Aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft

Patent metadata

Field	Value
Publication number	US-10399658-B2
Application number	US-201615176292-A
Country	US
Kind code	B2
Filing date	Jun 8, 2016
Priority date	Jun 29, 2015
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.

First claim

What is claimed is:

1. An aircraft comprising a force-absorbing structure comprising a plurality of structural components adapted for absorbing and transmitting forces in an aircraft, at least one of the structural components comprising a first panel element, a second panel element, a first reinforcing structure, and a second reinforcing structure, the first and second panel elements and the first and second reinforcing structure comprising fiber reinforced polymers; the first reinforcing structure being rigidly attached to the first panel element such that at least a first cavity is defined between the first panel element and the first reinforcing structure, the second reinforcing structure being rigidly attached to the second panel element such that at least a second cavity is defined between the second panel element and the second reinforcing structure, the aircraft being a rotorcraft and the force-absorbing structure is provided at a fuselage of the rotorcraft; the reinforcing structures being rigidly attached to the panel elements by means of a collective curing with the panel elements; the rotorcraft comprising a wheel landing gear having a rotatable shaft; at least one of the reinforcing structures being provided on either side of each of the two panel elements; the reinforcing structures on either side of each of the first and second panel elements pivotally bearing on the fuselage a bearing of the rotatable shaft of a wheel landing gear.

2. The aircraft according to claim 1 , wherein each of the reinforcing structures comprises a strap element rigidly attached to one of the panel elements.

3. The aircraft according to claim 2 , wherein each of the strap elements is rigidly attached to one of the panel elements by means of riveting and/or bonding.

4. The aircraft according to claim 1 , wherein the first cavity is at least partly filled with a foam core and/or a honeycomb core.

5. The aircraft according to claim 1 , wherein a third cavity is defined adjacent to the first cavity between the first panel element and the first reinforcing structure, the third cavity being at least partly filled with a foam core and/or a honeycomb core.

6. The aircraft according to claim 1 , wherein a force transmitting attachment shaft is provided for pivotally connecting the rotatable shaft to first panel element and the first reinforcing structure, the force transmitting attachment shaft being non-pivotally connectable to the rotatable shaft by means of at least one associated fixation bolt.

7. The aircraft according to claim 6 , wherein the first panel element and the first reinforcing structure are provided with at least one bearing element, the force transmitting attachment shaft being pivotally accommodated in the at least one bearing element.

8. The aircraft according to claim 6 , wherein the first reinforcing structure is arranged with a predetermined shaping around the force transmitting attachment shaft.

9. The aircraft according to claim 1 , wherein the first reinforcing structure is provided with a first geometry on a first side of the first panel element and with a second geometry on a second side of the first panel element.

10. The aircraft according to claim 1 , wherein the first reinforcing structure comprises at least one opening that is adapted to allow washing out of a dissolvable core provided in the first cavity.

11. A rotorcraft comprising:
a fuselage having a force-absorbing structure and a wheel landing gear having a rotatable shaft;
the force-absorbing structure comprising a plurality of structural components;
at least one of the structural components comprising:
a first panel element attached to a first reinforcing structure defining a first cavity between the first panel element and the first reinforcing structure; and
a second panel element attached to a second reinforcing structure defining a second cavity between the second panel element and the second reinforcing structure, the panel elements and the reinforcing structures comprising fiber reinforced polymers;
each of the first and second reinforcing structures being provided on either side of a respective one of the first and second panel elements; the reinforcing structures pivotally bearing on the fuselage a bearing of the rotatable shaft of the wheel landing gear.

12. The rotorcraft according to claim 11 , wherein each of the reinforcing structures comprises a first portion rigidly attached to one of the panel elements.

13. The rotorcraft according to claim 12 , wherein each of the first portion is rigidly attached to one of the panel elements by riveting and/or bonding.

14. The rotorcraft according to claim 11 , wherein the first cavity is at least partly filled with a foam core and/or a honeycomb core.

15. The rotorcraft according to claim 11 , wherein a third cavity is defined adjacent to the first cavity between the first panel element and the first reinforcing structure, the third cavity being at least partly filled with a foam core and/or a honeycomb core.

16. The rotorcraft according to claim 11 , further comprising a force transmitting attachment shaft pivotally connecting the rotatable shaft to first panel element and the first reinforcing structure, the force transmitting attachment shaft being non-pivotally connectable to the rotatable shaft by at least one associated fixation bolt.

17. The rotorcraft according to claim 16 , wherein the first panel element and the first reinforcing structure have a bearing element, the force transmitting attachment shaft being pivotally accommodated in the bearing element.

18. An aircraft comprising a force-absorbing structure comprising plurality of structural components, at least one of the structural components comprising a first panel element, a second panel element, a first reinforcing structure, and a second reinforcing structure, the panel elements and the reinforcing structure comprising fiber reinforced polymers; the first reinforcing structure attached to the first panel element defining a first cavity between the first panel element and the first reinforcing structure, the second reinforcing structure attached to the second panel element defining a second cavity between the second panel element and the second reinforcing structure, the force-absorbing structure is provided at a fuselage of the aircraft; the aircraft comprising a wheel landing gear having a rotatable shaft; the reinforcing structures being provided on either side of each of the panel elements and pivotally bearing on the fuselage a bearing of the rotatable shaft of a wheel landing gear.

19. The aircraft according to claim 18 , wherein each of the aircraft comprises a rotorcraft.

20. The aircraft according to claim 19 , wherein each of the reinforcing structures comprises a first member rigidly attached to one of the panel elements.

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Von-Wilmowsky Kaspar
• Reichensperger Christian
• Rack Andreas

Classifications

• F16B5/01

  by means of fastening elements specially adapted for honeycomb panels · CPC title

• F16B11/006

  by gluing (gluing of plastics material B29C65/48) · CPC title

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C27/04

  Helicopters · CPC title

• B64C2025/325

  specially adapted for helicopters · CPC title