NANOSAT Electrothermal Deployment System

Patent metadata

Field	Value
Publication number	US-2016107771-A1
Application number	US-201414517532-A
Country	US
Kind code	A1
Filing date	Oct 17, 2014
Priority date	Oct 17, 2014
Publication date	Apr 21, 2016
Grant date	—

Abstract

An electrothermal deployment system may be configured for controlled release of various apparatus from their prelaunch stowage positions in small satellites. The deployment system includes a fusible line secured to a structural component of the satellite, as well as to various deployable apparatus secured to, within, or on the satellite. The deployable apparatus may include items such as solar panels and antennas. The deployment system includes an electrically resistive element such as a burn bar formed of a cylinder or tube, including a resistor pad overlying and/or incorporated within an exterior surface of the burn bar. The burn bar may be coupled to an electrical circuit configured to heat the resistor for the purpose of melting the fusible line secured in direct contact therewith, thus causing the fusible line to break to cause deployment. The fusible line is configured to remain in secure contact with the resistor until apparatus deployment.

First claim

What is claimed is:

1 . A deployment system configured for controlled release of apparatus relative to small satellites, comprising:
an electrical power source; an energy release device in communication with the power source, and including a resistive element configured to generate heat via the electrical power source; a fusible line affixed to a structural component of the satellite, the fusible line also affixed to at least one deployable apparatus secured to the satellite; wherein the fusible line is configured for contact with the energy release device, and can be melted by the heat of the resistive element, for deployment of the apparatus.

2 . The deployment system of claim 1 , wherein the energy release device is a burn bar.

3 . The deployment system of claim 1 , wherein the burn bar is a cylindrical tube containing a resistor overlying an external portion of the tube.

4 . The deployment system of claim 1 , wherein the fusible line is secured under a tensile force against the burn bar.

5 . The deployment system of claim 1 , wherein the fusible line is a monofilament.

6 . The deployment system of claim 1 , wherein a direct contact of the fusible line may be assured by maintaining the line under tension.

7 . The deployment system of claim 1 , wherein the burn bar is a solid cylinder.

8 . A burn bar adapted to melt a fusible line to cause deployment of an apparatus secured to a small satellite, the burn bar comprising:
a reusable resistive element having a substrate body secured to the satellite; an insulative material deposited on an outer surface of the substrate body; a layer of electroconductive material deposited over an external portion of the insulative material; wherein a fusible line comprises a monofilament secured directly against the electroconductive material is electrically heated to the melting point of the monofilament to cause release of an apparatus secured to the monofilament.

9 . The burn bar of claim 8 , wherein the monofilament is secured under tension against the electroconductive material.

10 . The burn bar of claim 9 , wherein the monofilament is under a tensile force of between 10 and 15 pounds.

11 . The burn bar of claim 8 , wherein the electroconductive material comprises a resistor, wherein the substrate body comprises a cylindrical tube, and wherein the resistor overlies an external portion of the tube.

12 . The burn bar of claim 8 , wherein the monofilament is formed of nylon.

13 . The burn bar of claim 8 , further comprising a tubular body.

14 . The burn bar of claim 8 , further comprising solid Chevron shaped body.

15 . A method of deploying an apparatus secured by a fusible line to a nanosat, the method comprising the steps of:
providing a resistive element having a substrate body, and securing the substrate body to the nanosat; depositing an insulative material on a peripheral surface of the substrate body; depositing a layer of electroconductive material over portions of the insulative material; and providing an electrical source within the nanosat, and connecting the electroconductive material to the electrical source.

16 . The method of claim 15 , further comprising stringing a fusible line directly over the electroconductive material, and securing the fusible line to the nanosat.

17 . The method of claim 16 , further comprising attaching the fusible line to the apparatus to be released.

18 . The method of claim 16 , further comprising applying tension to the fusible line to assure direct contact between the fusible line and the electroconductive material until time of apparatus release.

19 . The method of claim 16 , further comprising providing an electrical current from the electrical source through the fusible line sufficient to heat the fusible line to its melting point to release the apparatus.

20 . The method of claim 19 , further comprising laser etching the electroconductive material to form a resistor.

Assignees

• Boeing Co

Inventors

• Orias Geoffrey
• Worcester Michael
• Behrens John
• Drolen Bruce L

Classifications

• H05B3/0014 Primary

  Devices wherein the heating current flows through particular resistances · CPC title

• H05B3/06

  Heater elements structurally combined with coupling elements or holders · CPC title

• B64G1/66 Primary

  Arrangements or adaptations of apparatus or instruments, not otherwise provided for · CPC title

• B64G1/2229 Primary

  characterised by the deployment actuating mechanism (inflating B64G1/2227) · CPC title

• B64G1/2222

  Folding · CPC title