Abstract: A vertical take-off and landing aircraft is shown. The VTOL aircraft has a main wing having a left wing and a right wing configured as folding wings, and one or more of a foreplane, having a left canard and a right canard configured as folding wings, and/or a tailplane, having a left stabiliser and a right stabiliser configured as folding wings. Each one of the folding wings has a fixed inboard section and a folding outboard section. The folding outboard section is downwardly foldable to a landing condition to support the aircraft on a surface.

Abstract: A vertical take-off and landing aircraft is shown. The VTOL aircraft has a main wing having a left wing and a right wing configured as folding wings, and one or more of a foreplane, having a left canard and a right canard configured as folding wings, and/or a tailplane, having a left stabiliser and a right stabiliser configured as folding wings. Each one of the folding wings has a fixed inboard section and a folding outboard section. The folding outboard section is downwardly foldable to a landing condition to support the aircraft on a surface.

Abstract: A composite turbomachine blade (34) comprises a composite material including reinforcing fibers in a matrix material, the turbomachine blade (34) comprises an aerofoil portion (36), a shank portion (38) and a root portion (40). The aerofoil portion (36) has a leading edge (42), a trailing edge (44). The composite turbomachine blade (34) also has a metallic protective member (52) arranged in the region of the leading edge (42) of the aerofoil portion (36) of the turbomachine blade (34). The metallic protective member (52) is adhesively bonded to the composite material in the region of the leading edge (42) of the aerofoil portion (36) of the composite turbomachine blade (34). The metallic protective member (52) has at least one metallic projection (56, 58) extending from the metallic protective member (52) towards the root portion (40) of the composite turbomachine blade (34).

Abstract: A composite turbomachine blade (34) comprises a composite material including reinforcing fibres in a matrix material, the turbomachine blade (34) comprises an aerofoil portion (36), a shank portion (38) and a root portion (40). The aerofoil portion (36) has a leading edge (42), a trailing edge (44). The composite turbomachine blade (34) also has a metallic protective member (52) arranged in the region of the leading edge (42) of the aerofoil portion (36) of the turbomachine blade (34). The metallic protective member (52) is adhesively bonded to the composite material in the region of the leading edge (42) of the aerofoil portion (36) of the composite turbomachine blade (34). The metallic protective member (52) has at least one metallic projection (56, 58) extending from the metallic protective member (52) towards the root portion (40) of the composite turbomachine blade (34).