A bonding tool is described that is used to secure sacrificial pads to bonding locations on a perimeter of a rib during a bonding process. In one embodiment, the bonding tool includes a base member having a rib receptacle dimensioned to receive a rib of a wing, a plurality of compression forms disposed around at least a portion of the rib receptacle and proximate to a perimeter of the rib, where the compression forms include a plurality of sacrificial pads that face towards bonding locations on the perimeter of the rib, and at least one bladder proximate to the compression forms that expands between a wall of the base member and the compression forms to press the sacrificial pads against the bonding locations while the sacrificial pads bond to the bonding locations.

A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.

An aircraft is described and includes a fuselage, a wing coupled to the fuselage, and a rotor system including a proprotor system and an engine. An interconnect driveshaft gear is configured to communicate mechanical energy between a gearbox and an interconnect driveshaft. An accessory gear is coplanar with and in mechanical communication with the driveshaft gear. A proprotor gear is coplanar with and in mechanical communication with the interconnect driveshaft gear and the accessory gear and communicates mechanical energy to the proprotor system. An engine gear coplanar and in mechanical communication with the interconnect driveshaft ear, the accessory gear, and the proprotor gear transmits mechanical energy to the proprotor system via the proprotor gear.

A wing assembly is disclosed. The wing assembly includes a main structure having a first contact face and a first recess arranged to receive a portion of a tension bolt; and a modular edge having a second contact face and a second recess arranged to receive a portion of the tension bolt. The modular edge is pivotally mounted on the main structure for rotation between an installation position and an operational position in which the modular edge is aligned with the main structure to form at least part of an edge of the wing assembly. The wing assembly is arranged such that, when the modular edge is in the operational position, tension in a tension bolt received in the first and second recesses acts to press the first and second contact faces together, thereby forming a tension joint that resists pivoting of the modular edge relative to the main structure.

An aircraft assembly including: a first aircraft structure, a second aircraft structure, first and second tension bolts arranged to suspend the first aircraft structure below the second aircraft structure, the first and second tension bolts connected to the first aircraft structure such that an end of each of the tension bolts is accessible from respective outer surfaces of the first aircraft structure and first and second fail-safe mechanisms each associated with a respective one of the first and second tension bolts and arranged to suspend the first aircraft structure below the second aircraft structure responsive to failure of the respective tension bolt.

In an example, a method is described. The method comprises forming a single hole into a bond gap repair area. The method also comprises evacuating, via an adhesive injection apparatus attached to the single hole, the bond gap repair area and an injection channel of the adhesive injection apparatus. The method also comprises forcing adhesive through the evacuated injection channel and into the evacuated bond gap repair area.

A composite structure including a multi-layer laminate having a plurality of regions each oriented out of plane relative to an adjacent region, and each extending in a longitudinal dimension of the multi-layer laminate, wherein the multi-layer laminate includes at least one ply layer having an oblique fiber orientation relative to the longitudinal dimension, and wherein the at least one ply layer includes a first section and a second section each having a side edge, the first and second sections aligned side-by-side such that a first interface defined between the respective side edges is oriented to extend in the longitudinal dimension.

A wing used for an aircraft includes a configuration member formed of a composite material. The configuration member is divided into a plurality of regions along a surface thereof. The plurality of regions include a first region formed of the composite material of a high strength type, and a second region formed of the composite material of a high elasticity type having higher rigidity than the high strength type. The first region includes any region closest to a wing end side out of the plurality of regions, and the second region includes a region closest to the wing end side and a trailing edge side out of the plurality of regions.

A flying vehicle comprising a wing ship body having a pair of wing spars secured thereto; and a plurality of hinged wing-rib assemblies disposed along each wing spar that allows the wings to be folded against the body of the flying vehicle. Fabric-coupling members connect wing fabric to the wing-rib assemblies. A method for folding or collapsing the wings of a wing-in-ground-effect wing ship comprising providing a wing-in-ground-effect wing ship having a pair of wings, and folding the wings toward and against the body of the wing-in-ground-effect wing ship. A fabric covered wing folding assembly including a pair of wings with each wing having a wing spar and covered by a fabric. A plurality of hinged wing-rib assemblies is disposed along each wing spar that allows the wings to be folded against the body of the aircraft. A method is provided for folding or collapsing the wings of an aircraft. The method comprises the steps of providing a cable connected assembly and a cable release mechanism coupled to the body of an aircraft; and providing a fabric covering the wings of the aircraft.

An end rib assembly for a high-lift device of an aircraft to reduce the noise caused by the transition between the wing and a high-lift device as well as the noise caused by the lateral side edge of the end rib assembly. An end rib assembly includes a noise-reducing portion configured to reduce noise caused by an airflow around the end rib assembly, and a guiding portion configured for guiding the end rib assembly along a pre-determined path when the high-lift device is moved between a retracted position and an extended position, wherein the guiding portion is formed such that an airflow impinging on the guiding portion is partly guided towards the noise-reducing portion.