An unmanned aerial vehicle (UAV) (103) is provided which includes a radioactive fuel source (111), and an external combustion engine (107) powered by said radioactive fuel source.

A method for joining two substantially planar fiber-composite structural components, includes stacking the two components on a support jig to overlap along a joining region. A lower component end section within the joining region borders a gap between the upper component and the jig, where the upper component is unsupported by the jig. The gap is bordered on an opposite side of the lower component end section by a filling portion of the upper component or a planar filler element supported by the jig. The lower component is joined to the upper component within the joining region by applying temperature and pressure to the components. A width of the gap allows the upper component to elastically deform along the gap under the pressure and bend down into the gap to abut the jig along the gap and thereby compensate thickness tolerances between the components during the pressure application.

A method for forming a laminate by stacking sheet materials containing reinforcing fibers includes a fixation step wherein a first region of the laminate in the length direction is fixed to a forming mold having a curved part which comprises at least either a convex shape or a concave shape in a predetermined direction; forming steps wherein the laminate is formed along the surface shape of the forming mold by pressing a second region of the laminate in the length direction, the first region of said laminate having been fixed in the fixation step, against the forming mold by means of a forming jig; and an installation step wherein a holding jig, which holds a state where the laminate is pressed against the curved part, is installed onto the curved part, while maintaining the state where the laminate is pressed against the forming mold by means of the forming jig.

In accordance with at least on aspect of this disclosure, there is provided a hydrogen fuel system for aircraft. The hydrogen fuel system includes a gas turbine engine and a fuel feed conduit. The fuel feed conduit is defined at least in part by, in fluid series, a liquid hydrogen tank fluidly connected to a combustor of the gas turbine engine, a liquid hydrogen pump to drive fuel to the combustor of the gas turbine engine, an evaporator, and an electric heat source in thermal communication with the evaporator to add heat into a flow of hydrogen passing through the evaporator. In embodiments, the electric energy source associated with the electric heat source to power the electric heat source.

A seat, in particular an aircraft seat, having a seat support structure having at least one seat surface with a seat surface frame and a backrest with a backrest frame being pivotable relative to the seat surface, a base support element supporting the seat support structure, and a seat adjustment arrangement, which includes at least one coupling unit movable relative to the base support element, the coupling unit is configured to connect the seat surface frame and the backrest frame to one another and which is provided with at least one bearing element, and which includes at least one guide element in which the bearing element is movably guided. The seat adjustment arrangement being adapted to transfer the seat support structure into a sitting position, a comfort position or lying position by displacing the bearing element along the guide element.

A composite manufacturing system is provided. The composite manufacturing system comprises a fiber placement head, a compaction roller associated with the fiber placement head, and a temperature regulation system associated with the compaction roller. The temperature regulation system is configured to actively control a temperature of the compaction roller. The temperature regulation system comprises a number of temperature sensors, a cooling system, and a controller. The number of temperature sensors are configured to detect the temperature of the compaction roller. The cooling system is associated with the compaction roller and is configured to cool the compaction roller. The controller is in communication with the number of temperature sensors and the cooling system. The controller is configured to cool the compaction roller such that the temperature is below a threshold temperature.

A composite laminate for an airframe lifting surface including: at least two sides and one ramp area defined by a decreasing staggered laminate extended along a ramp direction, wherein the composite laminate includes: first plies formed by tapes arranged parallel to the ramp direction, second plies formed by tapes arranged orthogonal to the ramp direction, third plies formed by tapes arranged in a first laying up direction, being the first laying up direction different from the ramp direction and the direction orthogonal to the ramp direction, and fourth plies formed by tapes arranged in a second laying up direction, being the second laying up direction different from the ramp direction, the direction orthogonal to the ramp direction and the first laying up direction; wherein in the ramp area, the tapes forming the third and/or fourth plies are extended from one laminate side to another laminate side.

Disclosed is an instrument panel designed to be integrated into an aircraft cockpit, the instrument panel comprising a main structure, extending longitudinally and having a concave shape defining a cavity, this cavity being configured to receive a plurality of navigation command and/or control units, and at least one inner wall, configured to delimit at least two recesses each intended to receive at least one of the plurality of navigation command and/or control units, the instrument panel being characterized in that the main structure is made from a single piece made from a composite material.

A composite structure including a multi-layer laminate having a plurality of regions each oriented out of plane relative to an adjacent region, and each extending in a longitudinal dimension of the multi-layer laminate, wherein the multi-layer laminate includes at least one ply layer having an oblique fiber orientation relative to the longitudinal dimension, and wherein the at least one ply layer includes a first section and a second section each having a side edge, the first and second sections aligned side-by-side such that a first interface defined between the respective side edges is oriented to extend in the longitudinal dimension.

A heated composite structure and a method for forming a heated composite structure. The structure includes carbon fibers embedded within a thermoplastic matrix. The carbon fibers are connected with first and second electrodes that are configured to be connected with an electric source such that applying current to the electrodes causes current to flow through the embedded carbon fibers to provide resistive heating sufficient to heat the composite structure to impede formation of ice on the composite structure.