FORCE LEVEL CONTROL FOR AN ENERGY ABSORBER FOR AIRCRAFT

• US 20100051401A1
• Filed: 01/31/2007
• Published: 03/04/2010
• Est. Priority Date: 02/15/2006
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE)
• Inventors: Schröder, Jan, Sperber, Martin, Demary, Michael, Harriehausen, Michael, Humfeldt, Dirk
• Granted Patent: US 8,573,372 B2
• Time in Patent Office: Days
• US Class Current: 188/371
• CPC Class Codes: B60R 22/28 incorporating energy-absorbing devices belt anchors provided with energy-absorbing means for protecting the occupants in case of physical contact therewith B60R21/055; belt retractors comprising energy-absorbing means B60R22/341, B60R22/4676
• CPC Class Codes: B64C 1/062 specially adapted to absorb crash loads
• CPC Class Codes: B64D 25/04 Seat modifications
• CPC Class Codes: F16F 7/123 Deformation involving a bending action, e.g. strap moving through multiple rollers, folding of members F16F7/125, F16F7/128 take precedence
• CPC Class Codes: F16F 7/128 characterised by the members, e.g. a flat strap, yielding through stretching, pulling apart

Abstract

A force level control for an energy absorber is provided for aircraft, and includes an adjustment element and a housing, whereby via the adjustment element, a bending radius of the energy absorber element is continuously adjustable in the housing.

Claims

1. A force level control for an energy absorber for an aircraft, the force level control comprising:

a housing;

an adjustment element; and

a cover plate;

wherein the energy absorber has an energy absorber element for absorption of an acceleration energy by plastic deformation;

wherein the plastic deformation of the energy absorber element takes place within the housing;

wherein via the adjustment element, a bending radius of the energy absorber element is continuously adjustable in the housing; and

wherein the cover plate is, by actuation of the adjustment element, displaceable in the direction of the energy absorber element, so that the energy absorber element runs along a contact surface of the cover plate.

2. The force level control of claim 1, further comprising:

a second adjustment element for displacing the cover plate and;

wherein the second adjustment element is actuatable independently from the first adjustment element.

3. The force level control of claim 1,

wherein the cover plate has a contact surface that is formed such that the energy absorber element bends in the area of the contact surface upon actuation of the adjustment element.

4. The force level control of claim 1, further comprising:

a second energy absorber element;

wherein the housing includes a first cover plate, a second cover plate and a fixed support for the second energy absorber element and the first energy absorber element.

5. The force level control of claim 1, and

wherein the first energy absorber element has a longitudinal slit;

wherein the housing further has an intermediate wall, which is mounted in the region of the slit.

6. The force level control of claim 1, further comprising:

a first attachment region; and

a second attachment region;

wherein the first attachment region is designed for attachment of the energy absorber to a primary structure of the aircraft; and

wherein the second attachment region is designed for attachment of the energy absorber to an inboard device.

7. The force level control of claim 1,

wherein the attachment of the holder to the primary structure or to the inner device is by one or more of screws, rivets, or self-locking locking pins.

8. The force level control of claim 1,

wherein the energy absorber has an energy absorption direction;

and

wherein an energy absorption occurs through the energy absorber upon exceeding a minimal force, which acts in the direction of the energy absorption direction.

9. (canceled)