Patent ID: 11970275
Assignee: ISRAEL AEROSPACE INDUSTRIES LTD.
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 19:
20. The kit according to claim 19, including one of the following:
wherein each said secondary propulsion unit module comprises an electrical motor unit that is configured for operating to turn a respective driveshaft about a respective rotor axis, and a respective rotor mounted to the driveshaft;
wherein each said secondary propulsion unit module comprises an electrical motor unit that is configured for operating to turn a respective driveshaft about a respective rotor axis, and a respective rotor mounted to the driveshaft, and, wherein each rotor is in the form of a single propeller having a plurality of blades;
wherein each said secondary propulsion unit module comprises an electrical motor unit that is configured for operating to turn a respective driveshaft about a respective rotor axis, and a respective rotor mounted to the driveshaft, and, comprising an electrical speed controller (ESC) configured for controlling rotational speed of the respective rotor according to command signals from a controller configured for controlling the DEP system;
wherein each said secondary propulsion unit module comprises an electrical motor unit that is configured for operating to turn a respective driveshaft about a respective rotor axis, and a respective rotor mounted to the driveshaft, and, comprising an electrical speed controller (ESC) configured for controlling rotational speed of the respective rotor according to command signals from a controller configured for controlling the DEP system, and, wherein groups of said secondary electrical propulsion modules share the same ESC;
wherein each said secondary propulsion unit module comprises an electrical motor unit that is configured for operating to turn a respective driveshaft about a respective rotor axis, and a respective rotor mounted to the driveshaft, and, comprising an electrical speed controller (ESC) configured for controlling rotational speed of the respective rotor according to command signals from a controller configured for controlling the DEP system, and, wherein groups of said secondary electrical propulsion modules connect the respective ESC to a group controller, which is in turn operatively connected to a controller configured for controlling the DEP system;
wherein each said secondary propulsion unit module is reversibly mechanically coupleable to a respective said wing via a respective coupling;
wherein each said secondary propulsion unit module is reversibly mechanically coupleable to a respective said wing via a respective coupling, and, wherein said coupling comprises a respective module operative interface configured for operatively coupling with a corresponding air vehicle body coupling interface affixed to the CTOL air vehicle configuration, to thereby enable operative coupling of the respective secondary electrical propulsion module with the CTOL air vehicle configuration.