Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail. The radome shell opening kinematic further comprises a radome cover shell rotation stopper that can stop movement of the radome cover shell at the completely opened position.

Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.

Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.

Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail. The radome shell opening kinematic further comprises a radome cover shell rotation stopper that can stop movement of the radome cover shell at the completely opened position.

Abstract: An en route fluid transmitting apparatus for transmitting a fluid from a transmitting entity to a probe of a receiving vehicle includes a funnel, a hose and a thrust producing device. Thrust producing device includes a main body that is rigidly attached to the funnel, and at least two rotors that are connected to the main body for producing thrust. The thrust producing device is adapted to move the funnel freely in any direction to a predetermined position relative to the probe where the funnel engages with the probe.

Abstract: An en route fluid transmitting apparatus for transmitting a fluid from a transmitting entity to a probe of a receiving vehicle includes a funnel, a hose and a thrust producing device. Thrust producing device includes a main body that is rigidly attached to the funnel, and at least two rotors that are connected to the main body for producing thrust. The thrust producing device is adapted to move the funnel freely in any direction to a predetermined position relative to the probe where the funnel engages with the probe.

Abstract: A rotorcraft comprising a cowling for closing an opening in the fuselage, the cowling being linked to the fuselage by means of a fastening system having a supporting means pivotally attached to the interior of the fuselage and a translation means coupled to the supporting means to respectively enable movements of rotation and translation of the cowling.

Abstract: A rotorcraft comprising a cowling for closing an opening in the fuselage, the cowling being linked to the fuselage by means of a fastening system having a supporting means pivotally attached to the interior of the fuselage and a translation means coupled to the supporting means to respectively enable movements of rotation and translation of the cowling.