A public transportation system combines a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software having specifications, standards, processes, capabilities, nomenclature, and concepts of operations that together include a concerted, comprehensive, multi-modal, future system for moving people and goods that is herein named Quiet Urban Air Delivery (QUAD) and in which uniquely-capable, ultra-quiet, one to six-seat, electrically-powered, autonomous aircraft (SkyQarts) fly sub-193 kilometer trips on precise trajectories with negligible control latency and perform extremely short take-offs and landings (ESTOL) with curved traffic patterns at a highly-distributed network of very small, airports (“SkyNests”) that themselves have standardized compatible facilities that interoperate with SkyQarts as well as with versatile, autonomous electric-powered payload carts (EPCs) and robotic delivery carts (RDCs) to provide safe, fast, on-demand, community-acceptable, environmentally friendly, high-capacity, affordable door-to-door delivery of both passengers and cargo across urban, suburban and rural settings across the globe.

An airfoil structure comprising a torsion-box member with a cover and a spar web connected by at least one pivot joint to a leading-edge or trailing-edge member, wherein the pivot joint is configured to permit rotation of the leading-edge member, or trailing-edge member, relative to the torsion-box member between an installation position and an operational position.

An aircraft having a wing, including a fixed wing with a wing tip device movably mounted at the outer end thereof is disclosed. The wing tip device is movable between: a flight configuration; and a ground configuration. The wing tip device and the fixed wing are separated along an oblique primary cut plane. The wing tip device and the fixed wing meet along an interfacing cut line. The wing tip device and fixed wing comprise a wing skin with a thickness, and end faces extending across the thickness of the wing skin provide interfacing surfaces corresponding to the interfacing cut line, wherein the interfacing surfaces are angled at a first orientation towards the front of the wing and a second, opposite, orientation towards the rear of the wing.

A spar for a wing includes a monolithic structure and a strut. The monolithic structure includes an upper chord, a lower chord, and a web positioned between the upper chord and the lower chord. The strut, distinct and separate from the monolithic structure, is coupled to the monolithic structure between the upper chord and the lower chord and extends across the web.

An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

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.

An aerostructure assembly of an aircraft is disclosed having a first aerostructure portion extending in a direction between a first position and a second position and including structurally of at least one rib or spar portion at least partially enclosed by a cover portion; a corresponding second aerostructure portion connected to the first aerostructure portion and extending continuously in the direction from the first aerostructure portion between the second position and a third position and including structurally of at least one further rib or further spar portion at least partially enclosed by a further cover portion. The first aerostructure portion has a first aerodynamic planform area (SI) and the corresponding second aerostructure portion has a corresponding second aerodynamic planform area (S2). A total aerodynamic planform area of the first aerostructure portion and corresponding second aerostructure portion is equal to the sum of the first aerodynamic planform area and the corresponding second aerodynamic planform area.

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.

Liquid shim injection devices and methods for injecting liquid shim material into a gap between adjacent components of an assembly. The liquid shim injection devices comprise a body, which comprises an injection shaft, a liquid shim conduit defined within the body and configured to channel liquid shim material within the injection shaft, and a fluid-permeable region formed along the injection shaft, an actuated fluid seal operably coupled to the injection shaft and configured to be selectively conformed among a plurality of conformations, and a fluid seal actuator assembly configured to transition the actuated fluid seal among the plurality of conformations. Methods comprise inserting the injection shaft into a bore that extends through the adjacent components of the assembly, forming a fluid seal between the liquid shim injection device and an interior component of the assembly, and flowing the liquid shim material from the liquid shim injection device into the gap.