Connecting device, flap system and aircraft having such a connecting device

Patent metadata

Field	Value
Publication number	US-9797437-B2
Application number	US-201213558973-A
Country	US
Kind code	B2
Filing date	Jul 26, 2012
Priority date	Feb 1, 2010
Publication date	Oct 24, 2017
Grant date	Oct 24, 2017

Abstract

The invention pertains to a connecting device for connecting a first structural component and a second structural component that can be moved relative to the first structural component in an articulated fashion such that three rotatory degrees of freedom are provided.

First claim

The invention claimed is:

1. A flap system of an aircraft, comprising:
at least a structural component of an airframe component;
at least a structural component of a flap component; and
one or more connecting device,
wherein the two structural components are at least partially connected to one another by the one or more connecting device,
wherein the structural component of an airframe component is the first structural component and the structural component of a flap component is the second structural component, or wherein the structural component of an airframe component is the second structural component and the structural component of a flap component is the first structural component,
wherein the one or more connecting device connects the first structural component and the second structural component that is movable relative to the first structural component in an articulated fashion such that three rotational degrees of freedom are provided, the connecting device comprising:
a joint head joint part with a joint head for being accommodated by a receiver of the first structural component and a joint head support with a joint part endpiece for being secured to the second structural component to thereby mount the joint head joint part on the second structural component such that a first load path between the first and the second structural components is formed due to the accommodation of the joint head in the receiver, with the joint head joint part comprising a cavity with an inner cavity surface, wherein the cavity extends through the joint head and the joint head support,
a securing arm with a securing arm endpiece for being secured to the second structural component to thereby mount the securing arm on the second structural component, with the securing arm extending into the cavity of the joint head joint part,

wherein the securing arm respectively is sectionally extending along an inner cavity surface of the joint head support such that the securing arm makes available a second load path between the first and the second structural component in case of a mechanical defect that involves a weakening or rupture of the joint head joint part and an accommodation of a section of the securing arm by the inner cavity surface of the joint head support.

2. The flap system according to claim 1 , wherein the joint head joint part has a multipart design and is composed of the joint head support and the joint head accommodated thereby.

3. The flap system according to claim 1 , wherein the joint head joint part is manufactured in one piece.

4. The flap system according to claim 1 , wherein the securing arm respectively is sectionally extending adjacent to an inner cavity surface of the joint head support such that the securing arm makes available a second load path between the first and the second structural component in case of a mechanical defect that involves a weakening or rupture of the joint head joint part and an accommodation of a section of the securing arm by the inner cavity surface of the joint head support.

5. The flap system according to claim 1 , wherein the cavity that extends through the joint head and the joint head support enlarges behind the joint head support towards the joint head.

6. The flap system according to claim 1 , wherein a clearance is sectionally provided between an outside contour of the securing arm and inside contours of the inner cavity surface of the joint head support and an inner cavity surface of the joint head such that the securing arm is not subjected to a load when the joint head joint part is mechanically intact.

7. The flap system according to claim 1 , wherein a clearance between the securing arm and an inner cavity surface of the joint head support and an inner cavity surface of the joint head amounts to no more than 5% of a maximum diameter of the joint head joint part.

8. The flap system according to claim 1 , wherein a clearance between the securing arm and an inner cavity surface of the joint head support and an inner cavity surface of the joint head amounts to no more than 20% of a minimum material thickness at the respective inner cavity surface.

9. The flap system according to claim 1 , wherein a pivoting range with respect to the rotational degrees of freedom is as large as 60°.

10. The flap system according to claim 1 , wherein a receiver safety is provided for being mounted on the first structural component, wherein the receiver safety prevents the joint head from being removed from the receiver in case of a mechanical defect that involves a weakening in the receiver.

11. The flap system according to claim 1 , wherein the securing arm and the joint head joint part are mountable to the second structural component by a same mount.

12. The flap system according to claim 1 , wherein the joint head or the receiver comprises a coating for improving relative sliding movements at least in contact regions of the joint head and the receiver.

13. The flap system according to claim 1 , wherein sections, in which the securing arm respectively is situated adjacent to an inner cavity surface of the joint head support and an inner cavity surface of the joint head, amount to at least 25% of the inside contour of the joint head joint part.

14. The flap system according to claim 1 , wherein at least one connecting device is provided between an actuator arranged on the airframe component and a regulating flap.

15. An aircraft comprising the flap system of claim 1 .

Assignees

• Dyckrup Werner
• Harding Hauke
• Airbus Operations Gmbh

Inventors

• Dyckrup Werner
• Harding Hauke

Classifications

• F16C11/0604 Primary

  Construction of the male part · CPC title

• F16C2326/43

  Aeroplanes; Helicopters · CPC title

• Y10T403/32631

  Universal ball and socket · CPC title