Actuator mounting method and method for producing an ice protection device as well as mounting device

Patent metadata

Field	Value
Publication number	US-10131449-B2
Application number	US-201414565924-A
Country	US
Kind code	B2
Filing date	Dec 10, 2014
Priority date	Dec 11, 2013
Publication date	Nov 20, 2018
Grant date	Nov 20, 2018

Abstract

An actuator mounting method for mounting at least one actuator involves providing a skin structure and at least one actuator, and fixing the at least one actuator to the inner surface of the skin structure.

First claim

The invention claimed is:

1. An actuator mounting method for mounting at least one actuator on or in a skin structure, comprising the following steps:
a) providing a skin structure;
b) providing at least one actuator configured to deform a surface area of the skin structure; and
c) fixing the at least one actuator to an inner face of the skin structure,
wherein step c) comprises the steps of:
c1) positioning the at least one actuator on a punch for a planar pressing of the at least one actuator against the inner face of the skin structure;
c2) holding the actuator on the punch by a releasable holding element;
c3) pressing the actuator against the inner face of the skin structure by the punch;
c4) connecting the actuator to the inner face; and
c5) releasing or removing the punch.

2. The actuator mounting method of claim 1 , wherein step c4) comprises the steps of:
c4.1) materially bonding the actuator to the inner face;
c4.2) gluing the actuator to the inner face;
c4.2.1) applying an adhesive to the inner face or a surface of the actuator that is to be glued to the inner face, prior to attaching the actuator to the inner face;
c4.2.2) curing the adhesive by pressing on the actuator according to step c3); and
c4.3) interposing an electrical insulation layer between the actuator and the inner face.

3. The actuator mounting method of claim 1 , wherein step c2) comprises the steps of:
c2.1) holding the actuator on the punch using double-sided adhesive tape during the insertion into the skin structure or the attachment to the skin structure.

4. The actuator mounting method of claim 1 , wherein step c3) comprises at least one the steps of:
c3.1) moving the punch in a guided manner by a guide unit;
c3.2) maintaining or keeping constant an application pressure by a force accumulator; and
c3.3) supporting an outer face of the skin structure by a support fixture that is complementary to the outer face.

5. The actuator mounting method according of claim 1 , wherein
step a) includes providing the skin structure with at least one planar surface on the inner face of the skin structure; and
step c) includes fixing the at least one actuator to the at least one planar surface.

6. The actuator mounting method of claim 1 , wherein step b) includes:
b.1) providing at least one piezoelectric actuator.

7. The actuator mounting method of claim 1 , wherein
step b) includes
b.2) providing at least one first actuator for deforming a section of the surface area that is formed on a first longitudinal half of the skin structure, and providing at least one second actuator for deforming a section of the surface area that is formed on a second longitudinal half of the skin structure, and

step c) includes
c5) simultaneously fixing the at least one first actuator to the inner face of the first longitudinal half and of the at least one second actuator to the inner face of the second longitudinal half.

8. A production method for producing a mechanical ice protection unit for an aircraft for keeping a surface area of the aircraft free from ice and/or for de-icing the surface area, the production method comprising:
a) providing a skin structure;
b) providing at least one actuator configured to deform a surface area of the skin structure; and
c) fixing the at least one actuator to an inner face of the skin structure,
d) attaching a heat output device for heating at least part of the skin structure, wherein the skin structure includes on the outer face thereof the surface area to be kept free from ice and to be de-iced.

9. The production method of claim 8 , wherein step d) comprises the steps of:
d1) providing a heat output device that is formed for a linear heat output to generate a predetermined breaking point or a predetermined breaking line or a separation line in ice accumulating on the surface area; and
d2) attaching the heat output device to the inner face of the skin structure in an area of a leading edge or of a stagnation line of a profile body to be formed by the skin structure.

10. A mounting device comprising:
a punch configure to press, in a planar manner, at least one actuator against an inner face of a skin structure for an aircraft to which the at least one actuator is to be fixedly mounted;
a releasable holder configure to hold the at least one actuator on the punch; and
a press-on unit configured to press the punch with the at least one actuator against the inner face of the skin structure.

11. The mounting device of claim 10 , further comprising:
an adhesive application unit configured to apply an adhesive to the inner face or a surface to be bonded to the inner face of the at least one actuator prior to the attachment of the actuator to the inner face; and
a curing unit configured to cure the adhesive while pressing on the actuator.

12. The mounting device of claim 10 , wherein the holder has an adhesion structure for releasably gluing the at least one actuator to the punch.

13. The mounting device of claim 10 , wherein
a) the press-on unit has a guide unit configured to move the punch in a guided manner or a force accumulation element configured to maintain or keep constant an application pressure, or
b) the mounting device has a support fixture configured to support the outer face of the skin structure while pressing the punch.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Strobl Tobias
• Storm Stefan

Classifications

• Y10T29/49826

  Assembling or joining · CPC title

• B64F5/10 Primary

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B32B2605/18

  Aircraft · CPC title

• B64D15/12

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title

• Y10T156/10

  Methods of surface bonding and/or assembly therefor · CPC title