Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: The invention describes carbon fibers which are produced on the basis of different process chains from CO2. These include routes through natural resources such as algal biomass to produce carbon fiber precursors such as PAN from CO2, as well as the purely synthetic route via the Fischer-Tropsch synthesis, which is also used to make CO2 carbon fiber precursors. In this way, CO2 from anthropogenic origin is to be converted into a solid aggregate state of carbon fiber, which can be disposed of at the end of its life cycle, after being used as highly valuable building material for industry and man, for the construction of buildings and vehicles. These processes produce by-products such as biodiesel and nutrients that generate added value. The production volumes of the resulting substances should be controllable by combining the methods presented here.

Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: A transportable device for heating food is provided. The device includes a container for receiving the food, a heating compartment, which is thermally coupled to the container by way of a heat-conducting wall, calcium oxide being present in the heating compartment, and a liquid supply unit including a liquid reservoir chamber, in which a water-containing liquid is present, wherein the liquid supply unit is designed so that, based on actuation on the part of a user, the water-containing liquid is brought into contact with the calcium oxide, or the substance mixture including calcium oxide. The water-containing liquid has an elevated dynamic viscosity, in comparison with water, of between 2 and 30000 mPas, and preferably between 50 and 1000 mPas or, alternatively, the liquid supply unit comprises a water retention agent. In both alternatives, the reaction between calcium oxide and water is damped and delayed.

Abstract: The invention describes carbon fibers which are produced on the basis of different process chains from CO2. These include routes through natural resources such as algal biomass to produce carbon fiber precursors such as PAN from CO2, as well as the purely synthetic route via the Fischer-Tropsch synthesis, which is also used to make CO2 carbon fiber precursors. In this way, CO2 from anthropogenic origin is to be converted into a solid aggregate state of carbon fiber, which can be disposed of at the end of its life cycle, after being used as highly valuable building material for industry and man, for the construction of buildings and vehicles. These processes produce by-products such as biodiesel and nutrients that generate added value. The production volumes of the resulting substances should be controllable by combining the methods presented here.

Abstract: A method for detecting damages to a rotor of an aircraft, where the aircraft comprises actuators for active vibration reduction, may comprising one or more of the following steps: determining actuator variables in a reference flight of the aircraft; plotting the actuator variables of respective data range tiles determined in the reference flight of the aircraft in first coordinates of a coordinate system, wherein the coordinate system contains numerous data range tiles; obtaining the number of actuator variables in the reference flight of the aircraft that are located in each data range tile; eliminating the data range tiles that have a number of actuator variables lying below a limit value for this in the reference flight of the aircraft, by means of which a reference flight signature is created; and determining actuator variables for a flight-specific signature.

Abstract: An actuator for aviation may include an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: A method for detecting damages to a rotor of an aircraft, where the aircraft comprises actuators for active vibration reduction, may comprising one or more of the following steps: determining actuator variables in a reference flight of the aircraft; plotting the actuator variables of respective data range tiles determined in the reference flight of the aircraft in first coordinates of a coordinate system, wherein the coordinate system contains numerous data range tiles; obtaining the number of actuator variables in the reference flight of the aircraft that are located in each data range tile; eliminating the data range tiles that have a number of actuator variables lying below a limit value for this in the reference flight of the aircraft, by means of which a reference flight signature is created; and determining actuator variables for a flight-specific signature.

Abstract: A transportable device for heating food is provided. The device includes a container for receiving the food, a heating compartment, which is thermally coupled to the container by way of a heat-conducting wall, calcium oxide being present in the heating compartment, and a liquid supply unit including a liquid reservoir chamber, in which a water-containing liquid is present, wherein the liquid supply unit is designed so that, based on actuation on the part of a user, the water-containing liquid is brought into contact with the calcium oxide, or the substance mixture including calcium oxide. The water-containing liquid has an elevated dynamic viscosity, in comparison with water, of between 2 and 30000 mPas, and preferably between 50 and 1000 mPas or, alternatively, the liquid supply unit comprises a water retention agent. In both alternatives, the reaction between calcium oxide and water is damped and delayed.

Abstract: The invention relates to carbon fibers which are produced from CO2 based on different process chains. Amongst these, there are ways to produce, from natural base materials such as algal biomass, carbon fibre base materials such as PAN from CO2, but there are also purely artificial ways to produce, by means of Fischer-Tropsch synthesis, via which carbon fibre precursors are also produced from CO2. Auxiliary products such as biodiesel and nutrients, which can generate an additional benefit, are produced according to said method.

Abstract: An actuator for aviation may include an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: An actuator for a rotor blade adjustment having an electromechanical drive unit may be connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: A transportable device for heating foodstuffs includes a container for receiving the foodstuff as well as a closed-off heating chamber which adjoins the container and is thermally coupled thereto while simultaneously being hermetically separated therefrom via a shared, thermally-conductive wall. The heating chamber includes a first chamber and a second chamber that are separated by a water vapor-permeable wall. In the first chamber is a substance or a substance mixture which, when a liquid, preferably water, is supplied, generates heat in an exothermic chemical reaction with water vapor being formed. In the second chamber, a zeolite is located which can adsorb the water entering from the first chamber via said water vapor-permeable wall, generating heat. A transportable heating element which can be used in the device contains a hermetically-sealed heating chamber that adjoins a thermally-dissipating outer wall.

Abstract: A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades.

Abstract: The present disclosure provides a rotor blade control device for a helicopter. The rotor blade control device may include a swash plate disk with a non-rotating component coupled to the helicopter. At least three actuators may be arranged around a rotor shaft axis of the helicopter, and a coupling element may be located between each actuator and the non-rotating component. The coupling element can be adjusted to change the position of a crosspoint at the non-rotating component of the swash plate disk alongside the rotor shaft axis in order to adjust the rotor blades. The actuators may be arranged onto the non-rotating component and may be able to pivot around a respective swivel axis. A radial distance of the first crosspoint to the rotor shaft axis may change with the swivel movement of an actuator around the swivel axis.

Abstract: The present embodiments provide an actuator for a rotor blade adjustment having an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: A control rod configuration for adjusting a position of a rotor blade of a helicopter. The control rod configuration includes a control rod which has a bearing eye, adjacent the swash plate, which is penetrated by an axle shaft which has a bearing supported by a bearing bracket. The control rod configuration, which can be simply constructed and is less susceptible to malfunction, has an eccentric with its pivotable bearing in the bearing bracket and which is provided between the bearing bracket and the bearing eye. In addition, a method in which a rotor blade of a helicopter has an assigned control rod which is supported by an axle shaft with a bearing in the bearing bracket which is mounted to the swash plate so as to enable adjustment of the control rod by pivoting the axle shaft during flight.

Abstract: A transportable device for heating foodstuffs includes a container for receiving the foodstuff as well as a closed-off heating chamber which adjoins the container and is thermally coupled thereto while simultaneously being hermetically separated therefrom via a shared, thermally-conductive wall. The heating chamber includes a first chamber and a second chamber that are separated by a water vapour-permeable wall. In the first chamber is a substance or a substance mixture which, when a liquid, preferably water, is supplied, generates heat in an exothermic chemical reaction with water vapour being formed. In the second chamber, a zeolite is located which can adsorb the water entering from the first chamber via said water vapour-permeable wall, generating heat. A transportable heating element which can be used in the device contains a hermetically-sealed heating chamber that adjoins a thermally-dissipating outer wall.

Abstract: A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades.

Abstract: Rotor blade control device for a helicopter, consisting of a swash plate disk, the swash plate disk consisting of a non-rotating part of the swash plate disk, which is stationary stationarily coupled to the helicopter, a rotating part of the swash plate disk, at least three actuators which are arranged around a rotor shaft axis of the helicopter, a coupling element between actuator and the non-rotating part of the swash plate disk. The coupling element can be adjusted in its tilt, in order to change the position of the crosspoint at the non-rotating part of the swash plate disk alongside the rotor shaft axis by means of the actuator through a control shaft, in order to adjust the rotor blades. Here, the coupling element is made up in a rigid way, and the actuators are arranged onto the stationary component being able to pivot around a respective swivel axis.