Fuselage structure made of composite material

1. A fuselage structure of composite material, comprising:

at least one panel being formed of at least one group of composite layers and having sandwich elements; and

at least one beam mounted the panel and provided with a flange positioned at least at one of its respective ends, and an essentially even outer surface and an essentially even inner surface at its flange, wherein the flange is configured for adhesive engagement with the at least one panel and the flange is in form locking engagement with the at least one group of composite layers of the panel;

wherein sandwich elements of the at least one panel are apart from the areas of contact between the at least one panel and the at least one beam;

wherein the at least one group of composite layers includes an outer group of composite layers being interrupted with a hole through which the beam is reaching;

wherein the essentially even inner surface at the flange of the beam is mounted to the outside of the outer group of composite layers; and

wherein the outer group of composite layers with the hole is overlapping partly the even inner surface for form lock with flange.

2. A fuselage structure according to claim 1 , wherein the at least one group of composite layers of the panel is overlapping onto the flange of the beam for the form locking engagement.

3. A fuselage structure according to claim 1 , wherein the at least one end of the at least one beam is T-shaped.

4. A fuselage structure according to claim 1 , wherein the at least one group of composite layers of the panel is interrupted for the form locking engagement with the flange of the beam.

5. A fuselage structure according to claim 1 , wherein the at least one panel is formed of two groups of composite layers.

6. A fuselage structure according to claim 5 , wherein the at least one panel is formed with an extra group of composite layers inside of the two groups of composite layers.

7. A fuselage structure according to claim 5 , wherein the inner layer of the panel is interrupted for the interlocking engagement with the flange of the beam.

8. A fuselage structure according to claim 1 , wherein flange is provided at its even outer surface with additional composite layers.

9. A fuselage structure according to claim 1 , wherein the at least one group of composite layers of the at least one panel includes an inner group of composite layers and an outer group of composite layers; and

wherein sandwich elements are interposed between the inner group of composite layers and the outer group of composite layers.

10. The fuselage structure according to claim 1 , wherein the fuselage structure is configured as a passenger door.

11. An aircraft door formed from a composite material, the door comprising:

a panel formed from an outer group of composite layers and an inner group of composite layers, the panel having sandwich structures interposed between the inner and outer layers to reinforce the panel, wherein the outer group of composite layers provides an outer skin of the door, the outer group of composite layers defining a first cutout;

an additional group of composite layers defining a second cutout, the additional group of composite layers arranged in contact with an inner surface of the inner group of composite layers;

at least one beam having a flange positioned at an end of the beam, the flange being in form locking engagement with the panel to form a monolithic structure;

wherein the inner and outer groups of composite layers are cured to one another to provide a monolithic panel section between the flange and sandwich elements such that the sandwich elements are spaced apart from the flange of the beam;

wherein the beam extends through the first and second cutouts such that an inner surface of the flange is in contact with an outer surface of the outer group of composite layers.

12. The aircraft door according to claim 11 , wherein the inner group of composite layers defines a third cutout; and

wherein the beam extends through the third cutout.

13. The aircraft door according to claim 11 , wherein the outer surface of the flange is generally flush with the outer surface of the outer group of composite layers to provide a smooth outer skin for the door.

14. The aircraft door according to claim 11 , wherein the inner group of composite layers are spaced apart from the flange of the beam.