System for fastening a load to a rotorcraft, and a rotorcraft

Patent metadata

Field	Value
Publication number	US-9487292-B2
Application number	US-201414196167-A
Country	US
Kind code	B2
Filing date	Mar 4, 2014
Priority date	Mar 7, 2013
Publication date	Nov 8, 2016
Grant date	Nov 8, 2016

Abstract

A fastener system ( 10 ) having attachment means ( 15 ) for attaching an external load to a rotorcraft, said fastener system ( 10 ) having a support beam ( 20 ) for attaching the attachment means ( 15 ) to a rotorcraft, said support beam ( 20 ) having a horizontal core ( 25 ) and two lateral section members ( 30 ) extending in elevation from said horizontal core ( 25 ), said fastener system ( 10 ) having a support member ( 50 ) in a central space ( 100 ) between said lateral section members ( 30 ) to carry attachment means ( 15 ), said support member ( 50 ) being connected to each lateral section member ( 30 ). Each lateral section member ( 30 ) includes a web ( 31 ) in elevation connected to the horizontal core ( 25 ), each web ( 31 ) presenting an obtuse angle (α) relative to said horizontal core ( 25 ) in said central space ( 100 ), each lateral section member ( 30 ) being a sloping section member capable of moving closer to said horizontal core ( 25 ) under the effect of vertical forces.

First claim

What is claimed is:

1. A fastener system having attachment means for attaching an external load to a rotorcraft, the fastener system having a support beam for attaching the attachment means to a rotorcraft, the support beam having a horizontal core and two lateral section members extending in elevation from the horizontal core, the fastener system having a support member in a central space between the lateral section members to carry attachment means, the support member being connected to each lateral section member, wherein each lateral section member includes a web in elevation connected to the horizontal core, each web presenting an obtuse angle (α) relative to the horizontal core in the central space, each lateral section member being a sloping section member capable of moving closer to the horizontal core under the effect of vertical forces, the support member including a fitting co-operating with the lateral section members, the fitting including a spring member for moving an attachment means away from a direction extending in the gravity direction, the support beam directly connecting to a fuselage of the rotorcraft.

2. A system according to claim 1 , wherein at least one web extends from a connection end connected to the horizontal core towards a free end, and at least one lateral section member includes a bearing portion secured to the free end of the web.

3. A system according to claim 2 , wherein the bearing portion is parallel to the horizontal core.

4. A system according to claim 1 , wherein at least one lateral section member includes a soleplate for fastening to the horizontal core, and the soleplate is connected to a web by a fastener device.

5. A system according to claim 4 , wherein the soleplate is arranged in the central space.

6. A system according to claim 1 , wherein at least one lateral section member comprises a soleplate for fastening to the horizontal core, and the soleplate is integral with a web so as to form a one-piece mechanical part.

7. A system according to claim 6 , wherein a web has a junction zone with a soleplate, and the junction zone presents a rounded portion to encourage the web to bend towards the horizontal core.

8. A system according to claim 1 , wherein at least one web is hinged to the horizontal core by means of a hinge, and the fastener system includes retaining means connecting one lateral section member to the other lateral section member.

9. A system according to claim 1 , wherein the fitting is fastened to each web between the middle of each web and a connection end of each web that is connected to the horizontal core.

10. A system according to claim 1 , wherein at least one lateral section member has a soleplate for fastening to the horizontal core, and the fitting is fastened to each soleplate.

11. A system according to claim 9 , wherein each web includes an orifice with a pin of the fitting passing therethrough.

12. A rotorcraft, including a fastener system according to claim 1 .

13. A system according to claim 1 , wherein the attachment means is carried by the fitting.

14. A fastener system for attaching an external load to a rotorcraft comprising:
a horizontal support beam to directly connect to a fuselage of the rotorcraft;
first and second lateral members directly connected to and extending in elevation from the beam and defining a central space therebetween, each lateral member having a sloping web section oriented at an obtuse angle relative to the beam in the central space to move closer to the beam in response to an upward vertical force;
a support member positioned within the central space, the support member directly connected to the first and second lateral members and extending therebetween;
a hook connected to the support member and carried in the central space by the support member; and
a spring member connected to the hook and the support member to turn the hook relative to the support beam.

15. A fastener system according to claim 14 wherein the support member is directly connected to each lateral member from a middle of each web section to a connection end of each lateral member, the connection end of each lateral member being directly connected to a respective end region of the horizontal support beam.

16. A fastener system according to claim 14 wherein each lateral member has a soleplate at a first connection end of the lateral member to connect to the horizontal support beam, and a bearing portion at a second free end of the lateral member, the soleplate forming a planar surface to mate with the beam, the bearing portion forming a horizontal segment to face a ground surface, the sloping web section extending between and connecting the soleplate and the bearing portion.

17. A fastener system according to claim 14 wherein each lateral member has a first connection end connected to the horizontal support beam and a second free end; and
wherein the first and second lateral members define transversely the central region as a flared internal space of frustoconical shape extending in elevation from a large base that is open and adjacent to free ends of the first and second lateral members towards a small base level with the beam and adjacent to the connection ends of the first and second lateral members.

18. A fastener system of claim 14 wherein each lateral member extends from the support beam towards a ground surface such that each lateral member is spaced apart from the ground surface when the rotorcraft is standing on the ground surface.

19. A method of fastening an external load to a rotorcraft with the help of a fastener system provided with attachment means, the fastener system having a support beam for attaching the attachment means to a rotorcraft, the support beam having a horizontal core and two lateral section members extending in elevation from the horizontal core, the fastener system having a support member in a central space between the lateral section members in order to carry attachment means, the support member being connected to each lateral section member, wherein each lateral section member is inclined so as to obtain a sloping section member presenting an obtuse angle (α) relative to the horizontal core in the central space so that each lateral section member moves closer to the horizontal core under the effect of vertical forces so as to be less aggressive for a fuselage of the rotorcraft, and wherein the support member is fitted with a fitting provided with a spring member for moving the attachment means away from a direction extending in the gravity direction, the support beam being directly connected to a fuselage of the rotorcraft and being independent of a rotorcraft landing gear.

Assignees

• Airbus Helicopters

Inventors

• Prud'Homme-Lacroix Pierre

Classifications

• Y10T29/49947

  by applying separate fastener · CPC title

• B64C27/04

  Helicopters · CPC title

• B64D9/00 Primary

  Equipment for handling freight; Equipment for facilitating passenger embarkation or the like · CPC title

• B64D1/22 Primary

  Taking-up articles from earth's surface · CPC title