The invention provides a composite spar 1 comprising a main body 2 and a pair of spaced apart leg 3, 4. The space between the legs permits access to the mandrel assembly within the spar in order to ease its removal. This arrangement permits a spar of any length and contour to be manufactured. There is further disclosed a method of manufacturing such a spar comprising laying a fabric on a mandrel assembly, laying a die assembly over the fabric, injecting liquid resin into the fabric and curing the fabric by applying an elevated temperature. The mandrel preferably comprises a main body mandrel arranged to form the main body of the spar and which is slidably removable from the spar. A plurality of mandrel segments may also be provided and arranged to form the legs of the spar, each segment being slidably removable from the spar, allowing for the making of relatively complex spar shapes.
Composite spar for a wing structure
2019-11-06
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |