Abstract: The invention relates to a drive train for a hybrid vehicle with an internal combustion engine, with a transmission and with an electric machine, wherein the electric machine is arranged between the internal combustion engine and the transmission. The drive train can be provided in a simple, economical and/or space-saving manner in that the transmission comprises at least one overrun-enabled forward gear transmitting traction torque only and at least one overrun-free forward gear. A hybrid vehicle can be operated with a drive train of this kind easily and efficiently in that, when an overrun-enabled forward gear transmitting only traction torque is engaged and while the vehicle speed lies below a certain engagement speed for an overrun-free forward gear and at least one criterion for the presence of a driving torque is established or satisfied, the transmission is shifted into the overrun-free forward gear.

Abstract: The invention relates to a drive train for a hybrid vehicle with an internal combustion engine, with a transmission and with an electric machine, wherein the electric machine is arranged between the internal combustion engine and the transmission. The drive train can be provided in a simple, economical and/or space-saving manner in that the transmission comprises at least one overrun-enabled forward gear transmitting traction torque only and at least one overrun-free forward gear. A hybrid vehicle can be operated with a drive train of this kind easily and efficiently in that, when an overrun-enabled forward gear transmitting only traction torque is engaged and while the vehicle speed lies below a certain engagement speed for an overrun-free forward gear and at least one criterion for the presence of a driving torque is established or satisfied, the transmission is shifted into the overrun-free forward gear.

Abstract: A trailing-edge flap system for a wing of an aircraft comprises a trailing-edge flap, a guide rail attached to the trailing-edge flap, a carriage slidably engaging the guide rail and rotatably attachable to a fixed position on the wing structure, and a drive means coupled the wing structure to a first joint on the guide rail. The drive means is configured to move the trailing-edge flap relative to the wing structure by moving the guide rail along the carriage by moving the first joint relative to the wing structure, such that the trailing-edge flap translates and rotates. The trailing-edge flap is at least movable into a cruise position, a high-lift position and an air brake position.

Abstract: A controllable hydraulic oscillating slide machine includes an inner rotor arranged in a housing and having cylindrical recesses. A bearing is formed in the housing, in which a co-rotating outer rotor is mounted eccentrically to the inner rotor, the outer rotor having several pivotably suspended slide drivers that engage into the recesses of the inner rotor for rotationally driving the outer rotor by way of the inner rotor and form modifiable chambers. The slide drivers may each be coupled to a piston that is guided in a respective associated recess. A pressure level different from that in the chambers between the inner and the outer rotor may be set in the chambers delimited by the recesses and the associated pistons so that two different pressure levels may be generated and two different consumers can be supplied using the oscillating slide machine.

Abstract: An air-sucking vehicle tail section component or wing section component includes an outer delimitation part having microperforation including boreholes, and inner delimitation part having a plurality of suction boreholes including fluid connections to the microperforation boreholes, and connecting elements. The inner delimitation part is connected via the connecting elements to the outer delimitation part. The outer delimitation part includes a continuously curved shape. The inner delimitation part includes two or more planar inner delimitation part components, which are each connected to one another at one edge to form a connection edge, and the connection edge is configured to be attached to the outer delimitation part. A type of framework structure is thus provided, which causes increased stability and can split impacting objects in particular if two inner delimitation part components are used on the vehicle tail section component or wing section component.

Abstract: A trailing-edge flap system for a wing of an aircraft comprises a trailing-edge flap, a guide rail attached to the trailing-edge flap, a carriage slidably engaging the guide rail and rotatably attachable to a fixed position on the wing structure, and a drive means coupled the wing structure to a first joint on the guide rail. The drive means is configured to move the trailing-edge flap relative to the wing structure by moving the guide rail along the carriage by moving the first joint relative to the wing structure, such that the trailing-edge flap translates and rotates. The trailing-edge flap is at least movable into a cruise position, a high-lift position and an air brake position.

Abstract: The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimize the natural vibration behavior of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behavior of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behavior of the structural element is optimized. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element.

Abstract: A controllable hydraulic oscillating slide machine includes an inner rotor arranged in a housing and having cylindrical recesses. A bearing is formed in the housing, in which a co-rotating outer rotor is mounted eccentrically to the inner rotor, the outer rotor having several pivotably suspended slide drivers that engage into the recesses of the inner rotor for rotationally driving the outer rotor by way of the inner rotor and form modifiable chambers. The slide drivers may each be coupled to a piston that is guided in a respective associated recess. A pressure level different from that in the chambers between the inner and the outer rotor may be set in the chambers delimited by the recesses and the associated pistons so that two different pressure levels may be generated and two different consumers can be supplied using the oscillating slide machine.

Abstract: The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimise the natural vibration behaviour of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behaviour of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behaviour of the structural element is optimised. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element.