Component arrangement on an aircraft structure, and a method for the installation of a component into an aircraft structure

1. A component arrangement on an aircraft structure, comprising:

at least one mounting structure connected with the aircraft structure,

at least one component configured to be mounted to the aircraft structure, and

at least one component carrier for the reception of the component to be mounted,

wherein the component carrier is configured as a one-piece aerodynamic plate and wherein the installation of the component takes place directly on the aerodynamic plate,

the component carrier being connected with the mounting structure, wherein the component carrier is inserted into a central receptacle of the round, approximately ring-shaped mounting structure from an inner side of the aircraft, wherein a supporting surface of a ring-shaped collar of the component carrier abuts against a seating face of a flange of the mounting structure, wherein the supporting surface is facing away from the inner side of the aircraft and the seating face is facing towards the inner side of the aircraft and

an outer surface of the component carrier, facing away from the component, extending approximately flush with an outer surface of the aircraft structure.

2. The component arrangement according to claim 1 , wherein said aircraft structure comprises a fuselage structure of an aircraft.

3. The component arrangement according to claim 1 , wherein said component comprises a measuring device.

4. The component arrangement in accordance with claim 1 , wherein the mounting structure is connected with an inner surface of the aircraft structure.

5. The component arrangement in accordance with claim 1 , wherein the component carrier has a receiving section for the reception of a projection of the component to be mounted.

6. The component arrangement in accordance with claim 5 , wherein the receiving section has an abutment face, facing towards the component, which can be brought into abutment against a flange face of the component.

7. The component arrangement in accordance with claim 6 , wherein at least one seal is arranged in a ring shaped groove of the abutment face.

8. The component arrangement in accordance with claim 7 , wherein said at least one seal comprises a sealing ring.

9. The component arrangement in accordance with claim 5 , wherein an end face of the projection of the component, via at least one thermally effective seal which thermally couples the component and the component carrier, abuts against a contact face of the component carrier.

10. The component arrangement in accordance with claim 1 , wherein a mounting web of the component carrier is approximately cup-shaped in design and the mounting structure is approximately ring-shaped, the component carrier being inserted in the mounting structure.

11. The component arrangement in accordance with claim 1 , wherein a supporting surface of the component carrier abuts against a seating face of the mounting structure.

12. The component arrangement in accordance with claim 1 , wherein the component carrier has an approximately L-shaped flange region with a ring-shaped collar, which is connected with the mounting structure.

13. The component arrangement in accordance with claim 1 , wherein the at least one component is a pressure measuring device.

14. The component arrangement in accordance with claim 13 , wherein the pressure measuring device is a static pressure load cell.

15. A method for the installation of a component into an aircraft structure, comprising the steps:

mounting a mounting structure on the aircraft structure,

connecting the component with the mounting structure via a component carrier, wherein the component carrier is designed as a one-piece aerodynamic plate and wherein the installation of the component takes place directly on the aerodynamic plate,

with an outer surface of the component carrier, facing away from the component, extending approximately flush with an outer surface of the aircraft structure, wherein the component carrier is inserted into a central receptacle of the round, approximately ring-shaped mounting structure from an inner side of the aircraft, wherein a supporting surface of a ring-shaped collar of the component carrier abuts against a seating face of a flange of the mounting structure, wherein the supporting surface is facing away from the inner side of the aircraft and the seating face is facing towards the inner side of the aircraft.

16. The method according to claim 15 , wherein the component is a measuring device on a fuselage structure of an aircraft.

17. The method in accordance with claim 15 , including the further step of connecting the mounting structure with the aircraft structure such that a seating face for the component carrier has a defined clearance from the outer surface of the aircraft structure.