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

Claim 3:
4. The air vehicle according to claim 1, including at least one of the following:
wherein the air vehicle comprises a control system configured for operating said DEP system to execute a landing maneuver
wherein each said first plurality of said secondary electrical propulsion units is mechanically coupled to the respective said port wing or the respective said starboard wing;
wherein each said secondary electrical propulsion units is coupled to the main aerodynamic lift generating wing arrangement via a respective coupling;
wherein each said secondary electrical propulsion units 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 electrical propulsion units 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 electrical propulsion units 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; or
wherein each said secondary electrical propulsion units 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, and, wherein each said rotor has a respective rotor diameter, circumscribed by the tips of the respective blades as they turn about the respective rotor axis, and, wherein the secondary electrical propulsion units of each one of said first plurality of secondary electrical propulsion units are spaced over each one of said port wing and said starboard wing at an inter-rotor spacing between each adjacent pair of said secondary electrical propulsion units, wherein said inter-rotor spacing are each less than a respective rotor diameter of the respective said rotor of the respective adjacent pair of said secondary electrical propulsion units.