The composite aerodynamically shaped, partic. helicopter rotor, blade comprises a tubular spar (12) configured on the outside to provide mating surfaces for a leading edge profile strip (18), a C-shaped rear end doubler (24) and a curved panel (16) covering the leading edge (44), extending back over the doubler (24) but clear of it. The panel should pref. be of titanium. The doubler carries the blade rear portion, comprising a shaped cellular core (26) with top (28) and underside (30) cladding extending over the doubler to fill the gap between it and cover panel (16). All components are rigidly bonded together using adhesive, in moulds. Main spar profiling can include provision for de-icing equipment (55).
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