Landing device for landing a span-wise loaded aircraft

Patent metadata

Field	Value
Publication number	US-10414516-B2
Application number	US-201615370112-A
Country	US
Kind code	B2
Filing date	Dec 6, 2016
Priority date	Dec 7, 2015
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A landing device for landing an aircraft thereon. The landing device comprises a first group of supporting elements arranged next to each other in a first direction, each supporting element configured to support a portion of a body or a portion of a wing of the aircraft. Each supporting element is further configured to bow when loaded by the mass of the body portion or the wing portion supported by the respective supporting element.

First claim

The invention claimed is:

1. A landing device for landing an aircraft thereon, the landing device comprising:
a first group of three or more supporting elements comprising elongated generally vertically arranged solid members having an axial length arranged next to each other in a first direction, each supporting element configured to directly engage and support a portion of a body or a portion of a wing of the aircraft,
wherein each supporting element is further configured to bow along the axial length when loaded by the mass of the body portion or the wing portion supported by the respective supporting element.

2. The landing device according to claim 1 , wherein an extent of the first group of supporting elements in the first direction is greater than an extent of the wing span of the aircraft.

3. The landing device according to claim 1 , further comprising a second group of supporting elements arranged next to each other in a second direction perpendicular to the first direction.

4. The landing device according to claim 3 , wherein each of the supporting elements of the first and second group comprises:
a base member; and
at least one elongated bristle of a solid bendable material, wherein a lower end of each bristle is fixedly coupled to the base member and an opposite upper end freely stands up and is configured and positioned to directly engage with the portion of the body or the portion of the wing of the aircraft.

5. The landing device according to claim 4 , wherein the upper free end of each bristle is configured to bow when the body portion or the wing portion of the aircraft skids over the bristle.

6. The landing device according to claim 4 , wherein at least an end portion of at least some of the bristles at the upper free end is pre-bent in a direction in which the aircraft lands.

7. The landing device according to claim 4 , wherein the at least one bristle comprises bristles of different lengths.

8. The landing device according to claim 7 , wherein each supporting element comprises multiple sets of bristles, each set having a respective bristle length.

9. A landing device for landing an aircraft thereon, the landing device comprising:
a first group of supporting elements comprising elongated members having an axial length and a free upper end arranged next to each other in a first direction, each supporting element configured to directly engage and support a portion of a body or a portion of a wing of the aircraft,
wherein at least an end portion of at least some of the supporting elements at the upper free end is pre-bent and each supporting element is further configured to bow along the axial length when loaded by the mass of the body portion or the wing portion supported by the respective supporting element.

10. The landing device according to claim 9 , wherein at least some of the elongated members are inflatable tubes.

11. The landing device according to claim 9 , further comprising a second group of supporting elements arranged next to each other in a second direction perpendicular to the first direction.

12. The landing device according to claim 11 , wherein each of the supporting elements of the first and second group comprises:
a base member; and
at least one elongated bristle of a bendable material, wherein a lower end of each bristle is fixedly coupled to the base member and an opposite upper end freely stands up and is configured and positioned to directly engage with the portion of the body or the portion of the wing of the aircraft.

13. The landing device according to claim 11 , wherein the upper free end of each bristle is configured to bow when the body portion or the wing portion of the aircraft skids over the bristle.

14. The landing device according to claim 11 , wherein the at least one bristle comprises bristles of different lengths.

15. The landing device according to claim 14 , wherein each supporting element comprises multiple sets of bristles, each set having a respective bristle length.

16. A landing device for landing an aircraft thereon, the landing device comprising:
a first group of supporting elements comprising elongated members having at least two different axial lengths arranged next to each other in a first direction, each supporting element configured to directly engage and support a portion of a body or a portion of a wing of the aircraft,
wherein each supporting element is further configured to bow along the axial length when loaded by the mass of the body portion or the wing portion supported by the respective supporting element.

17. The landing device according to claim 16 , wherein at least some of the elongated members are inflatable tubes.

18. The landing device according to claim 16 , further comprising a second group of supporting elements arranged next to each other in a second direction perpendicular to the first direction.

19. The landing device according to claim 18 , wherein each of the supporting elements of the first and second group comprises:
a base member; and
at least one elongated bristle of a bendable material, wherein a lower end of each bristle is fixedly coupled to the base member and an opposite upper end freely stands up and is configured and positioned to directly engage with the portion of the body or the portion of the wing of the aircraft.

20. The landing device according to claim 19 , wherein each supporting element comprises multiple sets of bristles, each set having a respective bristle length.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Closs Martin
• Kittmann Klaus

Classifications

• B64F1/025

  using decelerating or arresting beds · CPC title

• B64F1/02 Primary

  for arresting aircraft, e.g. nets or cables · CPC title

• B64F1/027 Primary

  using net or mesh · CPC title