Structure element for an aircraft

• US 20060273690A1
• Filed: 01/17/2006
• Published: 12/07/2006
• Est. Priority Date: 01/18/2005
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE), EADS Deutschland GmbH (Airbus SE)
• Inventors: Konstanzer, Peter, Frankenberger, Eckart
• Granted Patent: US 7,598,657 B2
• Time in Patent Office: Days
• US Class Current: 310/328
• CPC Class Codes: B64C 1/06 Frames; Stringers; Longerons ; Fuselage sections
• CPC Class Codes: B64C 1/18 Floors
• CPC Class Codes: B64C 1/40 Sound or heat insulation , e.g. using insulation blankets

Abstract

Nowadays floor structures in the fuselage of aeroplanes, which floor structures comprise transverse floor girders, are usually connected to the frame on the right and left by means of rivets and are in turn supported vertically downward by the frame by way of Samer rods. According to one embodiment of the present invention a structural element for an aircraft is stated, comprising an active element and a passive element. In this way additional stiffening of the fuselage, a reduction in fuselage deformation, or active vibration dampening can be provided without additional weight.

Claims

1. A structural element for an aircraft, the structural element comprising:

an active element; and

a passive element;

wherein the active element is adapted for controllable or regulable active introduction of forces into the passive element; and

wherein the structural element is adapted to stiffen a fuselage, to reduce deformation of the fuselage, or to dampen vibrations in the fuselage.

2. The structural element of claim 1,

wherein furthermore the active element is adapted for actively stiffening the structural element;

and

wherein the active element is essentially integrated in the passive element.

3. The structural element of claim 1,

wherein the active element comprises piezoceramics;

and

wherein the piezoceramics are deformable by applying a voltage signal to the piezoceramics.

4. The structural element of claim 3,

wherein electrical contacts are provided for measuring a voltage generated by the piezoceramics or for measuring a capacitance of the piezoceramics;

wherein the generated voltage corresponds to a force acting on the piezoceramics; and

wherein the capacitance corresponds to a temperature of the piezoceramics.

5. The structural element of claim 1,

wherein the passive element is selected from the group consisting of floor structure, frame, transverse girder and Samer rod.

6. An aircraft comprising a structural element of claim 1.

7. The aircraft of claim 6, further comprising:

measuring electronics for measuring a voltage generated by the active element or a capacitance of the active element;

evaluation electronics to evaluate the data measured by the measuring electronics; and

control- or regulating electronics to generate a control- or regulating signal for the active element.

8. The use of a structural element of claim 1 in an aircraft.

9. A method for the active structuring of aircraft, comprising the following steps:

generating a control- or regulating signal for an active element of a structural element by means of control- or regulating electronics;

driving the active element with the control- or regulating signal;

wherein the structural element comprises;

the active element; and

a passive element;

wherein the active element is designed for controllable or regulable active introduction of forces into the passive element; and

wherein the structural element is designed for reducing deformation in a fuselage or for dampening vibrations in the fuselage.

10. The method of claim 9, further comprising the following steps:

measuring forces experienced in a structural element by means of measuring electronics;

evaluating the data measured by the measuring electronics by way of evaluation electronics; and

generating a control- or regulating signal for the active element by the control- or regulating electronics on the basis of the evaluation.