Aircraft pylon

Patent metadata

Field	Value
Publication number	US-11174024-B2
Application number	US-201716470429-A
Country	US
Kind code	B2
Filing date	Dec 27, 2017
Priority date	Dec 28, 2016
Publication date	Nov 16, 2021
Grant date	Nov 16, 2021

Abstract

An aircraft pylon is provided, configured for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom. The pylon comprises an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing, and a carrying arrangement configured for carrying the payload and being pivotally articulated to the attachment mechanism. The pylon is configured to selectively pivot the carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward the fuselage.

First claim

The invention claimed is:

1. An aircraft pylon for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom, the aircraft pylon comprising:
an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing; and
a carrying arrangement configured for carrying said payload and being pivotally articulated to said attachment mechanism, the carrying arrangement including a housing defining an open-bottomed chamber therewithin and a payload release unit for suspension therefrom of said payload, the payload release unit being configured to shift between an operational position in which the payload release unit at least partially projects downwardly out of the housing, and a storage position in which the payload release unit is fully received within the chamber;
said aircraft pylon being configured, when the payload release unit shifts from the operational position to the storage position, to pivot said carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward said fuselage.

2. The aircraft pylon according to claim 1 , wherein said payload release unit comprises one or more sway braces for attaching the payload thereto, each of said sway braces comprising a vertical bearing member and a laterally projecting carrying arm having a length which is larger than the width of said chamber, and wherein said carrying arms are external to the chamber when the payload release unit is in its operational position.

3. The aircraft pylon according to claim 2 , configured for facilitating rotation of said sway braces upon shifting of the payload release unit from its operational position to its storage position.

4. The aircraft pylon according to claim 2 , wherein said payload release unit comprises a support bar to which said sway braces are articulated, and a shifting arrangement configured to actuate the support bar between raised and lowered positions.

5. The aircraft pylon according to claim 4 , said shifting arrangement comprising two parallely arranged pivot links, each pivotally articulated at one end thereof to the housing, and at another end thereof to the support bar, the shifting arrangement further comprising an actuator configured to selectively pivot said pivot links.

6. The aircraft pylon according to claim 5 , wherein said actuator is a linear actuator.

7. The aircraft pylon according to claim 5 , said payload release unit being configured to maintain the orientation of said support bar between its raised and lowered positions.

8. The aircraft pylon according to claim 1 , wherein said payload release unit is configured to mechanically facilitate pivoting of the carrying arrangement from its vertical to its tilted position when shifting from its operational to its storage position.

9. The aircraft pylon according to claim 1 , said attachment mechanism defining a receiving chamber therewithin, an upper part of said carrying arrangement comprising a suspension portion configured to be received within said receiving chamber and accommodated therein during pivoting of the carrying arrangement, said pylon axis passing through said receiving chamber and suspension portion.

10. The aircraft pylon according to claim 9 , further comprising a gasket configured to provide a tight seal between said attachment mechanism and suspension portion at least when said carrying arrangement is in its vertical and tilted positions.

11. The aircraft pylon according to claim 1 , wherein said carrying arrangement further comprises a door configured, in a closed position thereof, to cover the open bottom of said chamber when the payload release unit is in its storage position, and, in an open position thereof, to allow the projection of the payload release unit from the chamber.

12. The aircraft pylon according to claim 11 , wherein said door is configured to pivot between said open and closed positions thereof about a door axis being substantially parallel to said pylon axis.

13. The aircraft pylon according to claim 12 , wherein said door, in a fully open position thereof, lies substantially in registration with a vertical outer surface of said housing.

14. The aircraft pylon according to claim 11 , wherein said door comprises biasing elements configured to bias said door towards its closed position.

15. The aircraft pylon according to claim 14 , further comprising a securing arrangement configured to secure the door in its open position.

16. The aircraft pylon according to claim 11 , wherein said payload release unit includes one or more sway braces for attaching the payload thereto, each of said sway braces comprising a vertical bearing member and a laterally projecting carrying arm having a length which is larger than the width of said chamber, said carrying arms being external to the chamber when the payload release unit is in its operational position, the pylon being configured for facilitating rotation of said sway braces upon shifting of the payload release unit from the operational position to the storage position, wherein said door is configured to facilitate the rotation of the sway braces upon closing.

17. The aircraft pylon according to claim 16 , wherein said door comprises, on an interior surface thereof, a socket corresponding to each of the sway braces, each socket being configured to receive therein an end of the carrying arm of its corresponding sway brace, and to bear upon it in the direction of rotation as the door closes.

18. The aircraft pylon according to claim 17 , wherein each of said sockets is formed with an angled side wall for the bearing.

19. The aircraft pylon according to claim 1 , wherein said pylon axis is substantially parallel to a direction of flight of the aircraft.

Assignees

• Israel Aerospace Ind Ltd

Inventors

• Herzig Yoav
• Marom Daniel

Classifications

• B64C1/26

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64D1/10

  Stowage arrangements for the devices in aircraft · CPC title

• B64D1/08

  the articles being load-carrying devices · CPC title

• B64D1/04 Primary

  the articles being explosive, e.g. bombs · CPC title

• B64C1/1407

  Doors; surrounding frames · CPC title