Abstract: A composite manufacture assembly is disclosed including a pair of closed mould tools for pressing a composite laminate panel therebetween, the closed mould tools having opposing inner surfaces that define an inner cavity that decreases in height along a span of the inner cavity in accordance with a curved rational function, the decrease in height corresponding to a designed thickness of the composite panel. The composite laminate panel including a stack of fibre-reinforced composite plies; a plurality of sets of ply drops spaced along a span of the composite laminate panel at which a corresponding set of plies terminate such that the thickness of the composite laminate panel varies along the span in accordance with the position and thickness of the sets of ply drops, each set of ply drops comprising one or more ply drops.

Abstract: A winglet is disclosed including first and second covers, a front spar, a rear spar, a rib, and a mid spar between the front spar and the rear spar. The rib and each spar are joined to the first cover and to the second cover. The mid spar has a length and the mid spar curves along all or part of its length. The length of the mid spar extends from an inboard end of the mid spar to an outboard end of the mid spar, and the rib wraps around the inboard or outboard end of the mid spar.

Abstract: A composite spar is disclosed having a main body and a pair of spaced apart legs. 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.

Abstract: A wingtip device to attach to a wing of an aircraft includes an aerofoil portion and a connection spar arranged to be received in a connection spar receiving portion of the wing of an aircraft. The spar includes a first through hole in a first portion of the connection spar and a second through hole in a second rearward portion of the connection spar, the second portion being rearward of the first portion with respect to a direction of flight. The first and second through holes are arranged to receive a retaining pin that is to be inserted through both the first and second through holes.

Abstract: A winglet 100 configured for attachment to a wing portion 10 for an aircraft 1000. The winglet 100 includes a first outer wall 101, a second outer wall 102, and one or more spars 114, 116 between the first outer wall 101 and the second outer wall 102. The first outer wall 101 is unitary with the second outer wall 102 and/or with the one or more spars 114, 116.