Aurora Flight Sciences Corporation

The present disclosure relates to a reconfigurable battery system and method of operating the same. An example apparatus includes at least one memory, instructions in the apparatus, and processor circuitry to execute the instructions to determine a state of charge of a battery, determine a closed circuit voltage of the battery, determine a value of a parameter based on a ratio of the state of charge and the closed circuit voltage, and control a switch coupled to the battery based on the value of the parameter, the controlling of the switch to either cause the battery to be coupled to a battery string or cause the battery to be disconnected from the battery string.

The present disclosure relates to a reconfigurable battery system and method of operating the same. An example apparatus includes at least one memory, instructions in the apparatus, and processor circuitry to execute the instructions to determine a state of charge of a battery, determine a closed circuit voltage of the battery, determine a value of a parameter based on a ratio of the state of charge and the closed circuit voltage, and control a switch coupled to the battery based on the value of the parameter, the controlling of the switch to either cause the battery to be coupled to a battery string or cause the battery to be disconnected from the battery string.

Technology segments an input flight path into segments based on terrain data, identifies target altitude heights of endpoints of the segments based on the terrain data and a target cruise altitude of an aircraft, identifies local maximas associated with the segments that are arranged in an order along the input flight path, identifies one or more local maximas of the local maximas that represent a dip in altitude from a previous one or more of the local maximas, removes the one or more local maximas from the plurality of local maximas to generate a reduced list of local maximas, sets a plurality of waypoints as the endpoints and the local maximas in the reduced list of local maximas, generates a flight path based at least in part on the plurality of waypoints, and causes the flight path to be provided to the at aircraft.

Waterjet cutting apparatus and related methods are disclosed herein. An example apparatus includes a tank defining a volume to contain a fluid therein, a fixture extending from the tank, and a tube extending from the tank, the tube to isolate the fixture and a part supported by the fixture from turbulence of the fluid disposed in the tank.

A system for facilitating navigation of an aircraft comprises one or more processors and a memory coupled to the processors. The memory stores data into a data store and program code that, when executed by the processors, causes the system to detect an infrared site signal indicating a site code transmitted by one or more infrared beacons that form a beacon network around a site. The site code represents a site. In response to detecting the infrared site signal, the system determines the site indicated by the site code. The system searches for two or more infrared beacon signals and detects the two or more infrared beacon signals. In response to detecting the two or more infrared beacon signals, the system determines a location of the aircraft based on the two or more infrared beacon signals.

A method is provided for supporting a robot in response to a contingency event. The method includes detecting the contingency event during travel of the robot on a route to a destination. In response, the method includes determining a position of the robot, and accessing information about alternate destinations associated with the route. The method includes selecting an alternate destination from the alternate destinations based on a time to travel from the position of the robot to the alternate destination, and the information. And the method includes outputting an indication of the alternate destination for use in at least one of guidance, navigation or control of the robot to the alternate destination.

In an example, a rotor for an electric motor includes an inner hub, an outer rim, and a plurality of slats. Each slat of the plurality of slats has a first end at the inner hub and a second end at the outer rim. The rotor is configured to drive a plurality of propeller blades that provide force for an aerial vehicle. Additionally or alternatively, a rotor for an electric motor includes a housing that includes a first retaining structure and a second retaining structure that are configured to apply a force that is directed radially outward against a magnet to hold the magnet against the housing. The rotor is configured to drive a plurality of propeller blades that provide force for an aerial vehicle.

Technology segments an input flight path into segments based on terrain data, identifies target altitude heights of endpoints of the segments based on the terrain data and a target cruise altitude of an aircraft, identifies local maximas associated with the segments that are arranged in an order along the input flight path, identifies one or more local maximas of the local maximas that represent a dip in altitude from a previous one or more of the local maximas, removes the one or more local maximas from the plurality of local maximas to generate a reduced list of local maximas, sets a plurality of waypoints as the endpoints and the local maximas in the reduced list of local maximas, generates a flight path based at least in part on the plurality of waypoints, and causes the flight path to be provided to the at aircraft.

The present disclosure relates to propulsion system for an aircraft. The propulsion system comprises a motor, a battery bank, a thermal management system, and a controller. The motor being configured to rotate a rotor via a rotor shaft and to drive the thermal management system. The thermal management system configured to urge fluid through a fluid pathway defined by the battery bank. The controller configured to drive the motor and/or control charge and discharge of the battery bank.

Examples include an apparatus for delivering a payload. The apparatus includes a first autonomous vehicle and a second autonomous vehicle that are configured to be coupled to an aircraft. The first autonomous vehicle includes a wing and a first propulsion system configured to deliver the second autonomous vehicle to a first destination. The second autonomous vehicle includes a payload and a second propulsion system configured to deliver the payload to a second destination.