Abstract: A power supply system can include an electrical power source and a power converter connectable to a load. The electrical power source can provide a first DC voltage with a first potential difference (VH) between a first DC potential output and a second DC potential output, and a third DC potential output having a potential between the potential at the first DC potential output and the potential at the second DC potential output. The power converter can provide a second voltage with a second potential difference (VL) between a first potential output (V+) and a second potential output (V?). The second potential difference (VL) can be less than the first potential difference (VH). The power converter can electrically isolate the first DC voltage from the second voltage, and the second potential output (V?) can be connected to the third DC potential output using a first connection including an impedance.

Abstract: A battery module for an electrically-driven aircraft is disclosed. The battery module can house multiple battery cells and prevent a battery cell fire or explosion from one battery cell from damaging neighboring battery cells. The battery module includes: a housing; a plurality of cell tubes housing a plurality of battery cells, each cell tube having an elongated surface and being positioned in the housing spaced apart from each other; a heat absorbing member comprising a heat absorbing material, wherein the heat absorbing member is arranged between at least two neighboring cell tubes; and the heat absorbing material being configured to undergo a phase transition from an initial state of matter into a final state of matter when at least one of the plurality of cell tubes exceeds a predetermined temperature in case of explosion or fire of at least one of the plurality of battery cells.

Abstract: The present disclosure describes at least a coupling circuit for powering an electric or hybrid aircraft with an output voltage. The couple circuit can include multiple connecting inputs, a charging interface, a connecting output, a high-power diodes arrangement, and a pre-charge circuit. The multiple connecting inputs can connect multiple battery packs. The charging interface can connect to a charger for charging the multiple battery packs. The connecting output can connect with a hardware controller. The high-power diodes arrangement can electrically connect to each respective connecting input and the charging interface. The high-power arrangement can include for each battery pack a first high-power diode and a second high-power diode. The pre-charge circuit can electrically connect to the high-power diode arrangement. The pre-charge circuit can include a first branch with a first switch, and a second branch in parallel with the first branch.

Abstract: A battery module can include multiple battery cells, multiple cell tubes, and a first plate. The multiple cell tubes can accommodate the multiple battery cells within the plurality of cell tubes so that individual of the plurality of battery cells are positioned within individual of the plurality of cell tubes. Each battery cell can have a first electric pole and a second electric pole. The first plate can include a printed circuit board. The printed circuit board can include a first conductive layer and an isolating layer. The isolating layer can include at least one blind hole for wire-bonding the conductive layer to one of the battery cells.

Abstract: This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

Abstract: A blower spray device is provided having a housing which comprises an electrically driven blower and a spray nozzle, and having a liquid supply line opening into the spray nozzle. The housing has a funnel-shaped intake channel and a tubular blow-out channel, and an electrical valve is provided in the liquid supply line to activate and deactivate the liquid supply to the spray nozzle. An electronic controller having a regulating unit for the electric blower is further provided to adjust the air flow velocity.

Abstract: A power supply system can include an electrical power source and a power converter connectable to a load. The electrical power source can provide a first DC voltage with a first potential difference (VH) between a first DC potential output and a second DC potential output, and a third DC potential output having a potential between the potential at the first DC potential output and the potential at the second DC potential output. The power converter can provide a second voltage with a second potential difference (VL) between a first potential output (V+) and a second potential output (V-). The second potential difference (VL) can be less than the first potential difference (VH). The power converter can electrically isolate the first DC voltage from the second voltage, and the second potential output (V-) can be connected to the third DC potential output using a first connection including an impedance.

Abstract: A battery module can include multiple battery cells, multiple cell tubes, and a first plate. The multiple cell tubes can accommodate the multiple battery cells within the plurality of cell tubes so that individual of the plurality of battery cells are positioned within individual of the plurality of cell tubes. Each battery cell can have a first electric pole and a second electric pole. The first plate can include a printed circuit board. The printed circuit board can include a first conductive layer and an isolating layer. The isolating layer can include at least one blind hole for wire-bonding the conductive layer to one of the battery cells.

Abstract: This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

Abstract: This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of components, such as a power source for powering an electric motor, of the electric or hybrid aircraft. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

Abstract: The present disclosure describes at least a coupling circuit for powering an electric or hybrid aircraft with an output voltage. The couple circuit can include multiple connecting inputs, a charging interface, a connecting output, a high-power diodes arrangement, and a pre-charge circuit. The multiple connecting inputs can connect multiple battery packs. The charging interface can connect to a charger for charging the multiple battery packs. The connecting output can connect with a hardware controller. The high-power diodes arrangement can electrically connect to each respective connecting input and the charging interface. The high-power arrangement can include for each battery pack a first high-power diode and a second high-power diode. The pre-charge circuit can electrically connect to the high-power diode arrangement. The pre-charge circuit can include a first branch with a first switch, and a second branch in parallel with the first branch.

Abstract: A battery module can include multiple cell tubes, a first conductive plate, and multiple first spacers. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The first conductive plate can include multiple first holes and electrically connect first terminals of the multiple cells. The multiple first spacers can be mounted in the multiple first holes and support the multiple tubes and the multiple cells with respect to the first conductive plate, the multiple first spacers being configured to provide thermal and electrical isolation between the multiple battery cells and the first conductive plate.

Abstract: A battery module can include multiple cell tubes and a conductive plate. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The conductive plate can include a printed circuit board. The printed circuit board can include a first conductive layer and an isolating layer. The isolating layer can include a blind hole through which a wire bonding extends. The wire bonding can be electrically connected to the first conductive layer.

Abstract: This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

Abstract: A battery module can include multiple cell tubes, a first conductive plate, and multiple first spacers. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The first conductive plate can include multiple first holes and electrically connect first terminals of the multiple cells. The multiple first spacers can be mounted in the multiple first holes and support the multiple tubes and the multiple cells with respect to the first conductive plate, the multiple first spacers being configured to provide thermal and electrical isolation between the multiple battery cells and the first conductive plate.

Abstract: A battery module can include multiple cell tubes and a conductive plate. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The conductive plate can include a printed circuit board. The printed circuit board can include a first conductive layer and an isolating layer. The isolating layer can include a blind hole through which a wire bonding extends. The wire bonding can be electrically connected to the first conductive layer.

Abstract: This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of components, such as a power source for powering an electric motor, of the electric or hybrid aircraft. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

Abstract: A battery module can include multiple cell tubes, a first conductive plate, and multiple first spacers. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The first conductive plate can include multiple first holes and electrically connect first terminals of the multiple cells. The multiple first spacers can be mounted in the multiple first holes and support the multiple tubes and the multiple cells with respect to the first conductive plate, the multiple first spacers being configured to provide thermal and electrical isolation between the multiple battery cells and the first conductive plate.

Abstract: This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

Abstract: This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of components, such as a power source for powering an electric motor, of the electric or hybrid aircraft. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.