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

• US 10,538,319 B2
• Filed: 02/15/2017
• Issued: 01/21/2020
• Est. Priority Date: 04/02/2013
• Status: Active Grant

• Current Assignee: Hood Technology Corporation
• Original Assignee: Hood Technology Corporation
• Inventors: von Flotow, Andreas H., Roeseler, Corydon C.
• Primary Examiner(s): Benedik, Justin M
• Application Number:
  US15/433,563
• Publication Number:
  US 20170327229A1
• Time in Patent Office: 1,070 Days
• CPC Class Codes: B64C 2027/003 mounted on rotor hub, e.g. a rotary force generator
• CPC Class Codes: B64C 25/08 non-fixed, e.g. jettisonable
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 27/48 Root attachment to rotor head
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 1/00 Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight with respect to weapon sights devices F41G takes precedence, parachutes per se B64D17/00; ejectable seats B64D25/10; ejectable capsules B64D25/12; refuelling during flight B64D39/00; launching apparatus for projecting projectiles or missiles F41F1/00, F41F7/00; rocket or torpedo launchers F41F3/00
• CPC Class Codes: B64D 1/02 Dropping, ejecting, or releasing articles jettisonable fuel reservoirs B64D37/12
• CPC Class Codes: B64D 1/12 Releasing
• CPC Class Codes: B64D 3/00 Aircraft adaptations to facilitate towing or being towed B64D39/00 takes precedence
• CPC Class Codes: B64D 35/02 specially adapted for specific power plants
• CPC Class Codes: B64D 5/00 Aircraft transported by aircraft, e.g. for release or reberthing during flight flying units formed by separate aircraft B64C37/02
• CPC Class Codes: B64F 1/029 using a cable or tether
• CPC Class Codes: B64F 1/0295 aerodynamically or aerostatically supported, e.g. parafoil or balloon
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2101/00 : UAVs specially adapted for particular uses or applications
• CPC Class Codes: B64U 2101/67 : the UAVs comprising tethers for lowering the goods
• CPC Class Codes: B64U 2201/20 : Remote controls
• CPC Class Codes: B64U 30/20 : Rotors; Rotor supports
• CPC Class Codes: B64U 50/19 : using electrically powered motors
• CPC Class Codes: B64U 70/20 : for releasing or capturing UAVs in flight by another aircraft
• CPC Class Codes: B64U 70/30 : for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
• CPC Class Codes: B64U 80/70 : in containers B64U80/60 takes precedence
• CPC Class Codes: B65D 25/10 : Devices to locate articles in containers for protecting articles from mechanical damage B65D81/02
• CPC Class Codes: B65D 2585/687 : aircrafts
• CPC Class Codes: B65D 85/68 : for machines, engines or vehicles in assembled or dismantled form

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.

Claims

1. A fixed-wing aircraft fuselage-retaining device comprising:

a pair of pincers each having a free end, the pincers pivotably attached to one another so they are movable relative to one another between a fuselage-retaining orientation in which their free ends are separated by a first distance and a fuselage-release orientation in which their free ends are separated by a second greater distance greater than the first distance; and

a safety mechanism movable between an engaged position in which the safety mechanism prevents the pincers from moving from the fuselage-retaining orientation to the fuselage-release orientation and a disengaged position in which the safety mechanism does not prevent the pincers from moving from the fuselage-retaining orientation to the fuselage-release orientation.

2. The fixed-wing aircraft fuselage-retaining device of claim 1, wherein the second distance is larger than a diameter of a fuselage of a fixed-wing aircraft receivable in a spaced defined between the pincers.

3. The fixed-wing aircraft fuselage-retaining device of claim 2, wherein the first distance is smaller than the diameter of the fuselage.

4. The fixed-wing aircraft fuselage-retaining device of claim 1, which includes a biasing element that biases the pincers to the fuselage-retaining orientation.

5. The fixed-wing aircraft fuselage-retaining device of claim 4, wherein the biasing element includes a spring positioned to compress when the pincers are moved from the fuselage-retaining orientation to the fuselage-release orientation.

6. The fixed-wing aircraft fuselage-retaining device of claim 1, which includes a biasing element that biases the safety mechanism to the engaged position.

7. The fixed-wing aircraft fuselage-retaining device of claim 6, wherein the biasing element includes a spring disposed between one of the pincers and the safety mechanism.

8. The fixed-wing aircraft fuselage-retaining device of claim 1, wherein the safety mechanism is pivotably connected to one of the pincers, the engaged position is an engaged rotational position, and the disengaged position is a disengaged rotational position.

9. The fixed-wing aircraft fuselage-retaining device of claim 1, wherein one of the pincers includes a safety mechanism engager and the safety mechanism includes a rotation prevention element that is:

(1) in the rotational path of the safety mechanism engager of that pincer when the safety mechanism is in the engaged position, and (2) is not in the rotational path of the safety mechanism engager of that pincer when the safety mechanism is in the disengaged position.

10. The fixed-wing aircraft fuselage-retaining device of claim 1, which includes a flexible member attached to the safety mechanism so tensioning the flexible member causes the safety mechanism to move to the disengaged position.

11. A fixed-wing aircraft fuselage-retaining device comprising:

a first pincer having a free end;

a second pincer having a free end, the first and second pincers attached to one another so they are movable relative to one another between a fuselage-retaining orientation in which their free ends are separated by a first distance and a fuselage-release orientation in which their free ends are separated by a second greater distance greater than the first distance; and

a biasing element that biases the pincers to the fuselage-retaining orientation.

12. The fixed-wing aircraft fuselage-retaining device of claim 11, which includes a safety mechanism movable between an engaged position in which the safety mechanism prevents the pincers from moving from the fuselage-retaining orientation to the fuselage-release orientation and a disengaged position in which the safety mechanism does not prevent the pincers from moving from the fuselage-retaining orientation to the fuselage-release orientation.

13. The fixed-wing aircraft fuselage-retaining device of claim 12, which includes a safety mechanism biasing element that biases the safety mechanism to the engaged position.

14. The fixed-wing aircraft fuselage-retaining device of claim 11, which includes a safety mechanism movable between an engaged position in which the safety mechanism prevents the pincers from moving from the fuselage-retaining orientation to the fuselage-release orientation and a disengaged position in which the safety mechanism does not prevent the pincers from moving from the fuselage-retaining orientation to the fuselage-release orientation, and which includes a safety mechanism biasing element that biases the safety mechanism to the engaged position, the safety mechanism biasing element including a spring disposed between one of the pincers and the safety mechanism.

15. The fixed-wing aircraft fuselage-retaining device of claim 12, wherein one of the pincers includes a safety mechanism engager and the safety mechanism includes a rotation prevention element that is:

(1) in the rotational path of the safety mechanism engager of that pincer when the safety mechanism is in the engaged position, and (2) is not in the rotational path of the safety mechanism engager of that pincer when the safety mechanism is in the disengaged position.

16. The fixed-wing aircraft fuselage-retaining device of claim 12, which includes a flexible member attached to the safety mechanism so tensioning the flexible member causes the safety mechanism to move to the disengaged position.

17. The fixed-wing aircraft fuselage-retaining device of claim 11, wherein the second distance is larger than a diameter of a fuselage of a fixed-wing aircraft receivable in a spaced defined between the pincers.

18. The fixed-wing aircraft fuselage-retaining device of claim 17, wherein the first distance is smaller than the diameter of the fuselage.

19. The fixed-wing aircraft fuselage-retaining device of claim 11, wherein the biasing element includes a spring positioned to compress when the pincers are moved from the fuselage-retaining orientation to the fuselage-release orientation.

20. The fixed-wing aircraft fuselage-retaining device of claim 11, wherein the pincers are pivotably attached to one another.