Probe fastening system and aircraft

1. A probe fastening system, comprising:

a plate having at least one coupling-on recess and having at least two alignment elements arranged in the outer region of the plate, the at least two alignment elements having a cylindrical form extending from a surface of the plate and integrally formed with the surface of the plate;

a backplate having a fastening device for the fastening of a static probe and at least two recesses corresponding with the at least two alignment elements;

at least two peelable shims corresponding with the at least two alignment elements and arranged between the plate and the backplate;

at least two alignment devices corresponding with the at least two alignment elements, the at least two alignment devices configured to extend from a surface of the backplate and to align with the at least two recesses of the backplate to receive corresponding ones of the at least two alignment elements, the at least two alignment devices comprising a corresponding splint configured to be inserted into a corresponding hole of the corresponding alignment device; and

a coupling-on element defining a cavity and configured for isobarically coupling the static probe onto the coupling-on recess,

wherein each of the at least two alignment elements is surrounded by one of the at least two peelable shims, and

wherein the at least two alignment elements are arranged symmetrically on the plate.

2. The fastening system according to claim 1 , wherein the at least two alignment elements comprise an even number of alignment elements arranged pairwise on substantially opposite sides of the plate.

3. The fastening system according to claim 2 , wherein the at least two alignment elements comprise four alignment elements arranged rotationally symmetrically.

4. The fastening system according to claim 1 , wherein the at least two alignment elements comprise an external thread; and the at least two alignment devices comprise nuts with internal threads adapted to the external threads of the at least two alignment elements.

5. The fastening system according to claim 4 , wherein each of the at least two alignment elements has a laterally arranged recess; and the splint is configured to be inserted into and wedged in the recess of one of the at least two alignment elements.

6. The fastening system according to claim 5 , wherein the at least two alignment elements are of hollow form.

7. The fastening system according to claim 4 , wherein the at least two alignment devices comprise a cover arranged in each case over one of the at least two alignment elements.

8. The fastening system according to claim 1 , further comprising fastening means for fastening the plate to the backplate.

9. The fastening system according to claim 8 , wherein the fastening means comprise a peelable spacer element.

10. The fastening system according to claim 1 , wherein the backplate has a wall element and the fastening device are formed as part of the wall element.

11. The fastening system according to claim 1 , wherein the coupling-on element is formed integrally with the plate.

12. The fastening system according to claim 1 , wherein the coupling-on element is formed integrally with the backplate.

13. A clamping apparatus for the mounting of a fastening system according to claim 1 onto an aircraft skin, wherein the clamping apparatus comprises:

a body configured to fill the cavity defined by the coupling-on element; and

a fixing plate configured to be connected to the fastening device.

14. An aircraft having a fastening system according to claim 1 arranged on the fuselage of the aircraft, wherein the fastening system is arranged such that one of the at least two alignment elements of the fastening system is oriented in a direction of flight of the aircraft.