Multicopter-assisted system and method for launching and retrieving a fixed-wing aircraft

Patent metadata

Field	Value
Publication number	US-10293929-B2
Application number	US-201715434735-A
Country	US
Kind code	B2
Filing date	Feb 16, 2017
Priority date	Apr 2, 2013
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

First claim

The invention is claimed as follows:

1. A method for retrieving a fixed-wing aircraft from wing-borne flight, the method comprising:
flying a rotorcraft above an anchor system such that a part of a flexible capture member connected at one end to the rotorcraft, at another end to a flexible capture member payout and retract device of the anchor system, and to a breakaway device of the anchor system extends between the rotorcraft and the anchor system;
station-keeping the rotorcraft relative to the anchor system; and
contacting and capturing the part of the flexible capture member extending between the rotorcraft and the anchor system with the fixed-wing aircraft, which causes the breakaway device to release the flexible capture member when a designated tension in the flexible capture member is exceeded and, thereafter, causes the flexible capture member payout and retract device to pay out another part of the flexible capture member and impose a resistive force opposing movement of the fixed-wing aircraft.

2. The method of claim 1 , which includes retracting at least some of the paid-out part of the flexible capture member.

3. The method of claim 2 , wherein the retracting is performed by the flexible capture member payout and retract device.

4. The method of claim 1 , which includes station-keeping the rotorcraft relative to the anchor system to maintain a generally constant tension on the flexible capture member before the fixed-wing aircraft contacts the flexible capture member.

5. The method of claim 1 , which includes station-keeping the rotorcraft relative to the anchor system to maintain in a tension less than the designated tension on the flexible capture member before the fixed-wing aircraft contacts the flexible capture member.

6. The method of claim 1 , which includes attaching a GPS antenna to the rotorcraft before flying the rotorcraft above the anchor system.

7. The method of claim 1 , which includes, attaching a breakaway ring to the flexible capture member.

8. The method of claim 7 , which includes attaching the flexible capture member to the breakaway device via the breakaway ring.

9. The method of claim 8 , wherein attaching the flexible capture member to the breakaway device via the breakaway ring includes threading a breakaway finger of the breakaway device through the breakaway ring and attaching the breakaway sleeve to the collar.

10. The method of claim 1 , which includes, before flying the rotorcraft above the anchor system:
switching a first power circuit of the rotorcraft from an open state to a closed state to electrically connect a power source of the rotorcraft to an electrically powered component of the rotorcraft to power the component without electrically connecting the power source to a rotor motor of the rotorcraft; and
afterwards, switching a second power circuit from an open state to a closed state to electrically connect the power source to the rotor motor to power the rotor motor.

11. The method of claim 10 , wherein the rotorcraft includes a hub and multiple arms attachable to the hub, each arm including a rotor and a rotor motor drivingly engaged to the rotor.

12. The method of claim 11 , wherein switching the first power circuit from the open state to the closed state electrically connects the power source to the component without electrically connecting the power source to the rotor motors.

13. The method of claim 12 , wherein switching the second power circuit from the open state to the closed state electrically connects the power source to the rotor motor.

14. The method of claim 13 , which includes, before switching the second power circuit from the open state to the closed state, attaching the arms to the hub to electrically connect the arms to the hub so the rotor motors of the arms are electrically connected to the power source.

15. The method of claim 1 , which includes, after the fixed-wing aircraft captures the flexible capture member, descending the rotorcraft until the fixed-wing aircraft contacts an aircraft landing surface.

16. The method of claim 14 , which includes, after the fixed-wing aircraft contacts the landing surface, landing the rotorcraft on a rotorcraft landing surface.

17. The method of claim 15 , wherein the aircraft landing surface and the rotorcraft landing surface are the same surface.

18. The method of claim 15 , wherein the aircraft landing surface and the rotorcraft landing surface are different surfaces.

Assignees

• Hood Tech Corp

Inventors

• Von Flotow Andreas H
• Roeseler Corydon C
• Woodruff Caleb Andrew
• Reiss Daniel Pepin

Classifications

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64D5/00

  Aircraft transported by aircraft, e.g. for release or reberthing during flight · CPC title

• B64C27/26

  characterised by provision of fixed wings · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title

• B64D3/00

  Aircraft adaptations to facilitate towing or being towed · CPC title