Systems and methods for assembling a structurally reinforced composite structure are disclosed herein. The methods include deforming a composite tubular skin to a deformed conformation to generate clearance to permit a frame assembly to be conveyed into an internal volume that is defined by the composite tubular skin. The methods further include conveying the frame assembly into the internal volume, permitting the composite tubular skin to deform from the deformed conformation to the target conformation, and operatively attaching the frame assembly to the composite tubular skin to form the structurally reinforced composite structure. The systems include a frame support that is configured to support the frame assembly, a frame deformation assembly, a skin support that is configured to support the composite tubular skin, and a skin deformation assembly.

An aircraft fuselage structure is disclosed herein and includes an outer skin, with circumferential ribs, such that a recess is provided for receiving a wing torsion box in the outer skin, and the ribs are interrupted in the region of the recess. An object of the disclosure includes providing an aircraft fuselage structure designed such that the wing torsion box is able to extend at least partially through the upper region of the fuselage, without the stability of the fuselage being significantly reduced. This can include providing first longitudinal members which are adjacent to the recess and which extend along the longitudinal edges beyond the entire length thereof. End regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

A harness routing electrically connects a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section includes a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point. The harness installation and routing is optimized, in order to reduce harness length and weight, but at the same time assuring that any damage to the harness cables are prevented during the entire aircraft operative life.

Aspects of the present disclosure generally describe polyarylether ketones and methods of use. In some aspects, a composition includes one or more polymers of formulae (I), (II), or (III):

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An airframe component includes a skin panel, a plurality of stringers attached to the skin panel, and at least one former running substantially perpendicular to the plurality of stringers on the skin panel, the at least one former being generatively formed on the skin panel by an Additive Manufacturing (AM) method.

A replaceable web structure for an aircraft frame is described and includes a plurality of structural members fabricated from a first type of material, the replaceable web structure comprising a plurality of web members fabricated from thin sheets of a second type of material, wherein each of the web members is fastened to a web frame of one of the structural members to replace a web portion of the one of the structural members; wherein the second type of material is lighter weight than the first type of material; and wherein the second type of material is more heat-resistant than the first material.

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.

The object is to provide an aircraft component positioning device, an aircraft assembly system, and an aircraft assembly method with which it is possible to precisely dispose components on a planar member of an aircraft without using a positioning jig. A positioning device (2) includes a detection unit (5) that detects positions of a plurality of first components installed on a planar member of an aircraft, a virtual position creation unit (6) that creates a virtual position between the plurality of first components on the basis of the positions of the plurality of first components that are detected, and a position determination unit (7) that, on the basis of the virtual position that is created, determines an installation position of a second component, different from the plurality of first components, that is installed on the planar member.

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more motors are disposed within or attached to the spokes. Three or more propellers are proximate to a leading edge of the one or more spokes, distributed along the one or more spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight.

A system using a pressure differential to clamp welding heads on opposite sides of a joint of a thermoplastic composite structure to be welded. The heads are positioned over the joint opposite each other. Each head includes a housing defining a chamber having a lower pressure such that the pressure differential forces the head against the side. Each head includes a contour plate located in the space and against the joint, and at least one of the heads includes a heater located in the space and heating the contour plate to a welding temperature. The system may also include a first arm coupled with one of the heads and moving it along the joint so as to remain aligned with the other head, and a second arm coupled with the other head and moving it along the joint while the system welds the joint in successive overlapping sections.