Abstract: A hybrid electrical propulsion system, which comprises a mechanical load; a thermal engine; an electrical machine; a power transmission device comprising a first coupling device connected via a first connecting shaft to the thermal engine and via a second connecting shaft to a second coupling device; and a control system comprising a control logic to provide a setpoint command to the electrical machine. The first coupling device couples the first connecting shaft with the second connecting shaft in a driving manner if a first speed-dependent driving condition is fulfilled. The second coupling device couples a third connecting shaft with a drive shaft in a driving manner if the control logic provides the setpoint command for operating the electrical machine in motor mode and a second speed-dependent driving condition is fulfilled.

Abstract: A method of determining a remaining operating time of an electrical energy storage unit in an aircraft, comprising: using a first sensor arrangement for measuring first performance parameters of the electrical energy storage unit; determining first performance indicators based on the first performance parameters; using at least one second sensor arrangement for measuring second performance parameters of the electrical energy storage unit; determining second performance indicators based on the second performance parameters; comparing the first performance indicators with the second performance indicators to determine consolidated performance indicators; and determining predictive remaining operating times of the electrical energy storage unit based on the consolidated performance indicators, wherein the predictive remaining operating times comprise at least a predictive nominal remaining operating time and a predictive emergency remaining operating time.

Abstract: An electrical energy storage system for an aircraft, comprising at least one electrical energy storage unit with power supply lines and an energy source that is configured to store electrical energy and to supply electrical power at a predetermined voltage range via the power supply lines, wherein the at least one electrical energy storage unit comprises a power switching unit that is adapted to operate in an associated supply mode for supplying electrical power from the energy source via the power supply lines, and to operate in an associated disconnect mode for disconnecting the energy source from the power supply lines.

Abstract: An electrically powered rotary-wing aircraft with a first predetermined number of thrust producing units and a second predetermined number of batteries. Each one of the first predetermined number of thrust producing units may include a rotor, and an electrical drive unit with at least two electric motors. Each battery of the second predetermined number of batteries is coupled to at most one electric motor of the at least two electric motors of at least one of the first predetermined number of thrust producing units, and each electric motor of the at least one of the first predetermined number of thrust producing units is coupled to at most one of the second predetermined number of batteries.

Abstract: An electrical energy storage system for an aircraft, comprising at least one electrical energy storage unit with power supply lines and an energy source that is configured to store electrical energy and to supply electrical power at a predetermined voltage range via the power supply lines, wherein the at least one electrical energy storage unit comprises a power switching unit that is adapted to operate in an associated supply mode for supplying electrical power from the energy source via the power supply lines, and to operate in an associated disconnect mode for disconnecting the energy source from the power supply lines.

Abstract: An electrical system, and, more particularly, to an electrical system for an aircraft comprising one or more energy sinks and a hybrid energy storage system. The hybrid energy storage system may comprise one or more primary energy sources, a secondary energy source, and a secondary energy source control unit. The one or more primary energy sources may be coupled to and supply power to the one or more energy sinks. The secondary energy source may be coupled to the one or more primary energy sources and adapted to supply power at a variable output voltage to the one or more primary energy sources.

Abstract: An electrically powered rotary-wing aircraft with a first predetermined number of thrust producing units and a second predetermined number of batteries. Each one of the first predetermined number of thrust producing units may include a rotor, and an electrical drive unit with at least two electric motors. Each battery of the second predetermined number of batteries is coupled to at most one electric motor of the at least two electric motors of at least one of the first predetermined number of thrust producing units, and each electric motor of the at least one of the first predetermined number of thrust producing units is coupled to at most one of the second predetermined number of batteries.

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 at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.

Abstract: An electrical system, and, more particularly, to an electrical system for an aircraft comprising one or more energy sinks and a hybrid energy storage system. The hybrid energy storage system may comprise one or more primary energy sources, a secondary energy source, and a secondary energy source control unit. The one or more primary energy sources may be coupled to and supply power to the one or more energy sinks. The secondary energy source may be coupled to the one or more primary energy sources and adapted to supply power at a variable output voltage to the one or more primary energy sources.

Abstract: A multirotor aircraft with at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.

Abstract: A heater, in particular a high-temperature heater, for example for domestic heating appliances, in which a layer that produces heat when a current flows through is provided on a carrier material as a heating element, wherein a first electrically conductive layer which is formed from a free-flowing, non-electrically conductive base material and carbon nano tubes dispersed therein is applied to the carrier material, wherein a protective layer is applied to this first layer and at least partly penetrates into the first layer as it is applied, or wherein a functional layer with carbon nano tubes dispersed therein is applied to the carrier material, and wherein the at least one layer or the functional layer makes contact with strip-like contact elements, and the layers applied to the carrier material or the functional layer are heated.

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: A heater, in particular a high-temperature heater, for example for domestic heating appliances, in which a layer that produces heat when a current flows through is provided on a carrier material as a heating element, wherein a first electrically conductive layer which is formed from a free-flowing, non-electrically conductive base material and carbon nano tubes dispersed therein is applied to the carrier material, wherein a protective layer is applied to this first layer and at least partly penetrates into the first layer as it is applied, or wherein a functional layer with carbon nano tubes dispersed therein is applied to the carrier material, and wherein the at least one layer or the functional layer makes contact with strip-like contact elements, and the layers applied to the carrier material or the functional layer are heated.

Abstract: The invention relates to a method for producing a heater, in particular a high-temperature heater and also a high-temperature heater, for example for domestic heating appliances, in which a layer that produces heat when a current flows through is provided on a carrier material (12) as a heating element (14), wherein a first electrically conductive layer (16) which is formed from a free-flowing, non-electrically conductive base material and carbon nano tubes dispersed therein is applied to the carrier material (12), wherein a protective layer (17) is applied to this first layer (16) and at least partly penetrates into the first layer (14) as it is applied, or wherein a functional layer (21) with carbon nano tubes dispersed therein is applied to the carrier material (12), and wherein the at least one layer (16, 17) or the functional layer (21) makes contact with strip-like contact elements (18), and the layers (16, 17) applied to the carrier material or the functional layer (21) are heated.

Abstract: The invention relates to a method for producing a heater, in particular a high-temperature heater and also a high-temperature heater, for example for domestic heating appliances, in which a layer that produces heat when a current flows through is provided on a carrier material (12) as a heating element (14), wherein a first electrically conductive layer (16) which is formed from a free-flowing, non-electrically conductive base material and carbon nano tubes dispersed therein is applied to the carrier material (12), wherein a protective layer (17) is applied to this first layer (16) and at least partly penetrates into the first layer (14) as it is applied, or wherein a functional layer (21) with carbon nano tubes dispersed therein is applied to the carrier material (12), and wherein the at least one layer (16, 17) or the functional layer (21) makes contact with strip-like contact elements (18), and the layers (16, 17) applied to the carrier material or the functional layer (21) are heated.