Helicopter-mediated system and method for launching and retrieving an aircraft

• US 9,359,075 B1
• Filed: 01/15/2015
• Issued: 06/07/2016
• 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., Reiss, Daniel
• Primary Examiner(s): O'Hara, Brian M
• Application Number:
  US14/597,933
• Publication Number:
  US 20160152339A1
• Time in Patent Office: 509 Days
• US Class Current: 1/1
• CPC Class Codes: B64C 27/04 Helicopters
• 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 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 10/16 with five or more distinct rotor axes, e.g. octocopters
• CPC Class Codes: B64U 10/17 Helicopters flying platforms B64U10/13
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 10/60 Tethered aircraft
• 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

Abstract

Various embodiments of the present disclosure provide a helicopter-mediated system and method for launching and retrieving an aircraft capable of long-distance efficient cruising flight from a small space without the use of a long runway.

Claims

1. A helicopter-mediated method for retrieving an aircraft from wing-borne flight, said method comprising:

flying a helicopter above an anchor assembly such that a first portion of a tether connected to both the helicopter and the anchor assembly extends between the helicopter and the anchor assembly;

station-keeping the helicopter generally above the anchor assembly;

measuring tension in the first portion of the tether and, when the measured tension in the first portion of the tether is not substantially equal to a designated tension, moving the helicopter relative to the anchor assembly until the measured tension in the first portion of the tether is substantially equal to the designated tension; and

contacting and capturing a part of the first portion of the tether extending between the tether and the anchor assembly with the aircraft, thereby causing the anchor assembly to pay out a second portion of the tether and impose a resistive force opposing movement of the aircraft.

2. The method of claim 1, which includes station-keeping the helicopter generally above the anchor assembly before, during, and after the aircraft captures the part of the first portion of the tether.

3. The method of claim 1, which includes, after the aircraft captures the part of the first portion of the tether, lowering the helicopter to cause the aircraft to be received in a docking fixture.

4. The method of claim 1, which includes station-keeping the helicopter generally above the anchor assembly using a geographical location of the anchor assembly.

5. The method of claim 1, wherein moving the helicopter relative to the anchor assembly includes moving the helicopter substantially vertically.

6. The method of claim 1, which includes automatically station-keeping the helicopter.

7. The method of claim 1, which includes station-keeping the helicopter using manual control.

8. A helicopter-mediated system for retrieving an aircraft, said system comprising:

a helicopter including a first connector;

a tether connected to the helicopter via the first connector;

an anchor assembly connected to the tether such that a first portion of the tether extends between the helicopter and the anchor assembly,

a helicopter control system, and

a tension sensor configured to measure and to transmit, to the helicopter control system, a tension in the first portion of the tether extending between the helicopter and the anchor assembly,

wherein the anchor assembly is configured such that, when the tether is connected to the anchor assembly, imposition of an extending force on the tether in a direction away from the anchor assembly causes the anchor assembly to pay out a second portion of the tether and impose a resistive force opposing the extending force.

9. The system of claim 8, which includes a navigation device configured to determine a geographical location of the anchor assembly and to transmit the determined geographical location of the anchor assembly, and wherein the helicopter control system is one of:

(a) attached to the helicopter, and (b) remote from the helicopter and is configured to receive the determined geographical location of the anchor assembly from the navigation device.

10. The system of claim 9, wherein the helicopter control system is configured to use the determined geographical location of the anchor assembly to cause the helicopter to station-keep generally above the anchor assembly.

11. The system of claim 8, wherein a portion of the first portion of the tether is elastic.

12. The system of claim 8, wherein the helicopter control system is configured to use the measured tension in the first portion of the tether to, when the measured tension in the first portion of the tether is not substantially equal to a designated tension, cause the helicopter to move relative to the anchor assembly until the measured tension in the first portion of the tether is substantially equal to the designated tension.

13. The system of claim 12, wherein said movement is substantially vertical.

14. The system of claim 8, wherein the anchor assembly includes a breakaway device configured to:

(1) prevent the anchor assembly from paying out the second portion of the tether as long as a tension in the first portion of the tether extending between the helicopter and the anchor assembly does not exceed a designated tension, and (2) enable the anchor assembly to pay out the second portion of the tether when the tension in the first portion of the exceeds the designated tension.

15. The system of claim 8, wherein the anchor assembly includes a retracting device connected to the tether.

16. The system of claim 15, wherein the retracting device is configured to impose a designated retracting force on the first portion of the tether extending between the helicopter and the anchor assembly regardless of whether the extending force is imposed on the tether in the direction away from the anchor assembly.

17. The system of claim 16, wherein the extending force exceeds the designated retracting force.

18. The system of claim 8, wherein the first connector of the helicopter is connectable to a second connector of the aircraft to facilitate launch of the aircraft.