Mesh reflector satellite antennas with on-orbit extruded or printed support structure

Patent metadata

Field	Value
Publication number	US-11196174-B2
Application number	US-202017020501-A
Country	US
Kind code	B2
Filing date	Sep 14, 2020
Priority date	Jun 20, 2018
Publication date	Dec 7, 2021
Grant date	Dec 7, 2021

Abstract

Deployable reflector antenna includes a fabrication hub in which at least one additive fabrication unit disposed. The additive fabrication unit is configured to form at least one rigid structural element of a reflector antenna system. In a stowed condition, an RF reflector material comprised of a flexible webbing is disposed in a stowed configuration proximate to the fabrication hub. A fabrication control system controls the additive fabrication unit so as to form the at least one rigid structural element. The RF reflector material is arranged to transition during the additive fabrication process from the stowed configuration in which the flexible webbing material is furled compactly at the fabrication hub, to a deployed configuration in which the flexible webbing material is unfurled.

First claim

We claim:

1. A method for deploying a reflector antenna system, comprising:
transporting the reflector antenna system to a deployment location;
at said deployment location,
using an additive fabrication process to form at least one rigid structural element of a reflector antenna;
attaching a portion of an RF reflector material formed of a flexible web to a portion of the at least one rigid structural element;
causing deployment of the flexible web from a stowed configuration to an extended configuration by using the additive fabrication process to increase a length of the at least one rigid structural element to which the flexible web has been attached; and
upon completion of the deployment, facilitating support of the flexible web in a predetermined shape using the at least one-rigid structural element.

2. The method according to claim 1 , wherein the RF reflector material is a metallic woven mesh.

3. The method according to claim 1 , wherein the RF reflector material is secured to the at least one rigid structural element after the rigid structural element is at least partially formed.

4. The method according to claim 1 , wherein the additive fabrication process is a 3D printing process in which material is sequentially deposited in layers to form the at least one rigid structural element.

5. The method according to claim 1 , wherein the additive fabrication process is at least one of an extrusion process and a pultrusion process in which a material comprising the at least one rigid structural element is urged through a die.

6. The method according to claim 1 , wherein the additive fabrication process is performed at a central hub.

7. The method according to claim 6 , wherein a plurality of the rigid structural elements are formed so as to extend in radial directions originating at the central hub.

8. The method according to claim 7 , wherein a peripheral edge of the flexible web is secured to a tip end of each of the rigid structural elements distal from the central hub.

9. The method according to claim 8 , wherein the flexible web is deployed by causing the tip ends to extend in radial directions as a result of the additive fabrication process.

10. The method according to claim 8 , wherein the peripheral edge is secured to the tip end of each rigid structural element indirectly through an offset member which extends from the tip end in at least one direction transverse to the rigid structural element.

11. The method according to claim 7 , wherein the flexible web is secured to each of the plurality of rigid structural elements at predetermined intervals as the additive fabrication process progresses.

12. The method according to claim 1 , wherein the additive fabrication process further comprises forming the at least one rigid structural element to extend along a non-linear path extending from a perimeter hub.

13. The method according to claim 12 , further comprising continuing the additive fabrication process until the non-linear path results in a distal end of the at least one rigid structural element returning to the perimeter hub.

14. The method according to claim 12 , further comprising selecting the non-linear path to be a curved path forming a hoop that begins and ends at the perimeter hub.

15. The method according to claim 12 , further comprising securing the flexible web to the hoop at predetermined intervals along the non-linear path as the additive fabrication process progresses.

16. The method according to claim 1 , wherein the additive fabrication process comprises forming a plurality of the rigid structural elements to extend linearly from a perimeter hub.

17. The method according to claim 16 , wherein the additive fabrication process is controlled to selectively form the plurality of rigid structural elements to have different predetermined lengths.

18. The method according to claim 16 , wherein at least one point along a peripheral edge of the flexible web is secured to the peripheral hub.

19. The method according to claim 1 , wherein the deployment location is an space-based orbital location.

20. The method according to claim 1 , further comprising supporting with the at least one rigid structural element a network of cords which define the predetermined shape of the flexible web.

Assignees

• Eagle Tech Llc

Inventors

• Taylor Robert M
• Henderson Philip J

Classifications

• B64G1/2225

  Rolling or unfurling (B64G1/2227 takes precedence) · CPC title

• H01Q15/168

  Mesh reflectors mounted on a non-collapsible frame · CPC title

• H01Q15/165

  composed of a plurality of rigid panels (collapsible H01Q15/161) · CPC title

• H01Q15/163

  inflatable · CPC title

• H01Q15/161

  Collapsible reflectors · CPC title