Satellite thermal enclosure

Patent metadata

Field	Value
Publication number	US-2022194635-A1
Application number	US-202117553628-A
Country	US
Kind code	A1
Filing date	Dec 16, 2021
Priority date	Dec 17, 2020
Publication date	Jun 23, 2022
Grant date	—

Abstract

A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.

First claim

What is claimed is:

1 . A satellite assembly, comprising:
a satellite stowed in a launch vehicle, a shroud including a frame supporting a flexible thermal blanket enclosing the satellite.

2 . The satellite assembly of claim 1 , wherein the shroud has a proximal end portion and a distal end portion, the distal end portion being expandable.

3 . The satellite assembly of claim 2 , wherein the distal end portion of the shroud includes a door that expands and opens when deploying the satellite.

4 . The satellite assembly of claim 3 , wherein the door is configured to close after the satellite is deployed.

5 . The satellite assembly of claim 1 , wherein the shroud has trapezoidal sides.

6 . The satellite assembly of claim 1 , wherein the shroud has a stowed position and a deployed position, the satellite constraining lateral movement of the shroud when the shroud is in the stowed position, and releasing lateral constraint when the shroud expands into the deployed position.

7 . The satellite assembly of claim 1 , the shroud having a proximal end portion and a distal end portion, the distal end portion having a door covering an opening framed by a top frame element, a bottom frame element, and two side frame elements, the side frame elements being capable of telescoping between a stowed position and a deployed position for expanding the size of the opening.

8 . The satellite assembly of claim 7 , wherein the satellite engages at least one of the top and bottom frame elements, constraining lateral movement of the shroud, when the side frame elements are in the stowed position.

9 . An apparatus for transporting a satellite to space, comprising:
a launch vehicle, a thermal shroud including a frame and a flexible wall material supported by the frame, the shroud being connected to the launch vehicle and configured for housing a satellite during a launch phase.

10 . The apparatus of claim 9 , wherein the shroud is configured to house a plurality of stacked satellites.

11 . The apparatus of claim 10 , further comprising a ring structure connected to the launch vehicle, the ring structure having a central axis parallel to a launch axis of the launch vehicle, wherein the shroud is mounted on the ring structure.

12 . The apparatus of claim 11 , wherein the shroud has a long axis perpendicular to the launch axis.

13 . The apparatus of claim 9 , wherein the shroud has a proximal end portion and a distal end portion, the distal end portion being expandable.

14 . The apparatus of claim 13 , wherein the distal end portion is expandable only in a direction parallel to a launch axis of the launch vehicle.

15 . An assembly for transporting satellites to space, comprising:
a ring structure having a central axis parallel to a launch direction, a plurality of shrouds extending radially outward from the ring structure, each shroud including a frame supporting a flexible wall material, having a proximal end connected to the ring structure, and having a distal end including a door for permitting deployment of a satellite into space.

16 . The assembly of claim 15 , wherein the distal end of each shroud is expandable from a stowed configuration to a deployed configuration.

17 . The assembly of claim 16 , wherein the distal end of each shroud is expandable only in a direction parallel to the launch direction.

18 . The assembly of claim 15 , wherein each shroud has a top side, a bottom side, and a pair of lateral sides, wherein each of the top side, the bottom side, and the proximal end maintain a constant area while each of the pair of lateral sides and the distal end expand.

19 . The assembly of claim 15 , wherein the distal end of each shroud has a rectangular opening framed by a top strut, a bottom strut, and a pair of opposing side struts, each side strut including a spring for urging the distal end to expand into a deployed configuration.

20 . The assembly of claim 19 , wherein the door has a pair of opposing frame members, each frame member being capable of telescoping in parallel with the pair of opposing side struts.

Assignees

• Boeing Co

Inventors

• Aston Richard W
• Woods Emily Colleen
• Zilz Rachel Elizabeth
• Langmack Michael John
• Hastings Nicole Marie

Classifications

• B64G1/58 Primary

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

• B64G1/643

  for arranging multiple satellites in a single launcher · CPC title

• B64G1/6425

  arrangements for damping vibrations · CPC title

• B64G1/002 Primary

  Launch systems · CPC title

• B64G1/50

  for temperature control · CPC title