Sectioned self-mating modular satellite buses

Patent metadata

Field	Value
Publication number	US-10689131-B2
Application number	US-201816028821-A
Country	US
Kind code	B2
Filing date	Jul 6, 2018
Priority date	Jul 6, 2018
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

A satellite configuration includes a plurality of individual satellite buses each having a number of side panels that form a polygonal shape, where the individual satellite buses collectively fit together to form the satellite configuration having a regular polygon shape. A method of producing the satellite configuration includes forming a plurality of individual satellite buses each having a polygonal shape, and fitting the individual satellite buses together to form the satellite configuration in a regular polygonal shape.

First claim

What is claimed is:

1. A sectioned satellite bus arrangement comprising:
a plurality of separate satellite buses each having a polygonal shape formed using at least side panels mated using nesting joggle features;
wherein the plurality of separate satellite buses each fit together to form a regular polygon; and
wherein each of the plurality of separate satellite buses comprise:
a plurality of side panels arranged into the polygonal shape by at least nesting flanged longitudinal edges of each side panel into flanged longitudinal edges of adjacent side panels;
each of the plurality of side panels comprising a compressed composite material forming a front surface flanked by a first longitudinal edge and a second longitudinal edge;
the first longitudinal edge of each side panel comprising a flange forming an angle with the front surface;
the second longitudinal edge of each side panel comprising a flange forming an angle with the front surface; and
wherein a surface of the flange along the first longitudinal edge of each side panel nests with a surface of the flange along the second longitudinal edge of the adjacent side panel to form a joggle.

2. The sectioned satellite bus arrangement of claim 1 , wherein the sectioned satellite bus is configured to fit into a nose cone of a rocket.

3. The sectioned satellite bus arrangement of claim 1 , wherein each of the separate satellite buses has the same polygonal shape.

4. The sectioned satellite bus arrangement of claim 1 , comprising two isosceles trapezoidal satellite buses that fit together to form a hexagonal sectioned satellite bus.

5. The sectioned satellite bus arrangement of claim 1 , wherein each of the plurality of separate satellite buses are triangular.

6. The sectioned satellite bus arrangement of claim 1 , wherein one of the plurality of separate satellite buses forms a first half of the regular polygon and a remainder of the plurality of separate satellite buses together form a second half of the regular polygon.

7. The sectioned satellite bus arrangement of claim 1 , further comprising a solar panel attached to one side panel or top panel of each of the separate satellite buses with a mounting flange.

8. The sectioned satellite bus arrangement of claim 7 , wherein each of the solar panels is folded against one side panel of a respective separate satellite bus when the satellite bus is fit together with one or more separate satellite buses to form the sectioned satellite bus.

9. The sectioned satellite bus arrangement of claim 1 , wherein each of the separate satellite buses comprises an aperture in at least one side panel for attachment of an external component.

10. A satellite bus comprising:
a plurality of side panels coupled at mating edges with nesting joggle features that form a polygonal shape;
wherein the satellite bus fits together with one or more other satellite buses to form a sectioned satellite bus arrangement having a regular polygon shape; and
wherein the satellite bus comprises:
the plurality of side panels arranged into the polygonal shape by at least nesting flanged longitudinal edges of each side panel into flanged longitudinal edges of adjacent side panels;
each of the plurality of side panels comprising a compressed composite material forming a front surface flanked by a first longitudinal edge and a second longitudinal edge;
the first longitudinal edge of each side panel comprising a flange forming an angle with the front surface;
the second longitudinal edge of each side panel comprising a flange forming an angle with the front surface; and
wherein a surface of the flange along the first longitudinal edge of each side panel nests with a surface of the flange along the second longitudinal edge of the adjacent side panel to form a joggle.

11. The satellite bus of claim 10 , wherein the plurality of side panels form a half-hexagon shape.

12. The satellite bus of claim 10 , wherein the plurality of side panels form a quarter-hexagon shape.

13. The satellite bus of claim 10 , wherein the plurality of side panels form a triangle shape.

14. The satellite bus of claim 10 , further comprising a solar panel attached to one of the side panels or a top panel with a mounting flange.

15. The satellite bus of claim 14 , wherein the solar panel is folded against one of the side panels when the satellite bus is fit together with one or more other satellite buses to form the sectioned satellite bus arrangement.

16. The satellite bus of claim 10 , wherein at least one of the side panels comprises an aperture for attachment of an external component.

17. A satellite comprising the satellite bus of claim 10 .

18. A method of producing a sectioned satellite bus arrangement, comprising:
forming a plurality of separate satellite buses each having a polygonal shape and each comprising a plurality of side panels coupled at mating edges with nesting joggle features;
fitting each of the plurality of separate satellite buses together to form the sectioned satellite bus arrangement in a regular polygonal shape; and
wherein forming each of the plurality of separate satellite buses further comprises:
forming the plurality of side panels arranged into the polygonal shape by at least nesting flanged longitudinal edges of each side panel into flanged longitudinal edges of adjacent side panels;
forming each of the plurality of side panels with a compressed composite material that forms a front surface flanked by a first longitudinal edge and a second longitudinal edge;
forming the first longitudinal edge of each side panel as comprising a flange that forms an angle with the front surface;
forming the second longitudinal edge of each side panel as comprising a flange that forms an angle with the front surface; and
forming a surface of the flange along the first longitudinal edge of each side panel by at least nesting with a surface of the flange along the second longitudinal edge of the adjacent side panel to form a joggle.

19. The method of claim 18 , further comprising:
aligning the first longitudinal edge of each side panel with the second longitudinal edge of an adjacent side panel, such that the first longitudinal edge of each side panel is nested with the second longitudinal edge of the adjacent side panel using angled joggle features formed into the first longitudinal edge and the second longitudinal edge;
securing the first longitudinal edge of each side panel to the second longitudinal edge of the adjacent side panel;
attaching a top panel to each of the side panels along a top edge of each side panel; and
attaching a base to each of the side panels along a bottom edge of each side panel.

20. The method of claim 19 , further comprising using a die to form each of the plurality of side panels comprising at least the angled joggle features formed by the die into the first longitudinal edge and the second longitudinal edge.

Assignees

• Vector Launch Inc
• Lockheed Corp

Inventors

• Fraze Raymond Edward

Classifications

• B64G1/2222

  Folding · CPC title

• B64G1/428

  Power distribution and management · CPC title

• B29C70/46

  using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs · CPC title

• B64G1/10 Primary

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• B29L2031/3097

  Cosmonautical vehicles; Rockets · CPC title