AERIAL VEHICLE TETHER

• US 20200130810A1
• Filed: 06/20/2018
• Published: 04/30/2020
• Est. Priority Date: 06/21/2017
• Status: Abandoned Application

• Current Assignee: Astigan Limited
• Original Assignee: Astigan Limited
• Inventors: ELSON, Andrew Charles
• Application Number:
  US16/624,629
• Publication Number:
  US 20200130810A1
• Time in Patent Office: Days
• CPC Class Codes: B64C 3/18 Spars; Ribs; Stringers
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 20/65 Composite materials
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/40 Empennages, e.g. V-tails foldable or collapsible UAVs B64U20/50
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/31 generated by photovoltaics

Abstract

An aerial vehicle has a wing and a fuselage. A tether is anchored at opposing ends of the wing and/or the fuselage. The tether is arranged to prevent one or more parts of the aerial vehicle from separating from the remainder of the aerial vehicle in the event of structural failure of the aerial vehicle.

Claims

1-13. -13. (canceled)

14. An aerial vehicle comprising a wing, a fuselage and at least one tether anchored at opposing ends of the wing and/or the fuselage, wherein the at least one tether is arranged to prevent one or more parts of the aerial vehicle from separating from the remainder of the aerial vehicle in the event of structural failure of the aerial vehicle.

15. An aerial vehicle according to claim 14, including a plurality of the tethers, wherein one of the tethers is looped around another of the tethers so as to couple the tethers.

16. An aerial vehicle according to claim 14, wherein the wing and/or the fuselage includes a tubular structure and the at least one tether passes through the tubular structure.

17. An aerial vehicle according to claim 16, wherein the tubular structure includes at least one aperture configured to permit the tether to enter or exit the tubular structure.

18. An aerial vehicle according to claim 14, wherein the wing and/or the fuselage includes an elongate structure and the at least one tether is secured to the elongate structure at one or more intermediary locations between the opposing ends of the wing and/or the fuselage.

19. An aerial vehicle according to claim 14, wherein the at least one tether has a relatively high tensile strength and is more flexible than the wing and/or the fuselage.

20. An aerial vehicle according to claim 14, further comprising at least one component of significant mass as a proportion of the aerial vehicle as a whole, wherein the at least one tether is anchored to the at least one component of significant mass.

21. An aerial vehicle according to claim 20, wherein the at least one component of significant mass includes one or more of:

a flight control surface, a payload, a motor, or a propeller.

22. An aerial vehicle according to claim 14, wherein the at least one tether is configured to be anchored by passing the tether around one or more of:

a pin, a hook, or a loop.

23. An aerial vehicle according to claim 14, wherein the wing comprises a wing spar, and the at least one tether is anchored at opposing ends of the wing spar and extends along the wing spar.

24. An aerial vehicle according to claim 14, wherein the fuselage comprises a fuselage boom, and the at least one tether is anchored at opposing ends of the fuselage boom and extends along the fuselage boom.

25. An aerial vehicle according to claim 14, having at least one tether anchored at opposing ends of the wing, and configured such that in the event of structural failure of the wing, the aerial vehicle retained by the tether assumes a shape such that the aerial vehicle descends in a helical rotating motion.

26. An aerial vehicle according to claim 14, operable to fly in the stratosphere, preferably at altitudes above 18 kilometres.

27. An aerial vehicle according to claim 14, wherein the aerial vehicle is unmanned.

28. A method of assembling an aerial vehicle comprising a wing and a fuselage, the method comprising:

providing at least one tether; and

anchoring the tether at opposing ends of the wing and/or the fuselage, wherein the at least one tether is arranged to prevent one or more parts of the aerial vehicle from separating from the remainder of the aerial vehicle in the event of structural failure of the aerial vehicle.