Abstract: A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

Abstract: A method for operating an at least temporarily unmanned aircraft, wherein a flight is performed according to a prior flight plan in an airspace controlled by a control instance. A flight direction is determined during the flight via a control device influenced via a data connection by a control instance. The data connection is temporarily unavailable, and a hazardous or emergency situation requiring deviation from the flight plan, is identified by the control device based on first sensor data. An avoidance route is determined by the control device based on a second sensor data, the avoidance route including a avoidance manoeuvre avoiding the hazardous or emergency situation, the avoidance route is used in the meantime to fly towards a destination area with the least possible volume of air traffic; and the necessary avoidance manoeuvre(s) are performed based on the second data by the control device in an autonomous staggering procedure.

Abstract: A cooling system containing a two-phase refrigerant that comprises a condenser, an evaporator and a conveying device. The evaporator is integrated in a heat source or thermally coupled thereto. Gaseous refrigerant from the evaporator is expanded in an expander, converted into mechanical energy and used to drive a generator for generation of electricity. Furthermore, an aircraft comprising a cooling system, wherein an electrical drive is supplied with electricity from a fuel cell, cooled using the cooling system, and the generator of the cooling system.

Abstract: An energy recovery assembly, fuel cell system and vehicle, with an electrolyzer configured to provide a fuel and an oxidant, a fuel cell configured to convert the fuel and an oxidant to electrical energy, a tank configured to store the fuel or the oxidant, and a conduction pathway connecting the tank to the electrolyzer and the fuel cell. The assembly also includes: an expansion machine disposed in the conduction pathway and configured to expand a fluid flowing through the expansion machine and to obtain mechanical energy; and a valve arrangement configured to put the pathway in a first mode in which the fuel or the oxidant is guided to the tank, or in a second mode in which the fuel cell or the oxidant is guided to the fuel cell, wherein the fuel or the oxidant in the first and second modes flows through the expansion machine.

Abstract: A bipolar plate for use in an electrochemical device is proposed, in which a flow duct runs between two outer boundary surfaces and extends from a peripheral fluid inlet to a peripheral fluid outlet. As a result, very good cooling of electrochemical cells via a bipolar plate which is in surface contact therewith can be achieved.

Abstract: Matrix cells are used to improve the regeneration capacity of an electrolyzer system. The electrolyte is electrolyzed in the matrix cell. Gas (predominantly product gas) which has unwantedly accessed the electrolyte space is transported off from the electrolyte space into the gas space envisioned therefor by a degassing device. Additional measures such as ultrasonic transducers and field electrodes may realize electrolyte flow and improved transporting-off of gas.

Abstract: A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid tank.

Abstract: A device for carrying fuel in aircraft and spacecraft includes a carrier element having a longitudinal axis, and a fuel tank with a side wall and a chamber at least partially delimited by the side wall. The tank is arranged in the carrier element. The chamber and the side wall extend in a direction along the longitudinal axis. The side wall has a pressure-receiving component that converts a pressure from the chamber on the side wall into a contraction force acting on the side wall along the longitudinal axis. The contraction force compensates for an expansion force, resulting from the pressure from the chamber and acting on the side wall along the longitudinal axis. This provides an improved device for carrying fuel in aircraft and spacecraft, wherein the aircraft and spacecraft has constant flight mechanical properties because of the device.

Abstract: A cooling system containing a two-phase refrigerant that comprises a condenser, an evaporator and a conveying device. The evaporator is integrated in a heat source or thermally coupled thereto. Gaseous refrigerant from the evaporator is expanded in an expander, converted into mechanical energy and used to drive a generator for generation of electricity. Furthermore, an aircraft comprising a cooling system, wherein an electrical drive is supplied with electricity from a fuel cell, cooled using the cooling system, and the generator of the cooling system.

Abstract: A device for checking the consistency of a positioning includes: a transmitter, a receiver, a time measuring unit, a distance determining module and a check module. The transmitter emits at least one signal, and the receiver receives at least four response signals from at least four different response elements. A response element receives the at least one signal and, upon receipt, emits a response signal. The time measuring unit determines, for each response signal, a total delay time from a transmission time of the signal and a reception time of the respective signal. The distance determination module determines a distance to the respective response element based on each total delay time, and the check module performs a consistency check of a determination of a position based on distances to the different response elements. With the device, erroneous distance values may be detected in ground-based positioning systems.

Abstract: An energy management system for an aircraft, wherein the energy management system comprises a fuel cell configured to convert chemical energy into electric energy, at least one energy source configured to provide electric energy, at least one electrical load, an electric bus electrically coupled to the fuel cell, the at least one energy source, and the at least one electrical load, and a controller configured to control the at least one electrical load in such a manner that a minimum load to the fuel cell is ensured. Furthermore, an aircraft comprises such energy management system. A method for managing energy in a system comprises electrically coupling a fuel cell, at least one energy source, and at least one electrical load by an electric bus, and controlling at least one electrical load in such a manner that a minimum load to the fuel cell is ensured.

Abstract: An energy management system for an aircraft, wherein the energy management system comprises a fuel cell configured to convert chemical energy into electric energy, at least one energy source configured to provide electric energy, at least one electrical load, an electric bus electrically coupled to the fuel cell, the at least one energy source, and the at least one electrical load, and a controller configured to control the at least one electrical load in such a manner that a minimum load to the fuel cell is ensured. Furthermore, an aircraft comprises such energy management system. A method for managing energy in a system comprises electrically coupling a fuel cell, at least one energy source, and at least one electrical load by an electric bus, and controlling at least one electrical load in such a manner that a minimum load to the fuel cell is ensured.

Abstract: A method for operating an at least temporarily unmanned aircraft, wherein a flight is performed according to a prior flight plan in an airspace controlled by a control instance. A flight direction is determined during the flight via a control device influenced via a data connection by a control instance. The data connection is temporarily unavailable, and a hazardous or emergency situation requiring deviation from the flight plan, is identified by the control device based on first sensor data. An avoidance route is determined by the control device based on a second sensor data, the avoidance route including a avoidance manoeuvre avoiding the hazardous or emergency situation, the avoidance route is used in the meantime to fly towards a destination area with the least possible volume of air traffic; and the necessary avoidance manoeuvre(s) are performed based on the second data by the control device in an autonomous staggering procedure.

Abstract: Disclosed is a device for carrying fuel in aircraft and spacecraft. The device includes a carrier element having a longitudinal axis, and a fuel tank with a side wall and a chamber at least partially delimited by the side wall. The tank is arranged in the carrier element. The chamber and the side wall extend in a direction along the longitudinal axis. The side wall has a pressure-receiving component that converts a pressure from the chamber on the side wall into a contraction force acting on the side wall along the longitudinal axis. The contraction force compensates for an expansion force, resulting from the pressure from the chamber and acting on the side wall along the longitudinal axis. This provides an improved device for carrying fuel in aircraft and spacecraft, wherein the aircraft and spacecraft has constant flight mechanical properties because of the device.

Abstract: A bipolar plate for use in an electrochemical device is proposed, in which a flow duct runs between two outer boundary surfaces and extends from a peripheral fluid inlet to a peripheral fluid outlet. As a result, very good cooling of electrochemical cells via a bipolar plate which is in surface contact therewith can be achieved.

Abstract: A method for autonomous controlling of a remote controlled aerial vehicle, wherein a flight operator commands the aerial vehicle, comprising the steps of: initializing a data link between the aerial vehicle and a ground segment; determining an operation condition of the data link during use of the data link; and issuing at least one autonomous controlling command, if, as a result of the determining, a loss of the data link is determined.

Abstract: A method for operating an, at least temporarily, unmanned aircraft or spacecraft wherein a flight procedure of the aircraft or spacecraft is carried out in controlled airspace using a previously cleared flight plan, wherein a C2 link is at least temporarily unavailable, and wherein at least one sensor device of the aircraft or spacecraft identifies a dangerous and/or emergency situation which makes it necessary to deviate from the cleared flight plan. To have available a method which makes it possible for an at least temporarily unmanned aircraft or spacecraft to react independently to particular dangerous and/or emergency situations and to avoid damaging events, a control device of the aircraft or spacecraft independently uses a wireless data link to a supervisory authority in order to agree to a changed flight plan containing at least one change.

Abstract: An aircraft fuel system comprises a fuselage tank and wing fuel tanks each connected to the fuselage fuel tank by a respective fuel line. A first fuel line connects the fuselage fuel tank to a collector fuel tank, which is connected by second fuel lines to aircraft engines in use of the system. Unspent fuel output from the aircraft engines is returned to the collector fuel tank via third fuel lines. A fuel line arrangement is arranged to draw fuel from, and return that fuel to, the wing fuel tanks. Fuel within the third fuel lines is thermally coupled to fuel within the fuel line arrangement by a heat exchanger. Heat energy within unspent fuel output from the aircraft engines is transferred to the wing fuel tanks, reducing the likelihood of fuel freezing within these tanks during extended flying in cold environments.

Abstract: A device for checking the consistency of a positioning includes: a transmitter, a receiver, a time measuring unit, a distance determining module and a check module. The transmitter emits at least one signal, and the receiver receives at least four response signals from at least four different response elements. A response element receives the at least one signal and, upon receipt, emits a response signal. The time measuring unit determines, for each response signal, a total delay time from a transmission time of the signal and a reception time of the respective signal. The distance determination module determines a distance to the respective response element based on each total delay time, and the check module performs a consistency check of a determination of a position based on distances to the different response elements. With the device, erroneous distance values may be detected in ground-based positioning systems.

Abstract: A method for an aircraft for handling potential collisions in air traffic includes providing by a collision avoidance system a collision avoidance maneuver to avoid a collision with one or more intruders. The collision avoidance system is configured to obtain information about these intruders. The method includes further providing flight management constraints from an onboard flight system. Further, the method includes providing flight situation data from a navigation system. The method includes generating a modified collision avoidance maneuver based on the collision avoidance maneuver provided by the collision avoidance system, the flight situation data and the flight management constraints.