Hovering aerial vehicle and method of flying same

Patent metadata

Field	Value
Publication number	US-11148807-B2
Application number	US-201615528980-A
Country	US
Kind code	B2
Filing date	Nov 2, 2016
Priority date	Nov 3, 2015
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A hovering aerial vehicle is provided, comprising an airborne unit and an auxiliary unit. The airborne unit is configured to carry the auxiliary unit during flight and comprises a flight system configured to facilitate providing aerodynamic lift to facilitate hovering of the vehicle. The auxiliary unit comprises an electrical power source in electrical communication with the flight system to provide electrical power for its operation. The hovering aerial vehicle further comprises a decoupling system configured to facilitate selectively switching the vehicle between a detached configuration thereof wherein the airborne and auxiliary units are remote from each other, and an attached configuration thereof wherein the airborne and auxiliary units are secured to one another, and to maintain the electrical communication when the vehicle is in its detached configuration.

First claim

The invention claimed is:

1. A hovering aerial vehicle, comprising:
an airborne unit including a flight system that is configured to facilitate providing aerodynamic lift to facilitate hovering of the hovering aerial vehicle;
an auxiliary unit including an electrical power source in electrical communication with the flight system to provide electrical power for operation thereof;
wherein the airborne unit comprises a bay configured to at least partially receive therewithin the auxiliary unit during flight; and
a decoupling system configured to:
facilitate, during the flight while the electrical power is being provided to the airborne unit by the auxiliary unit, selectively switching the hovering aerial vehicle between a detached configuration thereof in which the auxiliary unit is completely out of the bay and continues to provide said electrical power to the airborne unit, and an attached configuration thereof in which the auxiliary unit is positioned at least partially within the bay, and the airborne and auxiliary units are secured to one another; and
maintain the electrical communication when the hovering aerial vehicle is in the detached configuration;

wherein the hovering aerial vehicle is configured, in the detached configuration, for ascension of the airborne unit from the auxiliary unit when the auxiliary unit is resting on an external surface.

2. The hovering aerial vehicle according to claim 1 , wherein the hovering aerial vehicle is configured, when in the attached configuration, to provide electrical communication between the electrical power source and the flight system using elements separate from the decoupling system.

3. The hovering aerial vehicle according to claim 1 , wherein the decoupling system includes one or more cables configured to maintain the electrical communication and attached, at opposite ends thereof, to the airborne and auxiliary units.

4. The hovering aerial vehicle according to claim 3 , wherein the decoupling system includes two of the one or more cables, wherein points of attachments of the one or more cables to the airborne unit are spaced from each other a first distance, and points of attachments of the one or more cables to the auxiliary unit are spaced from each other a second distance greater than the first distance.

5. The hovering aerial vehicle according to claim 4 , wherein the decoupling system includes a winch mounted to the airborne unit and configured to selectively release and retract the one or more cables.

6. The hovering aerial vehicle according to claim 4 , wherein a first of one or more the cables carries a positive electrical charge from the electrical power source to the flight system, and a second of the one or more cables carries a negative electrical charge from the electrical power source to the flight system.

7. The hovering aerial vehicle according to claim 3 , wherein the decoupling system is configured to determine a tautness of the one or more cables when the vehicle is in the detached configuration.

8. The hovering aerial vehicle according to claim 7 , wherein the decoupling system includes a motor and is configured to detect the tautness by measuring a current thereof.

9. The hovering aerial vehicle according to claim 1 , wherein the decoupling system is configured to maintain the electrical communication using wireless energy transmission.

10. The hovering aerial vehicle according to claim 1 , further comprising a tracking system configured to facilitate location of the auxiliary unit and to facilitate navigation of the airborne unit thereto.

11. The hovering aerial vehicle according to claim 1 , wherein the auxiliary unit includes a floatation arrangement configured to facilitate the auxiliary arrangement floating on a body of water.

12. The hovering aerial vehicle according to claim 1 , wherein the auxiliary unit includes a camera.

13. The hovering aerial vehicle according to claim 1 , being configured to facilitate recharging of the electrical power source.

14. The hovering aerial vehicle according to claim 1 , wherein the auxiliary unit has a weight that is at least 40 % of a weight of the hovering aerial vehicle.

15. The hovering aerial vehicle according to claim 1 , wherein the decoupling system is configured to determine a maximum separation distance between the airborne unit and the auxiliary unit within which the decoupling system is configured to maintain the electrical communication in the detached configuration of the vehicle.

16. The hovering aerial vehicle according to claim 15 , wherein the flight system is configured to facilitate the airborne unit hovering, when the hovering aerial vehicle is in the detached configuration, above the auxiliary system up to a height equal to at least the maximum separation distance.

17. The hovering aerial vehicle according to claim 1 , wherein the auxiliary unit includes a propulsion arrangement configured to facilitate locomotion thereof when the hovering aerial vehicle is in the detached configuration.

18. The hovering aerial vehicle according to claim 17 , wherein the propulsion arrangement includes a terrestrial propulsion arrangement configured to drive the auxiliary unit across land.

19. The hovering aerial vehicle according to claim 17 , wherein the propulsion arrangement includes a marine propulsion arrangement configured to drive the auxiliary unit across water.

20. The hovering aerial vehicle according to claim 17 , wherein the propulsion arrangement includes an auxiliary controller to direct operation thereof.

Assignees

• Israel Aerospace Ind Ltd

Inventors

• Marom Daniel

Classifications

• B64U10/14

  with four distinct rotor axes, e.g. quadcopters · CPC title

• B64U60/30

  detachable from the body · CPC title

• B64D1/22

  Taking-up articles from earth's surface · CPC title

• B64B1/02

  Non-rigid airships (B64B1/58 takes precedence; balloons B64B1/40) · CPC title

• B64D1/10

  Stowage arrangements for the devices in aircraft · CPC title