Spacecraft with open sides

Patent metadata

Field	Value
Publication number	US-9296493-B2
Application number	US-201313781483-A
Country	US
Kind code	B2
Filing date	Feb 28, 2013
Priority date	Feb 28, 2013
Publication date	Mar 29, 2016
Grant date	Mar 29, 2016

Abstract

A spacecraft may include a module structure having a plurality of module sides. The spacecraft may include a central cylinder extending through a center of the spacecraft. The central cylinder may be the only closed cross-section extending along a longitudinal axis of the spacecraft.

First claim

What is claimed is:

1. A spacecraft, comprising:
a module structure of a spacecraft having a plurality of module sides;
a central cylinder extending through a center of the spacecraft from a top end of the spacecraft to a bottom end of the spacecraft, the central cylinder being the only closed cross-section extending along a longitudinal axis of the spacecraft; and
a pair of rigid panels coupled to opposite sides of the central cylinder and being spaced apart from one another and non-co-planar, a longitudinal axis of the rigid panels being parallel to the longitudinal axis of the spacecraft.

2. The spacecraft of claim 1 , further comprising:
a propellant tank housed within the central cylinder.

3. The spacecraft of claim 1 , wherein:
the module structure includes open sides being devoid of one or more rigid members extending across the open sides.

4. The spacecraft of claim 3 , further comprising:
at least one non-rigid closeout covering at least a portion of an open side.

5. The spacecraft of claim 4 , wherein:
the non-rigid closeout comprises a thermal blanket.

6. The spacecraft of claim 1 , wherein:
the module structure includes a vertical shear panel coupling at least one of the rigid panels to the central cylinder.

7. The spacecraft of claim 6 , wherein:
the module structure includes a top end panel and a bottom end panel mounted on opposite ends of the module structure; and
each one of the rigid panels extending between and interconnecting the top end panel and the bottom end panel.

8. The spacecraft of claim 1 , further comprising:
at least one antenna coupled to at least one of the module sides.

9. The spacecraft of claim 1 , further comprising:
at least one solar panel coupled to at least one of the module sides.

10. The spacecraft of claim 1 , further comprising:
a generally planar thermal radiator panel included with at least one of the module sides.

11. A spacecraft, comprising:
a module structure of a 3-axis-stabilized spacecraft having a plurality of module sides;
a central cylinder extending through a center of the spacecraft from a top end of the spacecraft to a bottom end of the spacecraft;
a propellant tank housed within the central cylinder, the central cylinder being the only closed cross-section extending along a longitudinal axis of the spacecraft; and
a pair of rigid panels coupled to opposite sides of the central cylinder and being spaced apart from one another and non-co-planar, a longitudinal axis of the rigid panels being parallel to the longitudinal axis of the spacecraft.

12. A method of assembling a spacecraft, comprising the steps of:
providing a module structure of a spacecraft having a plurality of module sides;
extending a central cylinder through a center of the spacecraft from a top end of the spacecraft to a bottom end of the spacecraft, the central cylinder being the only closed cross-section extending along a longitudinal axis of the spacecraft; and
coupling a pair of rigid panels to opposite sides of the central cylinder, the rigid panels being spaced apart from one another and non-co-planar, a longitudinal axis of the rigid panels being parallel to the longitudinal axis of the spacecraft.

13. The method of claim 12 , further comprising the step of:
housing a propellant tank within the central cylinder.

14. The method of claim 12 , further comprising the step of:
omitting rigid members from open sides of the module structure.

15. The method of claim 14 , further comprising the step of:
covering at least a portion of an open side with at least one non-rigid closeout.

16. The method of claim 15 , wherein:
the non-rigid closeout comprises a thermal blanket.

17. The method of claim 12 , further comprising the step of:
coupling at least one of the rigid panels to the central cylinder using a vertical shear panel.

18. The method of claim 12 , further comprising the step of:
mounting a top end panel and a bottom end panel mounted on opposite ends of the module structure; and
interconnecting the top end panel and the bottom end panel with at least one of the rigid panels.

Assignees

• Boeing Co

Inventors

• Aston Richard W
• Tomzynska Anna M

Classifications

• B64G1/10 Primary

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

• Y10T29/49826

  Assembling or joining · CPC title

• B64G1/58

  Thermal protection, e.g. heat shields · CPC title

• B64G1/54

  Protection against radiation · CPC title

• B64G1/44

  using radiation, e.g. deployable solar arrays · CPC title