[특허]Method of enhancing microthruster performance

Purdue Research Foundation

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특허 상세정보

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Method of enhancing microthruster performance

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B63H-011/00
미국특허분류(USC)	060/204; 060/203.1
출원번호	US-0466357 (2009-05-14)
등록번호	US-8613188 (2013-12-24)
발명자 / 주소	Stein, William Benjamin Alexeenko, Alina A. Hrbud, Ivana Hitt, Darren L.
출원인 / 주소	Purdue Research Foundation
대리인 / 주소	Gallagher, Douglas G.
인용정보	피인용 횟수 : 2 인용 특허 : 20

초록
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Coaxial micronozzles are disclosed. Embodiments of the present disclosure include coaxial micronozzles with center-body geometries to exploit pressure thrust. Some embodiemnts include a generally cylindrical centerbody extending through at least a portion of the flowpath and extending into the exit so as to form a generally annular throat, wherein the microthruster is adapted and configured such that the Reynolds number through the throat is less than about one thousand. Some embodiments show a potential threefold increase in specific impulse under vacuu...

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1. A microthruster for a spacecraft, comprising: a supply of pressurized gas;a pressure vessel of the microthruster having an entrance for receiving the supply of gas and defining an exit for releasing the gas to ambient conditions, the pressure vessel defining an internal flowpath between the entrance and exit, anda generally cylindrical centerbody having an aft face extending through at least a portion of the flowpath and extending into the exit so as to form a generally annular throat, the generally cylindrical centerbody defining a central axis extending along the length of the generally cylindrical centerbody, the aft face of the generally cylindrical centerbody is coplanar with the exterior portion of the nozzle adjacent to and surrounding the exit;wherein the Reynolds number (Re) through the throat is less than about one thousand when the gas is released from the pressure vessel and travels through the throat to the exit, wherein the Reynolds number (Re) is Re=mnng⁢Vs⁢Dthuref, m being the neutral particle mass of the gas, nng being the neutral gas number density of the gas, Vx being the velocity component of the gas parallel to the central axis, Dth being the throat diameter, and uref being reference viscosity of the gas at 300K. 2. The microthruster of claim 1 wherein the Reynolds number is less than about one hundred. 3. The microthruster of claim 1 wherein the ambient pressure condition is a vacuum. 4. The microthruster of claim 1 wherein the aft face of the centerbody is blunt. 5. The microthruster of claim 4 wherein the aft face of the centerbody is flat. 6. The microthruster of claim 4 wherein the flowpath of the pressure vessel converges proximate to the exit and some of the exiting gas impinges on the aft face. 7. The microthruster of claim 4 wherein the blunt face is rounded. 8. The microthruster of claim 4, wherein the flowpath defined by the microthruster at the exit is directed inward toward the central axis to impinge on itself. 9. The microthruster of claim 4, wherein the flowpath defined by the microthruster at the exit creates a high pressure region aft of the exit. 10. The microthruster of claim 1 wherein the aft face of the centerbody is generally conical. 11. The microthruster of claim 10 wherein the included angle of the cone is greater than about thirty degrees from the centerline of the centerbody to the aft edge of the centerbody. 12. The microthruster of claim 10 wherein the included angle of the cone is greater than about sixty degrees from the centerline of the centerbody to the aft edge of the centerbody. 13. The microthruster of claim 1 wherein said centerbody has an aft face proximate to the throat and the aft face of the centerbody is biconical. 14. The microthruster of claim 1 which further comprises means for adding energy to the pressurized gas. 15. The microthruster of claim 14 wherein the energy addition means is the electrostatic type. 16. The microthruster of claim 14 wherein the energy addition means is the electromagnetic type. 17. The microthruster of claim 14 wherein the energy addition means is the electrothermal type. 18. The microthruster of claim 14 wherein the energy addition means is the chemical type. 19. The microthruster of claim 1 wherein the walls of the annular throat are adapted and configured to direct some of the exiting gas toward the centerline of the throat. 20. The microthruster of claim 1 wherein the gas is a cold gas and the microthruster does not include means for adding energy to the pressurized gas. 21. The microthruster of claim 1 wherein said centerbody has an outer diameter and said centerbody includes a rounded edge joining the outer diameter to the aft face. 22. The microthruster of claim 1 wherein said centerbody has an outer diameter, and said centerbody includes a chamfered edge joining the outer diameter to the aft face. 23. The microthruster of claim 1 wherein the flowpath of the pressure vessel converges in the direction of flow of the gas toward the exit. 24. The microthruster of claim 1, wherein the flowpath defined by the microthruster at the exit creates a stagnation zone aft of the centerbody. 25. The micronozzle of claim 1, wherein the thrust produced by the micronozzle is approximately one (1) mN. 26. A microthruster for a spacecraft, comprising: a supply of pressurized gas;a pressure vessel of the microthruster having an entrance for receiving the supply of gas and defining an exit for releasing the gas to ambient conditions, the pressure vessel defining an internal flowpath between the entrance and exit, anda centerbody having a first section extending through at least a portion of the flowpath, the first section having a conical outer surface such that the centerbody diameter increases in the direction of flow toward the exit, said centerbody having a second section extending from the first section to the exit; the second section having a conical outer surface such that the centerbody diameter decreases in the direction of flow toward the exit, the second section and the exit forming an annulus therebetween; wherein the centerbody includes an aft face is coplanar with the exterior portion of the nozzle adjacent to and surrounding the exit and the aft face is blunt. 27. The microthruster of claim 26 wherein the internal flowpath of the pressure vessel converges in the direction of flow of the gas toward the exit. 28. The microthruster of claim 27 wherein the walls of the internal flowpath facing the outer surface of the second section are generally parallel. 29. The microthruster of claim 27 wherein the walls of the internal flowpath facing the outer surface of the second section are generally divergent. 30. The microthruster of claim 27 wherein the centerbody and pressure vessel and adapted and configured such that the flow of pressurized gas is choked at the intersection of the first section and the second section. 31. The microthruster of claim 26 wherein the Reynolds number is less than about one hundred. 32. The microthruster of claim 26 wherein the ambient pressure condition is a vacuum. 33. The microthruster of claim 26 which further comprises means for adding energy to the pressurized gas. 34. The microthruster of claim 33 wherein the energy addition means is the electrostatic type. 35. The microthruster of claim 33 wherein the energy addition means is the electromagnetic type. 36. The microthruster of claim 33 wherein the energy addition means is the electrothermal type. 37. The microthruster of claim 33 wherein the energy addition means is the chemical type. 38. The microthruster of claim 26 wherein the annulus is conically converging in the direction of flow and directs some of the exiting gas toward the centerline of the throat. 39. The microthruster of claim 26 wherein the wherein the flowpath of the pressure vessel converges proximate to the exit and some of the exiting gas impinges on the aft face. 40. The microthruster of claim 26 wherein the blunt face is rounded. 41. The microthruster of claim 26 wherein the gas is a cold gas and the microthruster does not include means for adding energy to the pressurized gas. 42. The microthruster of claim 26, wherein the centerbody defines a central axis extending from the first section to the second section, and wherein the flowpath defined by the microthruster at the exit is directed inward toward the central axis to impinge on itself. 43. The microthruster of claim 26, wherein the flowpath defined by the microthruster at the exit creates a high pressure region aft of the exit. 44. The microthruster of claim 26, wherein the flowpath defined by the microthruster at the exit creates a stagnation zone aft of the centerbody. 45. The micronozzle of claim 26, wherein the thrust produced by the micronozzle is approximately one (1) mN. 46. A method for producing thrust with a microthruster in space, comprising: moving gas from a pressurized supply chamber of the microthruster, through an internal flowpath, to an exit, the internal flowpath being defined by a generally cylindrical cenerbody having an aft face extending into the exit and forming an annular throat, wherein the aft face of the generally cylindrical centerbody is coplanar with the exterior portion of the nozzle adjacent to and surrounding the exit; andreleasing the gas from the exit to ambient conditions;wherein the Reynolds number through the throat during said moving and said releasing is less than about one thousand. 47. The method of claim 46, comprising: positioning the microthruster in space.

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Method of enhancing microthruster performance

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Method of enhancing microthruster performance

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