spar forming apparatus further includes an electromagnetic coil system comprising at least one electrically activated coil and a controllable power source. The electrically activated coils are disposed in combination with each of the pedestal supports and the controllable power source selectively energizes the electrically activated coils to effect a magnetic clamping force between the mandrel assembly and one of the pedestal supports. Such electromagnetic coil system accurately positions the inflatable mandrel assembly during lay-up of the composite laminates and effects transfer of the mandrel assembly.

대표청구항 ▼

[ What is claimed is:] [1.] A method for manufacturing a composite spar (10), said composite spar (10) having upper and lower sidewall regions (40, 42) connected by forward and aft conic regions (45, 47), the method comprising the steps of:providing an inflatable mandrel assembly (110) having a widt

[ What is claimed is:] [1.] A method for manufacturing a composite spar (10), said composite spar (10) having upper and lower sidewall regions (40, 42) connected by forward and aft conic regions (45, 47), the method comprising the steps of:providing an inflatable mandrel assembly (110) having a width dimension (Dm) and having ferrous properties;providing a spar forming apparatus including:first and second pedestal supports (204a, 204b) each being suitably configured for supporting the inflatable mandrel assembly (110), and having a width dimension (Dpw) which is less than the width dimension (Dm) of the mandrel assembly (110), said pedestal supports (204a, 204b) being movable from a first orientation to a second orientation;at least one electrically activated coil (232) disposed in combination with each of the pedestal supports (204a, 204b); anda controllable power (234) source for selectively energizing said electrically activated coils (232) to effect a magnetic clamping force between the mandrel assembly (110) and one of the pedestal supports (204a, 204b);assembling crossply and unidirectional laminates (60, 70) over the mandrel assembly (110) to form a preform assembly (120) having the unidirectional laminates (70) interposed between the crossply laminates (60) and having structural joints (68) and slip planes (66) in areas corresponding to the forward and aft conic regions (45, 47) of the composite spar (10), said assembly step comprising the substeps of:a. energizing said electrically activated coil (232) associated with the one of the pedestal supports (204a, 204b) while in a first orientation to maintain the position of the mandrel assembly (110);b. laying said crossply and unidirectional laminates (60, 70) over a side of the mandrel assembly (110),c. forming said crossply and unidirectional laminates (60, 70) such that said crossply laminates (60) are caused to wrap around the mandrel assembly (110) in areas corresponding to the conic regions (45, 47) of the composite spar (10);d. moving said pedestal supports (204a, 204b) into a second orientation such that each is contiguous with the mandrel assembly (110)e. de-energizing the electrically activated coil (232) associated with one of the pedestal supports (204a or 204b) and energizing the electrically activated coil (232) associated with the other of the pedestal supports (204a or 204b) to effect transfer of the mandrel assembly (110) from one to the other of the pedestal supports (204a, 204b );f. repeating steps a through e until all crossply and unidirectional laminates have been laid, thereby forming a preform assembly (120);placing the preform assembly (120) into a curing mold having mold surfaces defining an outer contour of the composite spar (10);pressurizing the inflatable mandrel assembly (110) for urging the crossply and unidirectional laminates (60, 70) against the mold surfaces of the curing mold to compact the laminates (60, 70); and,curing the crossply and unidirectional laminates (60, 70),whereby the forming of structural joints (68) and slip planes (66) in conics regions (45, 47) facilitates uniform compaction of the crossply and directional laminates (60, 70).