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: 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: 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: 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.

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: An electric power apparatus is disclosed for use in powering an electric vehicle with an exhaust channel. The electric power apparatus can include a battery housing and multiple cell tubes. The multiple cell tubes can support multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells may be positioned within individual of the multiple cell tubes. The multiple cell tubes can be supported by the battery housing and direct combustion components from any fires in the multiple battery cells in a common direction. The multiple battery cells can each be self-contained and removable from the multiple cell tubes. The multiple battery cells can be electrically connected to power a motor that propels a vehicle housing, and the vehicle housing can support the battery housing and the motor.

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: This disclosure describes at least embodiments of a power management system for a vehicle. The vehicle can include a first transducer and a second transducer supported by a housing of the vehicle. The first transducer can be powered by a first battery, and the second transducer can be powered by a second battery different from the first battery. The first transducer and the second transducer can propel the housing, and the second transducer can charge the second battery. Electronic circuitry can cause the first battery to power the first transducer while the second transducer charges the second battery.

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 circuit can include a CAN bus and multiple nodes. The multiple nodes can reboot at the same time so that a Time 0 is set at boot for each node. Each node can store an ID node and determine from its ID node one time slot of a plurality of periodic time slots starting from Time 0 in which to transmit on the CAN bus. Each node can transmit messages on the CAN bus in its determined time slot subsequent to Time 0.