According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The panel is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

According to one implementation, a composite material structure includes a corrugated stringer and a panel. The corrugated stringer has a corrugated structure including portions each having hat-shaped cross section. The corrugated stringer is made of a composite material. The panel is integrated with the corrugated stringer. The panel is made of a composite material. Further, according to one implementation, a manufacturing method of a composite material structure includes: setting a textile on a laminated body of prepregs; and producing the composite material structure by covering the laminated body with a bagging film, forming a vacuum state in a space covered with the bagging film, impregnating the textile with the resin, and thermal curing of the laminated body of the prepregs. The laminated body is a panel before curing. The textile has a structure corresponding to a corrugated stringer.

A fuselage assembly for an aircraft including a stringer extending longitudinally along the fuselage. The stringer defines a fluid channel. The fluid channel is configured to form at least part of a distribution duct of a cabin air distribution system.

A composite structural member including at least one first flange element made from a first composite material, and at least one first web element made from a second composite material. The at least one first web element is connected to at least one first flange element in a non-coplanar manner along a corresponding mutual first edge via a first corner element made from a third composite material, the mutual first edge extending along a first direction. The third composite material includes a corresponding first plurality of third composite material first fibers and a corresponding second plurality of third composite material second fibers embedded in a corresponding third composite material matrix in a non-parallel orientation with respect to the third composite material first fibers, wherein the third composite material first fibers are nominally orthogonal to the mutual first edge or to the first direction.

A joining method for connecting at least two thermoplastic workpieces is provided to permit the joining even of non-transparent carbon fiber reinforced plastics parts by means of laser welding, in which a splice is produced at the edge regions of the workpieces and the workpieces are subsequently positioned relative to one another in such a manner that the opposite splice regions bound a seam region. Connecting bodies are then inserted into the seam region and heated by means of local heat input by laser beam such that a fixed integrally bonded connection forms between the workpieces and the connecting bodies.

A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube. The reinforcing element comprises: a fiber structure which has a hollow-cylindrical, helically wound mesh of fiber strands and forms an inner shell surface formed to receive the structural profile; and a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material. Also provided are a structural arrangement with such a reinforcing element, an aircraft or spacecraft with such a structural arrangement, as well as a method for producing such a structural arrangement.

Various embodiments for a foldable quad-rotor (FQR) inspired by an origami mechanism are disclosed herein. The FQR can fold its arms during flight to enable aggressive turning maneuvers and operations in cluttered environments. A dynamic model of folding is built for this system with the collected data, and a feedback controller is designed to control the position and orientation of the FQR. Lyapunov stability analysis is conducted to show that the system is stable during arm folding and extension, and motion planning of the FQR is achieved based on a modified minimum-snap trajectory generation method.

A mechanical arm having a shell and a lift power unit. A holding chamber is arranged in the mechanical arm shell, the lift power unit part is arranged in the holding chamber, the upper wall surface of the mechanical arm shell is provided with a first heat dissipation hole and a second heat dissipation hole. The first heat dissipation hole and the second heat dissipation hole are located on each side of the lift power unit, respectively. The lower wall surface of the mechanical arm shell is provided with a third heat dissipation hole and a fourth heat dissipation hole, and the third heat dissipation hole and the fourth heat dissipation hole are located on each side of the lift power unit, respectively.

A mechanical arm having a shell and a lift power unit. A holding chamber is arranged in the mechanical arm shell, the lift power unit part is arranged in the holding chamber, the upper wall surface of the mechanical arm shell is provided with a first heat dissipation hole and a second heat dissipation hole. The first heat dissipation hole and the second heat dissipation hole are located on each side of the lift power unit, respectively. The lower wall surface of the mechanical arm shell is provided with a third heat dissipation hole and a fourth heat dissipation hole, and the third heat dissipation hole and the fourth heat dissipation hole are located on each side of the lift power unit, respectively.

Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting in-ring propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing propellers, each of which is connected to an independently operating electric motor. The front and rear lifting in-ring propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing propeller and the left pushing propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.