Abstract: A fuselage arranged within a fuselage outer shell; at least one main rotor located on top of the fuselage; at least one engine provided for driving the at least one main rotor; and at least one energy source storage unit comprising at least one energy source configured to provide energy for powering the at least one engine for driving the at least one main rotor; wherein the at least one energy source storage unit is arranged outside the fuselage outer shell; and wherein the fuselage and the fuselage outer shell form in vicinity of the at least one energy source storage unit a crashable structure configured to be crashable in an emergency landing at least for limiting effects of impact on the at least one energy source storage unit.

Abstract: The disclosure is related to a rotary wing aircraft with a fuselage and an at least partially non-retractable landing gear, wherein the at least partially non-retractable landing gear comprises at least three individual support legs, wherein at least one individual support leg of the at least three individual support legs is mounted pivotally to the fuselage by means of an associated pivot bearing arrangement, wherein the at least one individual support leg is further connected to the fuselage via at least one torsion element with a predetermined elastic range, and wherein the at least one torsion element is adapted to act, in the predetermined elastic range, as a torsional spring, and, outside of the predetermined elastic range, as an energy absorber.

Abstract: An attachment for attaching an aircraft engine with a first receiving element to an aircraft structure with a second receiving element may include at least three fasteners and a stacked layer. Stacked layer may include at least two sheets, at least three holes through the stacked layer, a first connecting portion that includes a first hole of the at least three holes, a second connecting portion that includes second and third holes of the at least three holes, and a suspension portion that is located between the first connecting portion and the second connecting portion.

Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the c

Abstract: An overload coupling for coupling a driving device to a driven device. The present embodiments also relate to a rotating drive system with such an overload coupling, to a rotor system with such a rotating drive system, and to a rotary-wing aircraft with such a rotor system. The overload coupling may include concentrically arranged inner connecting element coupled to the driving device and outer connecting element coupled to the driven device. At least a first and a second arm, that each include an arrangement of at least one plate may connect the inner connecting element with the outer connecting element.

Abstract: A compound helicopter with a fuselage and at least one main rotor that is at least adapted for generating lift in operation, the at least one main rotor being arranged in an upper region of the fuselage, wherein at least one propeller is provided that is at least adapted for generating forward and/or backward thrust in operation. The at least one propeller is mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing and at least one lower wing. An upper wing section arrangement is provided in the upper region of the fuselage, the at least one upper wing of the fixed wing arrangement being mounted to the upper wing section arrangement.

Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the c

Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.

Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, the at least one electrical engine being mounted to the carrier beam.

Abstract: A braced wing aircraft with a fuselage and a fixed wing arrangement, the fixed wing arrangement comprising at least two braced wings that are arranged laterally and opposite to each other on the fuselage, each one of the at least two braced wings comprising at least one upper wing and at least one lower wing which are staggered and interconnected at a predetermined transition region, the at least one upper wing being connected to the fuselage at an associated upper wing root and the at least one lower wing being connected to the fuselage at an associated lower wing root.

Abstract: An attachment for attaching an aircraft engine with a first receiving element to an aircraft structure with a second receiving element may include at least three fasteners and a stacked layer. Stacked layer may include at least two sheets, at least three holes through the stacked layer, a first connecting portion that includes a first hole of the at least three holes, a second connecting portion that includes second and third holes of the at least three holes, and a suspension portion that is located between the first connecting portion and the second connecting portion.

Abstract: A compound helicopter with a fuselage and at least one main rotor that is at least adapted for generating lift in operation, the at least one main rotor being arranged in an upper region of the fuselage, wherein at least one propeller is provided that is at least adapted for generating forward and/or backward thrust in operation. The at least one propeller is mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing and at least one lower wing. An upper stub wing arrangement is provided in the upper region of the fuselage, the at least one upper wing of the fixed wing arrangement being mounted to the upper stub wing arrangement.

Abstract: A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, and wherein a carrier beam is at least mounted at a leading edge region of the cylindrical air duct to the shrouding such that the carrier beam is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, the at least one electrical engine being mounted to the carrier beam.

Abstract: A braced wing aircraft with a fuselage and a fixed wing arrangement, the fixed wing arrangement comprising at least two braced wings that are arranged laterally and opposite to each other on the fuselage, each one of the at least two braced wings comprising at least one upper wing and at least one lower wing which are staggered and interconnected at a predetermined transition region, the at least one upper wing being connected to the fuselage at an associated upper wing root and the at least one lower wing being connected to the fuselage at an associated lower wing root.

Abstract: A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.

Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.

Abstract: An aircraft with a modular airframe. The modular airframe has a load carrying framework and at least one exchangeable covering item that exhibits a first predetermined shaping. The at least one exchangeable covering item is detachably mounted to the load carrying framework. The modular airframe is customizable by exchanging the at least one exchangeable covering item with a substitute exchangeable covering item that exhibits a second predetermined shaping.

Abstract: The invention provides, in one aspect, a system for recirculating ozonated liquid. The system includes a contactor including at least two inlets and at least two outlets. The contactor is in fluid communication with a first liquid source at a first contactor inlet and a second liquid source at a second contactor inlet, and the second contactor inlet receives gas that purges at least a portion of gas from liquid received at the first contactor inlet. The purged gas exits the contactor at a first contactor outlet. The contactor is in fluid communication with the second liquid source at a second contactor outlet, and the contactor drains at least a portion of the liquid in the contactor, the drained liquid exiting the contactor at the second contactor outlet. The contactor includes a third inlet in fluid communication with the first liquid source, the third inlet allowing the first liquid source to release liquid at an ambient pressure.

Abstract: A compound rotorcraft with a fuselage and at least one main rotor, the fuselage comprising a lower side and an upper side that is opposed to the lower side, the at least one main rotor being arranged at the upper side, wherein at least one propeller is provided and mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing that is arranged at an upper wing root joint area provided at the upper side of the fuselage and at least one lower wing that is arranged at a lower wing root joint area provided at the lower side of the fuselage, the upper and lower wings being at least interconnected at an associated interconnection region.

Abstract: The invention provides, in one aspect, a system for recirculating ozonated liquid. The system includes a contactor including at least two inlets and at least two outlets. The contactor is in fluid communication with a first liquid source at a first contactor inlet and a second liquid source at a second contactor inlet, and the second contactor inlet receives gas that purges at least a portion of gas from liquid received at the first contactor inlet. The purged gas exits the contactor at a first contactor outlet. The contactor is in fluid communication with the second liquid source at a second contactor outlet, and the contactor drains at least a portion of the liquid in the contactor, the drained liquid exiting the contactor at the second contactor outlet. The contactor includes a third inlet in fluid communication with the first liquid source, the third inlet allowing the first liquid source to release liquid at an ambient pressure.