A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).

Aerodynamic structures and methods of forming aerodynamic structures are disclosed herein. The aerodynamic structures include a first skin region that includes a first skin edge and a second skin region that includes a second skin edge. The first skin region and the second skin region are angled relative to one another and define a gap between the first skin edge and the second skin edge. The aerodynamic structures also include a trailing edge structure that extends within the gap and between the first skin edge and the second skin edge. The aerodynamic structures further include a plurality of blind fasteners. A first subset of the plurality of blind fasteners operatively interconnects the first skin region and the trailing edge structure. A second subset of the plurality of blind fasteners operatively interconnects the second skin region and the trailing edge structure. The methods include methods of forming the aerodynamic structures.

A compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.

A drone includes a frame and a fuselage. The fuselage is coupled to the frame extending away from the frame. The fuselage has a front panel and a bottom panel, and the front panel is positioned at an angle between the bottom surface of the frame and the bottom panel of the fuselage. A first wing is opposite a second wing and are coupled to the frame. The first and second wings extend outwardly from opposite sides of the frame. A first and second mounting member are coupled to the frame and extend outwardly from opposite sides of the frame. A plurality of power generator systems are included and each system is coupled to the first or second mounting member. Each power generator system comprises a power source coupled to a propeller.

A process for assembling portions of an aeronautical wing, in which a wing covering is assembled with carrier structural elements, allows the simultaneous application of all filling tapes on an exposed surface, by speeding-up and making more reliable the process itself. The process includes: placing side by side the structural elements longitudinally, to form the spars, by determining a flat surface, having a plurality of longitudinal junctions, faced upwards; adhering to the longitudinal junctions respective filling tapes; translating and rotating by 180° the structural elements in one single solution, by keeping them fixed in the mutual positions thereof and by transferring them above an inner surface of a wing covering; and translating the structural elements in one single solution, by keeping them fixed in the mutual positions thereof, downwards, by making the flat surface thereof to coincide with said inner surface.

A spar assembly for an aircraft wing extends between an upper cover and a lower cover and includes linkages spaced consecutively along the length of the spar assembly, each linkage extending from an upper pivot, to a lower pivot, thereby joining upper and lower attachment structures of the spar assembly together. Each linkage includes a pair of fixed-length links pivotably connected at one end about a center pivot and pivotably connected at respective other ends. The spar assembly includes a drive bar connected to the center pivot of each of the linkages, and an actuator arranged to move the drive bar along the length of the spar assembly. When the actuator moves the drive bar along the length of the spar structure, the links in each pair of links are rotated relative to each other about the center pivot, thereby moving the upper and lower covers and warping the wing.

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.