Corrugated payload adaptor structure
A spacecraft. The spacecraft includes a rocket engine; a first stage connected to the rocket engine; and a payload stage connected to the first stage. The spacecraft also includes a payload structure inside the payload stage between a first compartment of the payload stage and a second compartment of the payload stage. The payload structure may be a single shell that has a corrugated shape such that an inside surface and an outside surface of the payload structure vary in shape to form the corrugations.
1. A spacecraft comprising:
a rocket engine;
a first stage connected to the rocket engine;
a payload stage connected to the first stage; and
a payload structure inside the payload stage between a first compartment of the payload stage and a second compartment of the payload stage, the payload structure being a single shell that has a corrugated shape such that an inside surface and an outside surface of the payload structure vary in shape to form the corrugations;
wherein the corrugations of the single shell vary in period along a longitudinal direction of the single shell, the period comprising a measure of how close the corrugations are to each other.
2. The spacecraft of claim 1 , wherein the single shell also forms a frustoconical shape.
3. The spacecraft of claim 1 , wherein the single shell comprises a composite material.
4. The spacecraft of claim 3 , wherein the composite material comprises either a fiber reinforced laminate material or a composite material composed of short fibers in a plastic matrix.
5. The spacecraft of claim 4 , wherein the composite material is completely solid.
6. The spacecraft of claim 2 , wherein the corrugations of the single shell vary in amplitude along a longitudinal direction of the frustoconical shape, the amplitude comprising a height between where the corrugations reach a maximum or a minimum relative to an average distance between minimums and maximums of the corrugations.
7. The spacecraft of claim 6 , wherein the amplitude is greatest at an apex of the single shell and is least at a base of the single shell.
8. The spacecraft of claim 7 , wherein the period is shortest at the apex and longest at the base.
9. The spacecraft of claim 1 , wherein a thickness of the single shell varies along the longitudinal direction of the single shell.
10. The spacecraft of claim 1 , wherein the corrugations are arranged such that the single shell comprises a sinusoidal wave or a sinusoidal-like wave.
11. The spacecraft of claim 1 , wherein the corrugations are arranged such that the single shell comprises one of a square wave, a tringle wave, and a saw-tooth wave.
12. The spacecraft of claim 1 , wherein a thickness of the single shell varies along the longitudinal direction of the single shell, the thickness being greatest on a first side of the single shell and least on a second side of the single shell.
13. The spacecraft of claim 1 , wherein the period is shortest at a first side of the single shell and is longest at a second side of the single shell.
14. The spacecraft of claim 1 , wherein the single shell is manufactured by one of:
forming the single shell as a sheet and wrapping the single shell into a frustoconical shape; and
forming the single shell in the frustoconical shape by a molding process.
15. A payload structure comprising:
a shell comprising a fiber-reinforced composite material, the shell having a corrugated frustoconical shape such that an inside surface and an outside surface of the payload structure vary in shape to form corrugations, and wherein corrugations vary in at least one of amplitude and period along a longitudinal direction of the shell, the amplitude comprising a height between where the corrugations reach a maximum or a minimum relative to an average distance between minimums and maximums of the corrugations, the period comprising a measure of how close the corrugations are to each other.
16. The payload structure of claim 15 , wherein the corrugations vary in both amplitude and period.
17. The payload structure of claim 16 , wherein the amplitude is greatest at an apex of the shell, wherein the amplitude is least at a base of the shell, wherein the period is shortest at the apex, and wherein the period is longest at the base.
18. The payload structure of claim 17 , wherein the shell varies in thickness, and wherein the shell is thickest at the apex and thinnest at the base.
19. A spacecraft comprising:
a rocket engine;
a first stage connected to the rocket engine;
a payload stage connected to the first stage; and
a payload structure inside the payload stage between a first compartment of the payload stage and a second compartment of the payload stage, the payload structure being a single shell that has a corrugated shape such that an inside surface and an outside surface of the payload structure vary in shape to form the corrugations;
wherein the corrugations of the single shell vary in amplitude along a longitudinal direction of the single shell, the amplitude comprising a height between where the corrugations reach a maximum or a minimum relative to an average distance between minimums and maximums of the corrugations.
20. The spacecraft of claim 19 , wherein the single shell also forms a frustoconical shape.