Patent classifications
B60L3/0092
POWER SOURCE SYSTEM
A power source system includes a first power source, a second power source, a Direct Current to Direct Current converter, a first load including a vehicle control device configured to perform predetermined control regarding at least one of traveling, steering, and braking of the vehicle regardless of a driving operation performed by a driver of the vehicle, and an electric actuator as a control target of the vehicle control device, and connected to the first path so as to be supplied with power from the first power source, and a power source control device configured to control an operation of the Direct Current to Direct Current converter such that power is supplied to the first path from the second power source in a case where the predetermined control is performed.
ON-BOARD POWER SYSTEM FOR A MOTOR VEHICLE, AND METHOD FOR OPERATING AN ON-BOARD POWER SYSTEM
The present disclosure relates to an on-board electrical network for a motor vehicle. The motor vehicle comprises a battery cell unit configured as a so-called SmartCell. The on-board electrical network also comprises a controller for operating the battery cell unit. In order to be able to be supplied with electric energy, the controller comprises a supply connection for supplying a supply voltage. The supply voltage is usually supplied by an energy supply device of the on-board electrical network, which is coupled to the controller via a first connection line. In order to allow for a redundant energy supply for the controller, a second connection line is provided in addition to the first connection line, via which a battery cell of the respective battery cell unit is coupled to the supply connection. The supply voltage can thus be supplied either via the first connection line or via the second connection line on the basis of an operating state of the energy supply device.
Systems and methods for a battery management system integrated in a battery pack configured for use in electric aircraft
A battery management and monitoring system integrated in a battery pack configured for use in electric aircraft. The system includes a sensor suite configured to measure a plurality of battery pack data. The system includes a battery monitoring component configured to detect a first fault in the battery pack and produce a first fault detection response notifying a user of the first fault in the battery pack. The system includes a battery management component configured to detect a second fault in the battery pack and produce a second fault detection response configured to mitigate the second fault in the battery pack. The system includes an interlock component having a first mode and a second mode, configured to enable the battery monitoring component and disable the battery management component when in the first mode and enable the battery management component and disable the battery monitoring component when in the second mode.
Torque-equalizing fault response for loss of low voltage DC electrical power in electric vehicle
An illustrative dual power inverter module includes a detection circuit configured to detect loss of low voltage DC electrical power supplied to a controller for a first power inverter and a second power inverter of a drive unit for an electric vehicle. A first backup power circuit is associated with the first power inverter and a second backup power circuit is associated with the second power inverter. Each backup power circuit is configured to convert high voltage DC electrical power to low voltage DC electrical power responsive to detection of loss of low voltage DC electrical power supplied to the controller. Three-phase short circuitry is configured to apply a same fault action to the first power inverter and the second power inverter responsive to detection of loss of low voltage DC electrical power supplied to the controller, wherein the same fault action includes applying equalized torque to each axle operatively coupled to the drive unit.
MOTOR DRIVE DEVICE AND ELECTRIC POWER STEERING DEVICE
A motor drive device includes a plurality of control systems that individually supply drive currents to a plurality of coil groups included in a motor. The motor drive device independently sets the current command values for the respective control systems. Based on the set current command values, drive instructions are supplied to drive circuits of inverters with respect to the respective control systems, thereby supplying drive currents from the inverters to the coil groups. The motor drive device detects a failure in any of the inverters and the coil groups with respect to each control system, and stops only the failed control system or causes only the failed control system to fall back. The motor drive device further includes a main computing device, and an auxiliary computing device. Consequently, if the auxiliary computing device is normal even in case the main computing device fails, driving of the motor can be continued using one or some of the control systems.
METHOD AND APPARATUS FOR CONTROLLING DISTRIBUTED PROPULSION SYSTEMS
A hierarchical vehicle control system for a vehicle powered by a distributed propulsion system (DPS) comprising plurality of propelling axles driven by plurality of motors and powered by a battery system comprising plurality of battery packs. Said hierarchical vehicle control system comprising a first controller, a second controller that generates axle command signals for operation of the propelling axles, and a third controller that generates motor command signals for operation of the electric motors wherein said third controller further comprising a DPS diagnosis/prognosis module, a DPS fault tolerance module and a power distribution management module.
FLIGHT CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT
A system and method for flight control of an aircraft, the flight control system including a plurality of flight components coupled to an aircraft, wherein the plurality of flight components includes a plurality of redundant control surfaces, a plurality of redundant low voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low voltage bus of the plurality of redundant low voltage busses does not impact the operability of the aircraft.
SYSTEMS AND METHODS FOR A BATTERY MANAGEMENT SYSTEM INTEGRATED IN A BATTERY PACK CONFIGURED FOR USE IN ELECTRIC AIRCRAFT
A battery management and monitoring system integrated in a battery pack configured for use in electric aircraft. The system includes a sensor suite configured to measure a plurality of battery pack data. The system includes a battery monitoring component configured to detect a first fault in the battery pack and produce a first fault detection response notifying a user of the first fault in the battery pack. The system includes a battery management component configured to detect a second fault in the battery pack and produce a second fault detection response configured to mitigate the second fault in the battery pack. The system includes an interlock component having a first mode and a second mode, configured to enable the battery monitoring component and disable the battery management component when in the first mode and enable the battery management component and disable the battery monitoring component when in the second mode.
Control schemes and intelligent battery selection for electric vehicles
Systems and methods are disclosed for control schemes and intelligent battery selection for electric vehicles. In one embodiment, an example method may include determining a first charge level of a first battery system that is configured to power a homopolar generator, causing the first battery system to be charged by a power input source, and determining that a second charge level of the first battery system is greater than a first threshold value. Example methods may include causing the first battery system to power the homopolar generator, wherein the homopolar generator is configured to output charging current to a second battery system, causing the solid state relay to form a parallel connection between a first battery, a second battery, and the homopolar generator, directing a first charging current from the homopolar generator to the first battery, and directing a second charging current from the homopolar generator to the second battery.
ONBOARD BATTERY CHARGING SYSTEM
Unique systems, methods, techniques and apparatuses of onboard battery charger systems are disclosed. One exemplary embodiment is a battery charging system comprising an isolation device and an electric vehicle charger. The isolation device includes an AC input terminal; an AC output terminal; two DC output terminals; a first portion of a detection circuit including a first sensor and a first resistor coupled in series; and a first controller. The charger includes an AC input terminal; two DC input terminals; and a second portion of the detection circuit including a second sensor and a second resistor coupled in series. The first controller is structured to isolate the AC input terminal of the isolation device from the AC output terminal of the isolation device when the two DC input terminals of the electric vehicle charger are not coupled to the two DC output terminals of the isolation device.