A connector for connecting a frame to a transversely extending stringer of a fuselage structure of an aircraft includes a base carrier extending in a longitudinal connector direction, a first connecting portion connected to the base carrier and extending in a first transverse connector direction, the first connecting portion having a coupling structure in an end region remote from the base carrier for engaging around an end region of a cross-section of the stringer, and a second connecting portion connected to the base carrier and adapted to be connected to the frame.

A blended wing body aircraft having an interior cabin with a usable volume of at most 4500 ft.sup.3 and a cabin aspect ratio of at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.7 and at most 2.8. Also, a blended wing body aircraft having an interior cabin with a usable volume of at least 1500 ft.sup.3 and at most 4500 ft.sup.3 and a cabin aspect ratio of at least 2 and at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.9 and at most 2.7. Also, a blended wing body aircraft wherein at least each profile section having normalized half-span values from 0 to 0.3 has a leading edge having a normalized height having a nominal value within the range set forth in Table 4.

A multi-axis aircraft with a wind resistant unit includes a fuselage having an upper face and a lower face. The fuselage includes a central axis passing through the upper face and the lower face. A plurality of rotors is mounted to the fuselage. Each rotor includes a rotating axis parallel to the central axis. A wind resistant unit includes a plurality of wind barriers disposed in a radial direction perpendicular to a reference axis. Each wind barrier includes a plurality of rods fixed by at least one fixing member. Two adjacent rods have a passage therebetween. Each rod includes an axis proximal end facing the reference axis and an axis remote end remote to the reference axis. Each wind barrier includes a coupling end and an airflow diversion end. The coupling end is fixed by at least one coupling member to the upper face of the fuselage.

A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head.

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 stronger than the first type of material such that one of the sheets of the second type of material is lighter weight than a sheet of equal strength of the first type of material.

Described herein are stringer assemblies, such as blade stringers, and methods of forming thereof. A stringer assembly comprises a first fabric composite stiffener, a second fabric composite stiffener, and an intermediate tape composite stiffener, disposed between and connected to each of the first and second stiffeners. Using three separate components allows forming sharp bends, eliminating voids and gap fillers, and adding new features, such as edge reinforcements. Each of the first and second fabric composite stiffeners comprises a web portion, a flange portion, and a curved portion, positioned between the web and flange portions. The web portions surround and are attached to the intermediate tape composite stiffener and, in some examples, include tapered-out edges for additional rigidity. The flange portions are attached to the composite base. The curved portions conform to the flared-out edges of the intermediate tape composite stiffener, which extends and connects to the composite base.

Described herein are methods and systems for forming composite stringer assemblies or, more specifically, for shaping composite charges while forming these stringer assemblies. A system comprises a bladder, having a bladder core, and a bladder skin. The bladder core is formed from foam. The bladder skin is formed from an elastic material and encloses the bladder core. When a composite stringer assembly is formed, the bladder is positioned over a charge base. The charge base later becomes a stringer base, such as a fuselage section or a wing skin. A charge hat is then positioned over the bladder and is conformed to the bladder. A combination of the bladder skin and the bladder core provides support during this forming operation and later while the stringer assembly is cured. In some examples, the bladder core is collapsible for the removal of the bladder from the cavity of the stringer assembly.

A coated wire suitable for aerospace applications includes a metallic conductor elongated along an axis and having an outer surface extending along the axis, and three coating layers surrounding the conductor. A first coating layer is connected to the outer surface of the conductor and extends along the axis to surround the conductor, and the first coating layer is formed of ethene-tetrafluoroethene. A second coating layer is connected to the first coating layer and extends along the axis to surround the first coating layer, and the second coating layer is formed of polyaryletherketone. A third coating layer is connected to the second coating layer and extends along the axis to surround the third coating layer, wherein the third coating layer is formed of ethene-tetrafluoroethene. The three coating layers may each be continuous and seamless extruded layers in one configuration.

A rotorcraft (1) having: a lift rotor (5); a wing (10) extending from a first end (11) carrying a first propulsive propeller (21) to a second end (12) carrying a second propeller (22); landing gear (30); and a tail (40). The rotorcraft (1) is provided with two fuselages (51, 52) secured to said wing (10) between said first and second propulsive propellers (21, 22) in such a manner as to present an inter-fuselage space (60) having no propeller between said fuselages (51, 52), each fuselage (51, 52) including at least one undercarriage of said landing gear (30).

A rotorcraft (1) having: a lift rotor (5); a wing (10) extending from a first end (11) carrying a first propulsive propeller (21) to a second end (12) carrying a second propeller (22); landing gear (30); and a tail (40). The rotorcraft (1) is provided with two fuselages (51, 52) secured to said wing (10) between said first and second propulsive propellers (21, 22) in such a manner as to present an inter-fuselage space (60) having no propeller between said fuselages (51, 52), each fuselage (51, 52) including at least one undercarriage of said landing gear (30).