Impact shield structures

Patent metadata

Field	Value
Publication number	US-2023103930-A1
Application number	US-202117907129-A
Country	US
Kind code	A1
Filing date	Mar 11, 2021
Priority date	Mar 27, 2020
Publication date	Apr 6, 2023
Grant date	—

Abstract

In some examples, an impact shield structure for use on a lower earth orbit spacecraft comprises a capture layer to absorb debris incident thereon.

First claim

1 . An impact shield structure for use on a lower earth orbit spacecraft, the impact shield structure comprising:
a capture layer to absorb debris incident thereon.

2 . The impact shield structure as claimed in claim 1 , wherein the capture layer is provided between first and second encapsulating layers on either side thereof.

3 . The impact shield structure as claimed in claim 2 , wherein the first encapsulating layer comprises a layer of graphene foam, a layer of ceramic metallic material, and/or an outer skin of the spacecraft.

4 . The impact shield structure as claimed in claim 2 , wherein the second encapsulating layer comprises a layer of graphene foam.

5 . The impact shield structure as claimed in claim 2 , wherein the capture layer and first and second encapsulating layers form a monolithic layer.

6 . The impact shield structure as claimed in claim 1 , wherein the capture layer comprises a powdered ceramic material.

7 . The impact shield structure as claimed in claim 1 , further comprising an outermost entry layer comprising a self-healing fabric.

8 . The impact shield structure as claimed in claim 1 , further comprising an electromagnetic (EM) shield layer to absorb radio frequency (RF) energy incident on the structure.

9 . The impact shield structure as claimed in claim 8 , wherein the EM shield layer comprises a metallic mesh, metallic sheet, or multiple metallic wires.

10 . The impact shield structure as claimed in claim 8 , wherein the EM shield layer is provided within or as part of the capture layer.

11 . The impact shield structure as claimed in claim 2 , wherein an electromagnetic (EM) shield layer, to absorb radio frequency (RF) energy incident on the structure, is provided within or as part of the first encapsulating layer.

12 . The impact shield structure as claimed in claim 8 , wherein the EM shield layer comprises multiple apertures with a dimension of around 0.1 times a selected target RF wavelength.

13 . The impact shield structure as claimed in claim 1 , wherein the capture layer is so configured as to absorb debris with a diameter of around 1 mm to 1 cm.

14 . The impact shield structure as claimed in claim 1 , wherein the structure has an overall thickness of around 1 cm to 10 cm.

15 . The impact shield structure as claimed in claim 1 , wherein the structure is so configured as to absorb debris directly incident on the structure, and debris that ricochets from an encapsulating layer.

16 . An impact shield structure for use on a lower earth orbit spacecraft, the impact shield structure comprising:
a capture layer to absorb debris incident thereon, the capture layer comprising a powdered ceramic material; a first encapsulating layer on a first side of the capture layer, the first encapsulating layer comprising a layer of graphene foam, a layer of ceramic metallic material, and/or an outer skin of the spacecraft; and a second encapsulating layer on a second side of the capture layer, the second encapsulating layer comprising a layer of graphene foam.

17 . The impact shield structure as claimed in claim 16 , wherein the capture layer and first and second encapsulating layers form a monolithic layer having an overall thickness of around 1 cm to 10 cm.

18 . An impact shield structure for use on a lower earth orbit spacecraft, the impact shield structure comprising:
an electromagnetic (EM) shield layer to absorb radio frequency (RF) energy incident on the structure, the EM shield layer comprising a metallic mesh, metallic sheet configured with apertures, or multiple metallic wires; a capture layer to absorb debris incident thereon, the capture layer comprising a powdered ceramic material; and an outermost entry layer comprising a self-healing fabric; wherein the capture layer is between the EM shield layer and the outermost entry layer.

19 . The impact shield structure as claimed in claim 19 , comprising:
a first encapsulating layer on a first side of the capture layer, the first encapsulating layer comprising a layer of graphene foam, a layer of ceramic metallic material, and/or an outer skin of the spacecraft; and/or a second encapsulating layer on a second side of the capture layer, the second encapsulating layer comprising a layer of graphene foam.

20 . The impact shield structure as claimed in claim 18 , wherein shield structure can comprises a number of cells, including a first cell and a second cell, the first cell comprising a first structural configuration, and the second cell comprising a second structural configuration, the first and second structural configurations being different from another.

Assignees

• Bae Systems Plc

Inventors

• Black Daniel Benjamin
• Dave Kinjal Ketanbhai

Classifications

• B64G1/56 Primary

  Protection against meteoroids or space debris · CPC title

• B32B9/007

  comprising carbon, e.g. graphite, composite carbon · CPC title

• B32B3/00

  Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form · CPC title

• B64G1/54

  Protection against radiation · CPC title

• B32B2605/18

  Aircraft · CPC title