LONG RANGE ELECTRIC AIRCRAFT AND METHOD OF OPERATING SAME

• US 20160031564A1
• Filed: 10/13/2015
• Published: 02/04/2016
• Est. Priority Date: 03/30/2012
• Status: Active Grant

• Current Assignee: Ampaire, Inc., Flight of the Century, Inc.
• Original Assignee: Flight of the Century, Inc.
• Inventors: YATES, William M.
• Granted Patent: US 9,650,138 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 3/00 Aircraft adaptations to facilitate towing or being towed B64D39/00 takes precedence
• CPC Class Codes: B64D 33/00 Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 2101/64 for parcel delivery or retrieval
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/34 In-flight charging photovoltaics B64U50/31
• CPC Class Codes: B64U 70/60 Take-off or landing of UAVs from a runway using their own power

Abstract

Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, and method of deploying and retrieving secondary aircrafts.

Claims

1. An apparatus for transferring electricity between at least two aircrafts during flight comprising:

a deployable towing cable comprising a first portion and a second portion, the deployable towing cable being attached to a first aircraft;

an electrical connection between the first portion of the cable and a source of electricity on the first aircraft;

a mechanism for connecting the cable to a second aircraft at the second portion of the cable, wherein the mechanism for connecting the cable to the second aircraft is designed to also provide an electrical connection between the first aircraft and the second aircraft;

wherein when the cable is connected to the second aircraft, the first aircraft at least partially tows the second aircraft while electricity is transferred between the first aircraft and the second aircraft.

2. The apparatus of claim 1 further comprising a reeling device to deploy and retract the cable.

3. The apparatus of claim 1 further comprising a device to regulate electrical current during any transfer of electricity between first and second aircraft.

4. The apparatus of claim 1 wherein the mechanism for connecting the first aircraft to the second aircraft is activated by contact.

5. The apparatus of claim 1 wherein the mechanism for connecting the first aircraft to the second aircraft is activated by proximity.

6. The apparatus of claim 1 wherein the mechanism comprises a spring operated latch.

7. The apparatus of claim 1 wherein the mechanism comprises a gas operated latch.

8. The apparatus of claim 1 wherein the mechanism comprises a hydraulically operated latch.

9. The apparatus of claim 1 wherein the mechanism comprises an electrical actuator.

10. The apparatus of claim 1 wherein the mechanism comprises an electromagnetic element.

11. The apparatus of claim 1 further comprising at least one aerodynamically stabilizing design feature on the cable.

12. The apparatus of claim 11 wherein the at least one aerodynamically stabilizing design feature comprises a flight control surface.

13. The apparatus of claim 11 wherein the at least one aerodynamically stabilizing design feature comprises a thruster.

14. The apparatus of claim 13 wherein the thruster is powered by at least one compressed gas.

15. The apparatus of claim 13 wherein the thruster is designed to be actuated in response to input from at least one sensor.

16. The apparatus of claim 1 wherein the portion of the cable with provisions for providing electrical connectivity between the first and second aircraft is less than the total length of the cable.

17. The apparatus of claim 1 wherein the source of electricity in the first aircraft is a battery.

18. The apparatus of claim 17 wherein the voltage of the battery is higher than the voltage in at least one battery in the second aircraft to be recharged.

19. A method for regenerating electricity in at least one flying aircraft comprising:

deploying a cable from a first aircraft using a reeling device, the cable having an upstream end connected to the reeling device and a downstream end;

connecting the downstream end of the cable to a second aircraft, wherein the second aircraft comprises at least one propeller and an energy storage medium and wherein the first aircraft tows the second aircraft after the connection is made; and

regenerating electricity for the energy storage medium on the second aircraft using a windmilling action of the at least one propeller.

20. A system for regenerating electricity in at least one flying aircraft comprising:

a deployable cable connected to a first aircraft, the cable comprising an upstream end and a downstream end;

the upstream end of the cable comprising a mechanical connection to a reeling device onboard the first aircraft;

the downstream end of the cable comprising a mechanism for connecting to a second aircraft having at least one Ram Air Turbine (“

RAT”

) and an energy storage medium;

a reciprocal mechanism connected to the second aircraft for receiving the connection mechanism of the cable;

wherein the cable is designed to allow the first aircraft to tow the second aircraft when it is connected to the second aircraft and wherein the RAT is designed to regenerate energy for the energy storage medium when the second aircraft is being towed.