Additively manufactured flyaway tools for aircraft
An airfoil component assembly for an aircraft includes an additively manufactured flyaway tool including an infill support core and an interface sheet surrounding the infill support core, a spar formed from one or more layers of composite material disposed on the interface sheet of the flyaway tool and a skin formed from one or more layers of composite material disposed on the spar and the interface sheet of the flyaway tool. The flyaway tool, the spar and the skin form the airfoil component assembly for use by the aircraft in flight.
1. An airfoil component assembly for an aircraft comprising:
an additively manufactured flyaway tool including an infill support core formed from fiber-reinforced polymer and an interface sheet surrounding the infill support core, the interface sheet integral with the infill support core and having a different density than the infill support core;
a spar formed from one or more layers of composite material disposed on the interface sheet of the flyaway tool; and
a skin formed from one or more layers of composite material disposed on the spar and the interface sheet of the flyaway tool;
wherein the flyaway tool, the spar and the skin form the airfoil component assembly for use by the aircraft in flight.
2. The airfoil component assembly as recited in claim 1 wherein the flyaway tool forms an inner mold line tool.
3. The airfoil component assembly as recited in claim 1 wherein the flyaway tool is formed from a plurality of flyaway tool segments.
4. The airfoil component assembly as recited in claim 1 wherein the flyaway tool further comprises a 3D printed flyaway tool.
5. The airfoil component assembly as recited in claim 1 wherein the infill support core forms a polygonal pattern.
6. The airfoil component assembly as recited in claim 1 wherein a forward edge of the flyaway tool forms a spar indentation and wherein the spar is disposed on the spar indentation.
7. The airfoil component assembly as recited in claim 1 wherein the infill support core forms an organic pattern.
8. The airfoil component assembly as recited in claim 3 wherein the plurality of flyaway tool segments comprise interlocking flyaway tool segments.
9. An aircraft comprising:
a fuselage; and
an airfoil component assembly comprising:
an additively manufactured flyaway tool including an infill support core formed from fiber-reinforced polymer and an interface sheet surrounding the infill support core, the interface sheet integral with the infill support core and having a different density than the infill support core;
a spar formed from one or more layers of composite material disposed on the interface sheet of the flyaway tool; and
a skin formed from one or more layers of composite material disposed on the spar and the interface sheet of the flyaway tool;
wherein the flyaway tool, the spar and the skin form the airfoil component assembly for use by the aircraft in flight.
10. The aircraft as recited in claim 9 wherein the airfoil component assembly further comprises a wing.
11. The aircraft as recited in claim 9 wherein the airfoil component assembly further comprises a rotor blade selected from the group consisting of a main rotor blade or a tail rotor blade.
12. The aircraft as recited in claim 9 wherein the airfoil component assembly further comprises a stabilizer selected from the group consisting of a horizontal stabilizer or a vertical stabilizer.
13. The aircraft as recited in claim 9 wherein the airfoil component assembly further comprises a control surface selected from the group consisting of an elevator or a rudder.
14. The aircraft as recited in claim 9 wherein the airfoil component assembly further comprises a pylon.
15. The aircraft as recited in claim 9 wherein the flyaway tool forms an inner mold line tool.
16. The aircraft as recited in claim 9 wherein the flyaway tool is formed from a plurality of flyaway tool segments.
17. The aircraft as recited in claim 9 wherein the flyaway tool further comprises a 3D printed flyaway tool.
18. The aircraft as recited in claim 9 wherein the infill support core forms a polygonal pattern.
19. The aircraft as recited in claim 9 wherein the infill support core forms an organic pattern.
20. The aircraft as recited in claim 16 wherein the plurality of flyaway tool segments comprise interlocking flyaway tool segments.