Satellite with integral thrusters

Patent metadata

Field	Value
Publication number	US-10220966-B2
Application number	US-201615091008-A
Country	US
Kind code	B2
Filing date	Apr 5, 2016
Priority date	Apr 5, 2016
Publication date	Mar 5, 2019
Grant date	Mar 5, 2019

Abstract

A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

First claim

What is claimed is:

1. A satellite comprising:
a structural frame; and
thrusters within the frame;
wherein the thrusters include thrusters in corners of the structural frame, located in cavities within the frame that are integrally formed during manufacture of the frame; and
wherein the frame is a cubic frame.

2. The satellite of claim 1 , wherein the structural frame is additively manufactured.

3. The satellite of claim 2 , wherein the thrusters are at least in part also additively manufactured, as part of the same additive manufacturing process as the structural frame.

4. The satellite of claim 1 , wherein the thrusters each include propellant.

5. The satellite of claim 4 , wherein the propellant is an electrically-operated propellant.

6. The satellite of claim 5 , wherein each of the thrusters includes electrodes operatively coupled to the electrically-operated propellant, to cause combustion of the electrically-operated propellant.

7. The satellite of claim 6 , wherein the thrusters each include a feed mechanism that feeds the propellant toward the electrodes, as the propellant is consumed.

8. The satellite of claim 7 , wherein the feed mechanism includes a resilient device that biases movement of the propellant toward the electrodes.

9. The satellite of claim 4 , wherein the thrusters each include nozzle inserts that are operatively coupled to the propellant such that pressurized gases produced by combustion of the propellant exit the satellite through the nozzle inserts.

10. The satellite of claim 9 , wherein at least some of the nozzle inserts are configured such that the pressurized gases passing through the at least some of the nozzle inserts exit the at least some of the nozzle inserts parallel to a longitudinal axis of the thruster.

11. The satellite of claim 9 , wherein at least some of the nozzle inserts are configured such that the pressurized gases passing through the at least some of the nozzle inserts exit the at least some of the nozzle inserts at one or more nonzero angles away from a longitudinal axis of the thruster.

12. The satellite of claim 1 , wherein the thrusters in the corners of the structural frame include at least four thrusters in the corners of the structural frame.

13. The satellite of claim 1 , wherein for each of at least some of the thrusters the structural frame surrounds and defines a combustion chamber.

14. The satellite of claim 1 , wherein the satellite is less than or equal to 15 cm in length, width, and height.

15. The satellite of claim 1 , wherein the satellite has a mass of less than or equal to 2 kg.

16. The satellite of claim 1 , wherein the frame defines a recess for receiving and enclosing a payload.

17. The satellite of claim 16 , further comprising the payload, with the payload in the recess, with the payload in the recess surrounded by the thrusters within the frame.

18. A method of making a satellite according to claim 1 , the method comprising:
additively manufacturing the frame of the satellite; and
additively manufacturing thrusters integrated with the frame.

19. The method of claim 18 , wherein the additively manufacturing of the frame and the additively manufacturing of at least part of the thrusters are parts of a single additive manufacturing process, building up the thrusters integrated with the frame while the frame is being additively manufactured.

20. The method of claim 18 , wherein the additive manufacturing of the frame includes producing chambers within the frame for the thrusters.

Assignees

• Raytheon Co

Inventors

• Koehler Frederick B
• Danforth Jeremy C
• Lyman Ward D
• Langhenry Mark T
• Summers Matt H
• Pontius Paul E
• Pape Brian M
• Stallings Jared D
• Villarreal James K
• Villarreal Thomas

Classifications

• B64G1/403 Primary

  Solid propellant rocket engines · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• B64G1/10

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• F02K99/00

  Subject matter not provided for in other groups of this subclass · CPC title

• F05D2230/31

  Layer deposition · CPC title