Thruster device responsive to solar radiation

• US 6,421,998 B1
• Filed: 06/13/2000
• Issued: 07/23/2002
• Est. Priority Date: 06/13/2000
• Status: Expired due to Term

• Current Assignee: Aerojet Rocketdyne Of De, Inc. (L3Harris Technologies, Inc.)
• Original Assignee: The Boeing Co.
• Inventors: Frye, Patrick E., Shoji, James M., Carroll, Joseph P.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US09/592,724
• Time in Patent Office: 770 Days
• Field of Search: 602/031, 165/118, 415/72, 415/73
• US Class Current: 60/203.1
• CPC Class Codes: B64G 1/401 Liquid propellant rocket engines Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: B64G 1/427 Thermal power storage
• CPC Class Codes: B64G 1/446 Thermal solar power generation
• CPC Class Codes: F02K 9/42 using liquid or gaseous propellants F02K9/72 takes precedence
• CPC Class Codes: F03H 99/00 Subject matter not provided for in other groups of this subclass
• CPC Class Codes: F05D 2230/11 by electrochemical methods
• CPC Class Codes: F05D 2250/25 helical
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2300/13 Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
• CPC Class Codes: F24S 20/20 Solar heat collectors for receiving concentrated solar energy, e.g. receivers for solar power plants
• CPC Class Codes: Y02E 10/40 Solar thermal energy, e.g. solar towers
• CPC Class Codes: Y10T 29/49346 Rocket or jet device making
• CPC Class Codes: Y10T 29/49355 Solar energy device making
• CPC Class Codes: Y10T 29/49995 Shaping one-piece blank by removing material

Abstract

A thruster device and associated methods are provided. The thruster device comprises a frustoconical inner layer and a frustoconical outer layer that surrounds the inner layer such that the inner and outer layers cooperate to define a spiral flow passage therebetween. An outlet, such as a nozzle, is attached to an exit end of the thruster device such that the outlet is in fluid communication with the spiral flow passage. In one embodiment, the thruster device includes an end flow cap that is also attached to the exit end and establishes the fluid communication between the spiral flow passage and the outlet. The end flow cap includes at least one channel for directing the propellant from the spiral flow passage to the outlet. The design of the thruster device allows the frustoconical inner and outer layers to be assembled without galling or damaging the spiral flow passage.

Claims

1. A thruster device responsive to solar radiation to heat a properllant, comprising:

a frustoconical inner layer having inner and outer surfaces and opposed ends;

a frustoconical outer layer surrounding said inner layer, said outer layer having inner and outer surfaces and opposed ends such that the outer surface of said inner layer and the inner surface of said outer layer cooperate to define a spiral flow passage, at least one of the inner and outer layers being operable to absorb solar radiation and transfer at least a portion of the solar radiation to the propellant; and

a thrust-producing outlet attached to one of said opposed ends of said inner and outer layers and in fluid communication with said spiral flow passage, said spiral flow passage operable to receive and direct the propellant therethrough to said outlet in order to produce thrust.

2. A thruster device according to claim 1, wherein the outer surface of said inner layer defines a spiral groove that at least partially defines said spiral flow passage.

3. A thruster device according to claim 1, wherein the inner surface of said outer layer defines a spiral groove that at least partially defines said flow passage.

4. A thruster device according to claim 1, wherein said inner and outer layers are comprised of at least one of rhenium, hafnium carbide, tantalum carbide, and zirconium carbide.

5. A thruster device according to claim 1, further comprising an end flow cap defining at least one radial channel that is in fluid communication with both the flow passage and said outlet for directing propellant to said outlet.

6. A thruster device according to claim 1, wherein said outlet is a nozzle.

7. A thruster device responsive to solar radiation to heat a propellant, comprising:

a frustoconical inner layer having inner and outer surfaces and opposed ends;

a frustoconical outer layer surrounding said inner layer, said outer layer having inner and outer surfaces and opposed ends, at least one of the inner and outer layers being operable to absorb solar radiation and transfer at least a portion of the solar radiation to the propellant;

means for defining a spiral flow passage disposed between said inner and outer layers; and

a thrust-producing outlet attached to one end of said opposed ends of said inner and outer layers and in fluid communication with the spiral flow passage for directing propellant theretrough to said outlet in order to produce thrust.

8. A thruster device according to claim 7, wherein the outer surface of said inner layer at least partially comprises the means for defining the spiral flow passage.

9. A thruster device according to claim 7, wherein the inner surface of said outer layer at least partially comprises the means for defining the spiral flow passage.

10. A thruster device according to claim 7, wherein said inner and outer layers are comprised of at least one of rhenium and hafnium carbide.

11. A thruster device according to claim 7, further comprising an end flow cap defining at least one radial channel that is in fluid communication with both the spiral flow passage and said outlet for directing propellant to said outlet.

12. A thruster device according to claim 7, wherein said outlet is a nozzle.