A stringer runout configuration has a pair of fittings with each fitting having a fitting web that is configured for attachment to a stringer web of a stringer on opposite sides of a terminating end of the stringer. The stringer web has a terminating end with a curved configuration and base flanges with rounded terminating ends. Each fitting has a base flange that has a bottom surface with a first surface area and a second surface area positioned at different heights. The first surface area of each of the fittings is configured for attachment to a stringer base flange on opposite sides of a terminating end of the stringer. The second surface area of each of the fittings is configured for attachment to a composite panel surface adjacent the terminating end of the stringer. These and other detailed design features described herein enhance the capability of the runout configuration.

A wing structure for a vehicle, and a vehicle. The wing structure comprises at least one multi-connecting-rod structure. The multi-connecting-rod structure is arranged in a direction extending from the main body of a vehicle to a wingtip, each multi-connecting-rod mechanism comprises a plurality of connecting rods, and connecting rods which are adjacent to each other are connected by means of a motor. The present technical solution provides a wing structure having the feature of a morphing wing having a large range in both chordwise and spanwise directions. The wing structure has the capability of changing airfoil and changing a pitch angle within a large range, the capability of twisting along a spanwise direction at a distal portion, the capability of swinging perpendicularly within a large range along the plane in which the main body of the vehicle is located, and the capability of swinging longitudinally within a large range along the main body of the vehicle, adjustment can be performed on a complex flow field or environment, the motion speed and the motion efficiency are significantly improved, and high maneuvering actions can be achieved.

The invention relates to a supporting structure (46) which is positioned in a fluid flow (44) and characterised in that it is configured to be elastically deformed, on at least one portion of the supporting structure (46), between a first idle state in the absence of external stress and a second deformed state in the presence of external stresses caused by the fluid flow (44) due to a change in the orientation of the supporting structure (46) and/or the fluid flow (44). The invention also relates to an aircraft comprising at least one such supporting structure (46).

Systems and methods are provided for fabricating composite parts. One embodiment is a method for fabricating a composite part. The method includes forming a skin panel preform comprising fiber reinforced material, disposing rigid end caps at the skin panel preform at end locations of stringer preforms that will be placed at the skin panel, locating the stringer preforms at the skin panel preform via the rigid end caps, and anchoring the stringer preforms to the skin panel preform.

A hat-stringer assembly for an aircraft comprises a hat stringer with a first hat-stringer leg, a second hat-stringer leg, a first hat-stringer sidewall, a connecting wall, a second hat-stringer sidewall, and a ventilation opening, extending through the connecting wall. The hat stringer assembly also comprises a fitting, comprising a first channel member in contact with the first hat-stringer sidewall and the first hat-stringer leg. The fitting also comprises a second channel member in contact with the second hat-stringer sidewall and the second hat-stringer leg. The fitting further comprises a web cap, in contact with the first channel member and the second channel member. The web cap comprises a web-cap opening, which is in fluidic communication with the ventilation opening.

A composite stiffener for a stiffener reinforced panel is disclosed. The stiffener has a longitudinal direction and a run-out region which terminates at an end of the stiffener. The stiffener also has a constant section region inboard of the run-out region in the longitudinal direction and having a constant cross section transverse to the longitudinal direction with a crown between adjacent foot portions. The run-out region has a changing cross section transverse to the longitudinal direction with a crown between adjacent foot portions and the crown reduces in height towards the end of the stiffener forming a ramp. The composite stiffener comprises a number of blankets of non-crimp fabric layers.

An aircraft panel assembly with a panel and a plurality of stiffeners on the panel is disclosed. Each stiffener has an attachment part attached to the panel and a structural part spaced apart from the panel. A rib foot beam crosses the stiffeners at a series of intersections. At each intersection the rib foot beam is located between the panel and the structural part of a respective one of the stiffeners.

According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The panel is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

An example aircraft wing includes a skin, a composite shear tie, a stringer base charge overlaying the skin, and a stringer overlaying the stringer base charge. The composite shear tie includes a shear-tie web, a first shear-tie flange extending from a first side of the shear-tie web, a second shear-tie flange extending from a second side of the shear-tie web, and a first shear-tie tab extending from an end of the first side of the shear-tie web. The stringer includes a stringer web, a first stringer flange extending from a first side of the stringer web, and a second stringer flange extending from a second side of the stringer web. The first stringer flange is stitched to and integrated with the stringer base charge and the skin. Further, the first shear-tie flange is stitched to and integrated with the first stringer flange.

A bladder mandrel package, used to manufacture a composite structure, includes a mandrel and a wrap ply, surrounding the mandrel to form a wrapped mandrel. The bladder mandrel package also includes a first radius filler, coupled to the wrap ply at a first radius of the wrapped mandrel, and a second radius filler coupled to the wrap ply at a second radius of the wrapped mandrel. The mandrel, the wrap ply, the first radius filler, and the second radius filler are consolidated to from the bladder mandrel package.