Separation system and burn wire release mechanism for tethered spacecraft

Patent metadata

Field	Value
Publication number	US-10266284-B2
Application number	US-201414229905-A
Country	US
Kind code	B2
Filing date	Mar 29, 2014
Priority date	Sep 29, 2011
Publication date	Apr 23, 2019
Grant date	Apr 23, 2019

Abstract

A tethered spacecraft has a first endmass and a second endmass with a telescoping stacer spring and a tether arranged between the endmasses. The spring is coiled around a center rod and initially contained within a housing, the spring being biased to push the first endmass away from the second endmass. The spring housing is affixed to the first endmass, a first end of the spring being affixed to the spring housing, and tether are affixed to spring at one end and to the second endmass at the other end. A pretensioned loop holds the endmasses abuttingly together, and a burnwire release mechanism cuts the loop to deploy the spring. Upon deployment, the spring extends to its full length to form a cylindrical boom, and the endmasses continue to move outward along the spring centerline until stopped by the tether.

First claim

The invention claimed is:

1. A tethered spacecraft, comprising:
a first endmass;
a second endmass;
a telescoping spring coiled around a center rod and initially contained within a housing, the spring being biased to push the first endmass away from the second endmass; and
a tether wound on a spool,
the housing being affixed to the first endmass, a first end of the spring being affixed to the spring housing, a first end of the tether being affixed to a second end of the spring, and the tether having a second end affixed to the second endmass.

2. The tethered spacecraft according to claim 1 , wherein upon deployment, the telescoping spring is released and extends to form a rigid cylindrical boom, the telescoping spring pushes the endmasses apart, and the tether unwinds from the spool as the endmasses continue to move apart.

3. The tethered spacecraft according to claim 1 , wherein the spring housing extends along a centerline of the spacecraft and fits within an interior surface of the spool in a stowed position.

4. The tethered spacecraft according to claim 1 , wherein the tether spool is in direct contact with the second end of the spring and in direct contact with the tether, the tether spool providing attachment between the spring and tether.

5. The tethered spacecraft according to claim 4 , wherein the tether, the spring, and the tether spool comprise electrically conductive materials, forming a continuous electrical path between the first end mass and the second end mass.

6. The tethered spacecraft according to claim 1 , wherein the tether comprises an electrically conductive metal and the telescoping spring comprises an electrically conductive metal, with a conductive connection between the tether and the spring, forming a continuous electrical path from the first endmass to the second endmass.

7. The tethered spacecraft according to claim 1 , further comprising:
a pretensioned loop extending between a tensioning system in the first endmass and a burn wire release system in the second endmass, the pretensioned loop configured to hold the first endmass in position abutting the second endmass until the burn wire release system cuts the pretensioned loop.

8. The spacecraft according to claim 7 , wherein the tensioning system configured to pretension the loop to hold the first endmass in position abutting the second endmass before release.

9. The spacecraft according to claim 7 , wherein the burn wire release system includes at least one burn wire release mechanism, each mechanism having a resistively heated burn wire positioned in contact with the pretensioned loop, wherein in operation, a current flows through the burn wire in either a primary or secondary mechanism, heating the burn wire sufficiently to cut the pretensioned loop material.

10. The spacecraft according to claim 9 , wherein each end mass has a bulkhead with an opening therethrough, and wherein the pretensioned loop extends through the openings in each bulkhead, and wherein the burn wire release mechanisms are positioned on the bulkhead of one of the end masses.

11. The spacecraft according to claim 7 , wherein the burn wire release system includes at least two burn wire release mechanisms.

12. The spacecraft according to claim 7 , wherein the burn wire comprises nichrome and the pretensioned loop material comprises a polymer.

13. The spacecraft according to claim 7 , wherein the pretensioned material comprises a spun liquid crystal polymer.

14. The tethered spacecraft according to claim 1 , further comprising: a central hollow rod affixed to the second endmass along a centerline of the spacecraft, the telescoping spring being wound around the central hollow rod.

15. The tethered spacecraft according to claim 1 , wherein the tether comprises braided plurality of strands of para-aramid synthetic fiber and electrically conductive metalized aromatic polyamide fiber.

Assignees

• Coffey Shannon
• Carroll Joseph A
• Oppenheimer Paul
• Schlater Jordan R
• Galysh Ivan
• Levin Eugene
• Hogan Curt
• Thurn Adam
• Us Navy

Inventors

• Coffey Shannon
• Carroll Joseph A
• Oppenheimer Paul
• Schlater Jordan R
• Galysh Ivan
• Levin Eugene
• Hogan Curt
• Thurn Adam

Classifications

• Y10T83/293

  Of tool · CPC title

• B64G1/648 Primary

  Tethers · CPC title

• B64G1/363

  using sun sensors · CPC title

• B64G1/44

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

• B64G1/366

  using magnetometers · CPC title