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

Patent metadata

Field	Value
Publication number	US-10633085-B2
Application number	US-201715432571-A
Country	US
Kind code	B2
Filing date	Feb 14, 2017
Priority date	Apr 2, 2013
Publication date	Apr 28, 2020
Grant date	Apr 28, 2020

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 modular multicopter comprising:
a hub module including multiple first connectors;
multiple rotor arm modules each including a second connector, wherein each second connector is configured to:
mate with one of the multiple first connectors to form a mechanical connection and an electrical connection of that rotor arm module and the hub module; and
extend around part of that rotor arm module, such that the electrical connection is formed by the first connector and second connector on opposing first and second axial sides of the rotor arm module; and

a fixed-wing aircraft attacher connected to the hub module.

2. The modular multicopter of claim 1 , wherein each rotor arm module includes a rotor and a rotor motor drivingly engaged to the rotor.

3. The modular multicopter of claim 2 , wherein, for each rotor arm module, when the second connector of that rotor arm module is mated with one of the first connectors of the hub module: (1) the rotor motor of that rotor arm module is electrically connected to the hub module; and (2) that rotor arm module is mechanically connected to the hub module.

4. The modular multicopter of claim 3 , which includes multiple rotor motor controllers, each of which is electrically connected to one of the first connectors.

5. The modular multicopter of claim 1 , which includes multiple rotor motor controllers, each of which is electrically connected to one of the first connectors, wherein each rotor arm module includes a rotor and a rotor motor drivingly engaged to the rotor, and wherein, for each rotor arm module, when the second connector of that rotor arm module is mated with one of the first connectors of the hub module, the rotor motor of that rotor arm module is electrically connected to the rotor motor controller electrically connected to that first connector.

6. The modular multicopter of claim 1 , wherein one of the first connectors includes multiple pins and one of the second connectors includes multiple pin receptacles, the pins slidably receivable in the pin receptacles.

7. The modular multicopter of claim 1 , wherein one of the second connectors includes multiple pins and one of the first connectors includes multiple pin receptacles, the pins slidably receivable in the pin receptacles.

8. A modular multicopter comprising:
a hub module including four first connectors;
four rotor arm modules each including a second connector, a rotor, and a rotor motor drivingly engaged to the rotor, each rotor arm module being mechanically attachable to and electrically connectable to the hub module via mating the second connector of that rotor arm module with one of the first connectors, wherein each second connector extends around part of one of the four rotor arm modules, such that an electrical connection is formed on opposing first and second axial sides of the rotor arm module;
four rotor motor controllers each electrically connected to a different one of the first connectors; and
a fixed-wing aircraft attacher connected to the hub module.

9. The modular multicopter of claim 8 , wherein, for each rotor arm module, when the second connector of that rotor arm module is mated with one of the first connectors of the hub module, the rotor motor of that rotor arm module is electrically connected to the rotor motor controller electrically connected to that first connector.

10. The modular multicopter of claim 8 , wherein each rotor arm module includes an upper rotor, an upper rotor motor drivingly engaged to the upper rotor, a lower rotor, and a lower rotor motor drivingly engaged to the lower motor.

11. The modular multicopter of claim 10 , which includes eight rotor motor controllers, wherein different pairs of the rotor motor controllers are respectively electrically connected to the first connectors.

12. The modular multicopter of claim 11 , wherein for each rotor arm module, when the second connector of that rotor arm module is mated with one of the first connectors of the hub module: (1) the upper rotor motor of that rotor arm module is electrically connected to one of the rotor motor controllers electrically connected to that first connector, and (2) the lower rotor motor of that rotor arm module is electrically connected to the other rotor motor controller electrically connected to that first connector.

13. The modular multicopter of claim 8 , wherein one of the first connectors includes multiple pins and one of the second connectors includes multiple pin receptacles, the pins slidably receivable in the pin receptacles.

14. The modular multicopter of claim 8 , wherein one of the second connectors includes multiple pins and one of the first connectors includes multiple pin receptacles, the pins slidably receivable in the pin receptacles.

15. A method of preparing a multicopter to launch a fixed-wing aircraft, the method comprising:
attaching the fixed-wing aircraft to a hub module of the multicopter, the hub module including multiple first connectors; and
mechanically attaching and electrically connecting multiple rotor arm modules to the hub module,
wherein the multiple rotor arm modules each include a second connector, the second connector extending around part of the rotor arm module, such that electrically connecting the rotor arm module to the hub module comprises electrically connecting the second connector and one of the multiple first connectors on opposing first and second axial sides of the rotor arm module.

16. The method of claim 15 , which includes attaching the fixed-wing aircraft to the hub module before mechanically attaching and electrically connecting the rotor arm modules to the hub module.

17. The method of claim 15 , wherein mechanically attaching and electrically connecting multiple rotor arm modules to the hub module includes, for each rotor arm module, mating the second connector of that rotor arm module with one of multiple first connectors of the hub module.

18. The method of claim 17 , wherein mating the second connector of one of the rotor arm modules with one of the first connectors of the hub module includes sliding multiple pins of one of the first connector and the second connector into multiple pin receptacles of the other of the first connector and the second connector.

19. The method of claim 15 , which includes mechanically attaching and electrically connecting four rotor arm modules to the hub module.

Assignees

• Hood Tech Corp

Inventors

• Von Flotow Andreas H
• Roeseler Corydon C
• Reiss Daniel Pepin

Classifications

• B64D1/02

  Dropping, ejecting, or releasing articles (jettisonable fuel reservoirs B64D37/12) · CPC title

• B64C27/001

  Vibration damping devices · CPC title

• B64C25/08

  non-fixed, e.g. jettisonable · CPC title

• B65D85/68

  for machines, engines or vehicles in assembled or dismantled form · CPC title

• B65D2585/687

  aircrafts · CPC title