TOLERANCE COMPENSATION COMPOSITION AND SEALANT

Abstract

A curable material is disclosed for simultaneous filling of tolerances and for sealing of components to be bonded in aircraft construction.

The curable material can be made of fiber-reinforced plastic (CFRP). The curable material enables simultaneous structural adhesive bonding. The curable material can be based on two-component epoxy resin.

Claims

1. A curable material for simultaneous filling of tolerances and for sealing of components to be bonded in aircraft construction.

2. The curable material according to claim 1, made of fiber-reinforced plastic (CFRP).

3. The curable material according to claim 1, wherein the curable material enables simultaneous structural adhesive bonding.

4. The curable material according to claim 1, based on two-component epoxy resin.

5. The curable material according to claim 1, having a modulus of elasticity having nonlinear dependence on shear stress and deflection.

6. The curable material according to claim 1, having a modulus of elasticity represented by: $E\left(t\right)=\frac{\left(t\right)}{\mathrm{.Math.}}$ $\mathrm{with}.Math..Math.=\mathrm{shear}.Math..Math.\mathrm{stress},\mathrm{.Math.}=\mathrm{deflection}.Math..Math.\mathrm{and}.Math..Math.t=\mathrm{time}.$

7. The curable material according to claim 1, wherein the curable material is drillable.

8. The curable material according to claim 1, having tack in order to hold bonded components together firmly but flexibly with respect to one another.

9. The curable material according to claim 1, having curability at 55 C. to 120 C.

10. The curable material according to claim 9, having curability below 90 C.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0008] In the figures, identical reference numerals are used for identical or at least similar elements, components or aspects. It should be noted that there follows a detailed description of embodiments that are merely illustrative and not restrictive.

[0009] FIG. 1 shows two components between which there is a tolerance-related gap.

[0010] FIG. 2 shows two components, the mutually facing surfaces of which are activated. This can be effected physically (e.g. grinding, corona) or chemically (e.g. etching).

[0011] FIG. 3 shows two components, the mutually facing surfaces of which are cleaned.

[0012] FIG. 4 shows two components, with a composition according to the disclosure herein positioned in the tolerance-related gap between them.

[0013] FIG. 5 shows two components bonded by composition according to the disclosure herein.

DETAILED DESCRIPTION

[0014] FIG. 1 shows two components (1) and (2) between which there is a tolerance-related gap (3).

[0015] FIG. 2 shows two components (1) and (2), the mutually facing surfaces of which are activated (4). This can be effected physically (e.g. grinding, corona) or chemically (e.g. etching).

[0016] FIG. 3 shows two components (1) and (2), the mutually facing surfaces of which are cleaned (5).

[0017] FIG. 4 shows two components (1) and (2), with a composition (6) according to the disclosure herein positioned in the tolerance-related gap (3) between them. This is a 2-component epoxy resin which, after curing, has a modulus of elasticity dependent on shear stress. In a further embodiment, the composition (7) according to the disclosure herein is injected between two abutting components (1) in order to fill and to seal both the vertical gap between the two components (1) and the gap between the components (1) and (2).

[0018] FIG. 5 shows two components (1) and (2) bonded by composition (6) according to the disclosure herein

[0019] In a manner completely surprising to the person skilled in the art, it has been found that a curable material for simultaneous filling of tolerances and for sealing of components to be bonded in aircraft construction remedies the disadvantages of the prior art. It is preferable here that the components to be bonded in aircraft construction consist of or comprise fiber-reinforced plastic (CFRP). It is preferable here that the material simultaneously enables structural adhesive bonding. It is preferable here that the material is formulated on the basis of two-component epoxy resin. It is preferable here that the modulus of elasticity thereof has nonlinear dependence on shear stress and deflection. Modulus of elasticity:

[00001]$E=\frac{}{\mathrm{.Math.}}.Math..Math.\mathrm{with}.Math..Math.=\mathrm{tension},\mathrm{.Math.}=\mathrm{elongatio}$

[0020] It is preferable here that the material has a modulus of elasticity that obeys the formula:

[00002]$E\left(t\right)=\frac{\left(t\right)}{\mathrm{.Math.}}$$\mathrm{with}.Math..Math.=\mathrm{shear}.Math..Math.\mathrm{stress},\mathrm{.Math.}=\mathrm{deflection}.Math..Math.\mathrm{and}.Math..Math.t=\mathrm{time}.$

[0021] This means that the material has a high modulus of elasticity under an abrupt significant impulse, and a low modulus of elasticity under the influence of normal impulses that act over comparatively longer periods.

[0022] It is preferable here that the material is drillable. It is preferable here that the material has tack in order to hold the bonded components together firmly but flexibly with respect to one another. It is preferable here that it is curable at 55 C. to 120 C., preferably below 90 C.

[0023] The above-described aspects and further aspects, features and advantages of the disclosure herein can likewise be inferred from the examples of the embodiments that are described hereinafter with reference to the appended drawings.

[0024] While the disclosure herein has been illustrated and described in detail in the drawings and the preceding description, the intention is that such illustrations and descriptions are merely illustrative or exemplary and not restrictive, such that the disclosure herein is not restricted by the embodiments disclosed. In the claims, the word having does not exclude other elements and the indefinite article a does not exclude a multitude.

[0025] Merely the fact that particular features are mentioned in different dependent claims does not restrict the subject-matter of the disclosure herein. Combinations of these features can also be used advantageously. The reference numerals in the claims are not intended to restrict the scope of the claims.

[0026] While at least one exemplary embodiment of the invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms comprise or comprising do not exclude other elements or steps, the terms a, an or one do not exclude a plural number, and the term or means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.

LIST OF REFERENCE NUMERALS

[0027] 1 component [0028] 2 component [0029] 3 gap [0030] 4 means of activating the surfaces [0031] 5 means of cleaning the surfaces [0032] 6 composition according to the invention [0033] 7 injection of composition according to the invention