Aircraft and method for producing an aircraft
The present disclosure relates to an aircraft. The aircraft has a primary structural element, which extends along a main axis of the aircraft, and at least one monolithic structural component, which is produced by a three-dimensional printing method. The aircraft also has an aircraft system for carrying out an aircraft-specific function. The at least one monolithic structural component is fixed on the primary structural element by a fixing device, system, means, or mechanism. The monolithic structural component is embodied to accommodate the aircraft system. The disclosure also relates to a method for producing an aircraft.
1. An aircraft comprising:
a primary structural element extending along a main axis of the aircraft;
a monolithic structural component, which is produced by a three-dimensional printing method, the monolithic structural component comprising a porous structure and forming an outer skin region of the aircraft; and
an aircraft system for carrying out an aircraft-specific function, the aircraft system comprising an electric lead, a hydraulic line, a control cable, a control unit, and a tank;
wherein the monolithic structural component is fixed on the primary structural element; and
wherein the monolithic structural component accommodates the aircraft system.
2. The aircraft according to claim 1 , comprising:
a plurality of additional monolithic structural components;
wherein each monolithic structural component of the plurality of additional monolithic structural components is produced by a three-dimensional printing method;
wherein the monolithic structural components are fixed on the primary structural element adjacent to one another along the main axis of the aircraft to form a basic structure of the aircraft.
3. The aircraft according to claim 1 , wherein the porous structure comprises a plurality of cells or cavities that are internal to the monolithic structural component and the outer skin region of the aircraft comprises an aerodynamically smooth outer surface.
4. The aircraft according to claim 1 , wherein the primary structural element comprises a spar of a wing structure of the aircraft.
5. The aircraft according to claim 1 , wherein the primary structural element comprises a keel beam of a fuselage structure of the aircraft.
6. The aircraft according to claim 1 , wherein:
the primary structural element comprises a spar of a wing structure of the aircraft; and
the primary structural element comprises a keel beam of a fuselage structure of the aircraft.
7. The aircraft according to claim 1 , wherein the aircraft system is embedded in the monolithic structural component.
8. The aircraft according to claim 1 , wherein the monolithic structural component is fixed on the primary structural element with a force-fit joint, a form-fit joint, or a material joint.
9. The aircraft according to claim 1 , wherein the monolithic structural component is produced from a metallic alloy.
10. The aircraft according to claim 9 , wherein composition of the metallic alloy of the monolithic structural component changes along the primary structural element.
11. A method for producing an aircraft, the method comprising:
providing an elongate primary structural element extending along a main axis of the aircraft;
three-dimensionally printing at least one monolithic structural component, which comprises a porous structure and forms an outer skin region of the aircraft;
providing an aircraft system for carrying out an aircraft-specific function, the aircraft system comprising an electric lead, a hydraulic line, a control cable, a control unit, and a tank;
fixing the at least one monolithic structural component on the primary structural element; and
integrating the aircraft system into a receiving region of the at least one monolithic structural component.
12. The method according to claim 11 , comprising:
integrating the aircraft system into the receiving region of the at least one monolithic structural component during three-dimensional printing of the at least one monolithic structural component.
13. The method according to claim 11 , comprising:
providing a plurality of additional monolithic structural components, wherein each monolithic structural component of the plurality of additional monolithic structural components is produced by a three-dimensional printing method; and
fixing the monolithic structural components on the primary structural element adjacent to one another along the main axis of the aircraft to form a basic structure of the aircraft.
14. The method according to claim 11 , wherein the porous structure comprises a plurality of cells or cavities that are internal to the monolithic structural component and the outer skin region of the aircraft comprises an aerodynamically smooth outer surface.
15. The method according to claim 11 , wherein the primary structural element comprises a spar of a wing structure of the aircraft and/or a keel beam of a fuselage structure of the aircraft.
16. The method according to claim 11 , wherein the aircraft system is embedded in the monolithic structural component.
17. The method according to claim 11 , wherein the fixing of the monolithic structural component on the primary structural element is performed with a force-fit joint, a form-fit joint, or a material joint.
18. The method according to claim 11 , wherein the monolithic structural component is produced from a metallic alloy.
19. The method according to claim 18 , wherein composition of the metallic alloy of the monolithic structural component changes along the primary structural element.