SYSTEMS AND METHODS FOR RECOVERING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT

• US 20120223182A1
• Filed: 10/21/2011
• Published: 09/06/2012
• Est. Priority Date: 04/24/2009
• Status: Active Grant

• Current Assignee: Insitu Incorporated (The Boeing Co.)
• Original Assignee: Insitu Incorporated (The Boeing Co.)
• Inventors: Dennis, Brian D., Mack, Jaime, Sliwa, Steven M., Gilchrist, Robert III, Stafford, John, Smith, Allen, Schrick, Bradley, Hughes, Robert
• Granted Patent: US 9,944,408 B2
• Time in Patent Office: Days
• US Class Current: 244/110.F
• CPC Class Codes: B64F 1/0297 adjustable to align with aircraft trajectory
• 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

Systems and methods for recovering unmanned aircraft and controlling post-recovery motion of the aircraft are disclosed herein. An aircraft recovery system for handling an unmanned aircraft in accordance with one embodiment of the disclosure includes a base portion and an elongated aircraft capture member having a first end movably coupled to the base portion and a second, free end opposite the first end. The aircraft capture member includes a first portion and a second portion at a distal end of the first portion and positioned to intercept an unmanned aircraft in flight. The first and/or second portions are generally flexible. The system further includes an energy capture and dissipation assembly operably coupled to the aircraft capture member and positioned to receive at least a portion of the landing forces from the aircraft.

Claims

1. An aircraft recovery system for handling an unmanned aircraft, the system comprising:

a base portion;

an elongated aircraft capture member having a first end movably coupled to the base portion and a second, free end opposite the first end, wherein the aircraft capture member has a first portion and a second portion at a distal end of the first portion and positioned to intercept an unmanned aircraft in flight, and wherein at least one of the first and second portions is generally flexible; and

an energy capture and dissipation assembly operably coupled to the aircraft capture member and positioned to receive at least a portion of the landing forces from the aircraft.

2. The aircraft recovery system of claim 1 wherein the aircraft capture member is movably coupled to the base portion via an attachment member, and wherein the aircraft capture member is positioned to pivotably move between an angled and a generally vertical orientation relative to the base portion.

3. The aircraft recovery system of claim 1 wherein the first and second portions are generally aligned with each other and extend along a longitudinal axis of the elongated aircraft capture member.

4. The aircraft recovery system of claim 1 wherein:

the first portion of the aircraft capture member has a first stiffness; and

the second portion of the aircraft capture member has a second stiffness less than the first stiffness.

5. The aircraft recovery system of claim 1 wherein:

the first portion of the aircraft capture member has a first length and a first cross-sectional dimension; and

the second portion of the aircraft capture member has a second length less than the first length, and a second cross-sectional dimension less than the first cross-sectional dimension.

6. The aircraft recovery system of claim 1 wherein the first and second portions are composed of the same material.

7. The aircraft recovery system of claim 1 wherein the first and second portions are composed of different materials.

8. The aircraft recovery system of claim 1 wherein the first and second portions are composed of a carbon fiber material.

9. The aircraft recovery system of claim 1 wherein the first and second portions are composed of a carbon graphite material.

10. The aircraft recovery system of claim 1 wherein the first and second portions are integral with each other.

11. The aircraft recovery system of claim 1 wherein the first and second portions are separate, discrete components that are attached together.

12. The aircraft recovery system of claim 1 wherein at least part of the second portion is coated with a soft, flexible sheath material configured to engage at least a portion of the aircraft, and wherein the sheath material is selected to provide a desired level of friction between the aircraft and the aircraft capture member.

13. The aircraft recovery system of claim 1 wherein the aircraft capture member is an elongated, generally flexible rod.

14. The aircraft recovery system of claim 1 wherein the energy capture and dissipation assembly comprises at least one of the following:

a hydraulic damper, a pneumatic damper, plastically deforming material, a passive takeup reel, or a brake.

15. An aircraft recovery system for recovering an unmanned aircraft in flight, the system comprising:

a base portion;

means for capturing an aircraft attached to and extending away from the base portion, wherein the means for capturing an aircraft includes—

a first end pivotably coupled to the base portion via a joint and a second, free end opposite the first end; and

a first portion and a second portion at a distal end of the first portion, wherein the second portion is positioned to intercept an unmanned aircraft in flight, and wherein at least one of the first and second portions is generally flexible; and

means for capturing and dissipating energy from the aircraft operably coupled to the means for capturing the aircraft, wherein the means for capturing and dissipating energy is positioned to receive at least a portion of the aircraft'"'"'s kinetic energy.

16. The aircraft recovery system of claim 15 wherein the means for capturing and dissipating energy comprises a flexible rod composed of at least one of the following:

a carbon fiber material, a carbon graphite material, fiberglass, a carbon/graphite composite material, a graphite/boron composite material, or bamboo.

17. The aircraft recovery system of claim 15 wherein the means for capturing and dissipating energy is carried by the base portion.

18. The aircraft recovery system of claim 15 wherein:

the means for capturing the aircraft has an initial, generally vertical orientation before the unmanned aircraft intercepts the means for capturing the aircraft in flight; and

the means for capturing and dissipating energy comprises a tension line attached to the second portion of the means for capturing the aircraft, and a tension reel operably coupled to the tension line and configured wind and/or unwind the tension line during operation.

19. The aircraft recovery system of claim 15 wherein at least one of the first and second portions of the means for capturing the aircraft comprises:

an inner inflatable portion including one or more bladders configured to be filled to a desired pressure with a gas; and

an outer engagement portion at least partially covering the inner inflatable portion, wherein the outer engagement portion is positioned to engage the aircraft.

20. The aircraft recovery system of claim 15 wherein the second portion of the means for capturing the aircraft is at least initially generally curved, and wherein the second portion comprises:

a first end attached to the first portion of the means for capturing the aircraft; and

a second end removably attached to a local surface, and wherein the second end of the second portion is configured to detach from the local surface after the unmanned aircraft intercepts the second portion in flight.

21. A method for recovering an unmanned aircraft in flight, the method comprising:

flying an unmanned aircraft to intercept an elongated flexible rod having a first end movably coupled to a base portion in contact with a local support surface, and a second, free end opposite the first end, wherein the flexible rod has a first portion and a second portion at a distal end of the first portion and positioned to intercept the unmanned aircraft, and wherein at least one of the first and second portions is generally flexible; and

releasably capturing the aircraft with the flexible rod, wherein at least a portion of the flexible rod is configured to flex during capture in response to the landing forces from the aircraft.

22. The method of claim 21, further comprising suspending the aircraft from the flexible rod and out of contact the local support surface or ground after releasably capturing the aircraft.

23. The method of claim 21 wherein the flexible rod is operably coupled to an energy capture and dissipation assembly, and wherein releasably capturing the aircraft with the flexible rod further comprises transferring the landing forces from the aircraft to the energy capture and dissipation assembly via the flexible rod.

24. The method of claim 21 wherein the flexible rod has an initial, first angled orientation relative to the base portion, and wherein releasably capturing the aircraft with the flexible rod comprises pivotably moving the flexible rod from the first angled orientation through a generally vertical position and to a second, angled orientation relative to the base portion different than the first angled orientation.

25. The method of claim 21 wherein:

flying the unmanned aircraft to intercept the elongated flexible rod comprises flying the unmanned aircraft such that a leading edge of a wing of the aircraft intercepts the second portion of the flexible rod at the second, free end of the flexible rod; and

releasably capturing the aircraft with the flexible rod comprises releasably engaging the second portion of the flexible rod with a capture device at an outboard edge of the wing.