An automated commissioning and floorplan configuration (CAFC) device can include a CAFC system having a transceiver and a CAFC engine, where the transceiver communicates with at least one device disposed in a volume of space, where the CAFC engine, based on communication between the transceiver and the at least one device, commissions the at least one device.

Systems and methods of calculating a ballistic solution for a projectile are provided. A ballistic system may include an airborne device, a ballistic computer, a data interface, and a flight module, or any combination thereof. The airborne device (e.g., a drone) may be operable to gather wind data along or adjacent to a flight path of a projectile to a target. The ballistic computer may be in data communication with the airborne device to receive the wind data. The ballistic computer may be configured to calculate a ballistic solution for the projectile based on the wind data. The data interface may be in data communication with the ballistic computer to output the ballistic solution to a user. The flight module may be configured to calibrate a flight path of the airborne device.

Provided is a control device for controlling flight vehicles, including a replacement control unit for controlling replacement of a first flight vehicle covering a target area on the ground by a cell in a first frequency band with a second flight vehicle, in which the replacement control unit is for controlling the replacement such that, after the second flight vehicle moves to a location corresponding to a location of the first flight vehicle, the first flight vehicle continues using one part of a frequency band in the first frequency band and stops using a remaining part of the frequency band, and also the second flight vehicle forms a cell in a frequency band excluding the one part of the frequency band but including the remaining part of the frequency band, which overlaps with the cell formed by the first flight vehicle, and the first flight vehicle stops forming the cell.

The present disclosure relates to a reconfigurable battery system and method of operating the same. The reconfigurable battery system comprising a plurality of switchable battery modules, a battery supervisory circuit, and a battery pack controller, where the plurality of switchable battery modules electrically arranged in series to define a battery string defining an output voltage. The battery pack controller operably coupled to the battery supervisory circuit to selectively switch, for each of the plurality of switchable battery modules, the battery switch between the first position and the second position based at least in part on the one or more parameters of the battery and in accordance with a predetermined switching routine.

A control device is provided which forms a communication area on a ground to control an aircraft having an antenna for providing a radio communication service to a user terminal in the communication area. The control device includes a control unit that makes a plurality of aircrafts fly in formation, and controls the plurality of aircrafts such that the communication area of each of the plurality of aircrafts moves while covering a part of a preset target area and the entire target area is covered by a plurality of the communication areas of the plurality of aircrafts.

Provided is a control device for controlling a flight vehicle including a solar cell panel, and an antenna for forming a communication area on the ground to provide wireless communication service for a user terminal in the communication area by using electric power generated by the solar cell panel. The control device comprises a control unit for controlling a first flight vehicle and a second flight vehicle so that during a first time period, the second flight vehicle of the first flight vehicle and the second flight vehicle is caused not to cover a first target area and the first flight vehicle is caused to cover the first target area, and during a second time period following the first time period, the first flight vehicle is caused not to cover the first target area and the second flight vehicle is caused to cover the first target area.

The present disclosure relates to a reconfigurable battery system and method of operating the same. The reconfigurable battery system comprising a plurality of switchable battery modules, a battery supervisory circuit, and a battery pack controller, where the plurality of switchable battery modules electrically arranged in series to define a battery string defining an output voltage. The battery pack controller operable to connect the battery string to the external bus via a pre-charge switch to perform a pre-charge cycle.

A method, apparatus, and system for charging an electrical storage system in a vehicle. The vehicle comprises a support frame, a propulsion, an electric storage system, an extendable structure, and a power management unit. The propulsion system, the electrical storage system, and the power management unit are physically coupled to the support frame. The electrical storage system supplies the electrical energy to the propulsion system. The group of thermoelectric modules physically is physically coupled to the extendable structure and generates a current in response to a heat being transferred through the group of modules. The power management unit is electrically coupled to the electrical storage system and the group of thermal thermoelectric modules and controls storing the electrical energy in the electrical storage system using the current from the group of thermoelectric modules and supplying the electrical energy to the propulsion system.

A modular vertical take-off and landing aircraft for transporting persons and/or loads, comprising a flight module with multiple drive units arranged on a supporting framework structure, each drive unit having an electric motor and a propeller operatively connected to the electric motor, a transport module having a conveying pod and a connection device for connecting the conveying pod to the flight module. The connection device has an elongated shaft, one end of which is attached to the conveying pod, and a coupling device for connecting the flight module to another end of the elongate shaft of the transport module.

Disclosed is a transport module (1) for a vertical take-off and landing aircraft for transporting persons and/or loads, having a conveying pod (2) and a connection device (3) for connecting the conveying pod (2) to a flight: module (5). The connection device (3) has an elongate shaft (6), one end of which has a coupling device (4) and the other end of which is attached to the conveying pod (2).