Composite structures for aerospace vehicles, and associated systems and methods
Composite structures for space vehicles and other aerospace vehicles are disclosed herein. In one embodiment of the disclosure, a space vehicle pressure vessel includes composite panels or sidewalls with septumized core. In another embodiment, a splice joint for joining septumized composite panels in space vehicle structures is disclosed herein.
1. A space vehicle configured to contain at least one of crew or payload, the space vehicle comprising:
a septumized composite sandwich panel that forms a damage resistant outer wall of the space vehicle, wherein the septumized composite sandwich panel comprises
an outer face sheet that forms an exterior surface of the outer wall of the space vehicle;
an inner face sheet spaced apart from the outer face sheet;
at least one intermediate sheet disposed between the outer and inner face sheets;
a first core portion disposed between the outer face sheet and the intermediate sheet; and
a second core portion disposed between the inner face sheet and the intermediate sheet, wherein the septumized composite panel forms a redundant structure in which the intermediate sheet, the second core portion, and the inner face sheet are configured to perform without structural failure if the outer face sheet and the first core portion are damaged from object impact.
2. The space vehicle of claim 1 wherein the outer and inner face sheets, the intermediate sheet, and the first and second core portions form a pressure vessel.
3. The space vehicle of claim 1 wherein the outer and inner face sheets, the intermediate sheet, and the first and second core portions form a pressure vessel configured to maintain an internal pressure that is greater than the external pressure.
4. The space vehicle of claim 1 wherein the outer and inner face sheets, the intermediate sheet, and the first and second core portions form a space vehicle capsule.
5. The space vehicle of claim 1 wherein the outer face sheet, the inner face sheet, and the intermediate sheet are comprised of fiber reinforced epoxy fabric, and wherein the first and second core portions are comprised of a honeycomb core.
6. The space vehicle of claim 1 wherein at least the outer face sheet includes a layer of electrically conductive material.
7. The space vehicle of claim 1 wherein at least the outer face sheet includes a layer of material with a high ballistic modulus.
8. The space vehicle of claim 1 wherein at least the outer face sheet includes a layer of para-aramid synthetic fiber material.
9. The space vehicle of claim 1 wherein the space vehicle is a pressure vessel, and wherein the septumized composite sandwich panel includes a low porosity sealing layer to at least reduce pressure leakage from the pressure vessel.
10. The space vehicle of claim 1 , wherein the intermediate sheet is a first intermediate sheet, and wherein the septumized composite sandwich panel further comprises:
at least a second intermediate sheet disposed between the outer and inner face sheets and spaced apart from the first intermediate sheet; and
a third core portion disposed between the first intermediate sheet and the second intermediate sheet.
11. The space vehicle of claim 1 wherein the septumized composite sandwich panel further comprises:
four or more core portions disposed between the outer and inner face sheets; and
three or more intermediate sheets alternatingly interposed between each of the core portions.
12. The space vehicle of claim 1 wherein the outer face sheet and the first core portion comprise a first sandwich panel, wherein the inner face sheet and second core portion comprise a second sandwich panel, and wherein the first sandwich panel is attached to the second sandwich panel by a fastener extending through potting compound in the first and second sandwich panels.
13. The space vehicle of claim 1 wherein the septumized composite sandwich panel forms a cylindrical sidewall portion of the space vehicle, and wherein the space vehicle is a pressure vessel.
14. The space vehicle of claim 1 wherein the septumized composite sandwich panel forms a cylindrical sidewall portion of the space vehicle, and wherein the space vehicle further comprises:
a forward cap sealably attached to a forward end of the cylindrical sidewall portion; and
an aft cap sealably attached to an aft end of the cylindrical sidewall portion, wherein the cylindrical sidewall portion, the forward cap, and the aft cap form a pressure vessel.
15. The space vehicle of claim 1 wherein the septumized composite sandwich panel forms a cylindrical sidewall portion of the space vehicle, and wherein the space vehicle further comprises:
a forward cap sealably attached to a forward end of the cylindrical sidewall portion, wherein the forward cap is formed from a septumized composite sandwich structure; and
an aft cap sealably attached to an aft end of the cylindrical sidewall portion, wherein the aft cap is formed from a septumized composite sandwich structure, and wherein the cylindrical sidewall portion, the forward cap, and the aft cap form a pressure vessel.