Launch vehicle and system and method for economically efficient launch thereof
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/40
B64G-001/00
F42B-006/00
F41A-001/04
F42B-015/10
F42B-015/12
F02K-009/95
F41B-006/00
출원번호
US-0211779
(2014-03-14)
등록번호
US-9617016
(2017-04-11)
발명자
/ 주소
Palmer, Miles R.
Brown, Jr., Glenn William
출원인 / 주소
8 Rivers Capital, LLC
대리인 / 주소
Womble Carlyle Sandridge & Rice, LLP
인용정보
피인용 횟수 :
0인용 특허 :
26
초록▼
The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, o
The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.
대표청구항▼
1. A launch vehicle adapted for high velocity delivery of a payload, the launch vehicle comprising: a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting
1. A launch vehicle adapted for high velocity delivery of a payload, the launch vehicle comprising: a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting exhaust; andone or more electrical conductors comprising sliding electrical contacts and configured to direct flow of electrical current from an external source to the electrical heater, and comprising arms positioned between the sliding electrical contacts and the electrical heater. 2. The launch vehicle according to claim 1, further comprising an expansion nozzle in fluid communication with the exiting exhaust from the electrical heater. 3. The launch vehicle according to claim 1, wherein the electrical heater is a resistive heater. 4. The launch vehicle according to claim 3, wherein the resistive heater comprises at least one electrically heated porous cylinder inside a containment vessel. 5. The launch vehicle according to claim 4, wherein the electrically heated porous cylinder comprises carbon walls. 6. The launch vehicle according to claim 5, wherein the carbon walls include a coating material selected from the group consisting of diamond, tungsten, hafnium carbide, and combinations thereof. 7. The launch vehicle according to claim 4, wherein the electrically heated porous cylinder is a transpiring tungsten-containing cylinder. 8. The launch vehicle according to claim 4, wherein the resistive heater comprises a discharge port in fluid communication with a chamber that is internal to the containment vessel and external to the electrically heated porous cylinder. 9. The launch vehicle according to claim 1, wherein the electrical heater is an arc heater. 10. The launch vehicle according to claim 9, wherein the arc heater comprises a swirl chamber within a containment vessel. 11. The launch vehicle according to claim 10, wherein the containment vessel comprises transpiration cooled walls. 12. The launch vehicle according to claim 10, wherein the swirl chamber is configured to establish a swirl stabilized electrical vortex arc. 13. The launch vehicle according to claim 10, wherein the arc heater comprises coaxial electrical terminals spaced apart by the swirl chamber. 14. The launch vehicle according to claim 1, wherein the sliding electrical contacts comprise an inner conductor at least partially surrounded by an outer rim. 15. The launch vehicle according to claim 14, wherein the outer rim is configured for transpiration cooling. 16. The launch vehicle according to claim 15, wherein the outer rim is porous. 17. The launch vehicle according to claim 16, wherein pores in the porous outer rim are at least partially filed with a cooling material. 18. The launch vehicle according to claim 17, wherein the cooling material is selected from the group consisting of hydrogen, sulfur hexafluoride, and combinations thereof. 19. The launch vehicle according to claim 14, wherein the sliding electrical contacts further comprise one or more of a magnetic rim, an ablative shield, an inner cooled rim, and an ablative rim between the inner conductor and the outer rim. 20. The launch vehicle according to claim 1, wherein the sliding electrical contacts are configured to receive the electrical current from a plasma arc. 21. The launch vehicle according to claim 1, wherein the electrical conductors comprise elongated conductive elements attached to or integral with one or both of the payload container and the propellant tank. 22. The launch vehicle according to claim 21, wherein the elongated conductive elements are configured to receive the electrical current from a plasma arc. 23. The launch vehicle according to claim 1, wherein the propellant tank comprises one or more sliding contact strips on at least a portion of an outer surface of the propellant tank. 24. The launch vehicle according to claim 23, wherein the sliding contact strips are configured to be vaporizable. 25. The launch vehicle according to claim 1, wherein the payload container comprises one or more of a human or animal passenger, a satellite, a vehicle, a commodity, and a weapon. 26. The launch vehicle according to claim 1, wherein one or all of the payload container, the propellant tank, and the electrical heater are reusable. 27. The launch vehicle according to claim 1, wherein the propellant is selected from the group consisting of hydrogen, diborane, ammonia, methane, and combinations thereof. 28. The launch vehicle according to claim 1, wherein the vehicle is configured to provide a specific impulse (Isp) of at least 500 sec. 29. The launch vehicle according to claim 1, wherein the electrical heater is configured to heat the propellant to a temperature of about 1,000 K to about 100,000 K. 30. The launch vehicle according to claim 1, wherein the exiting exhaust is selected from the group consisting of molecular hydrogen, atomic hydrogen, hydrogen plasma, and combinations thereof. 31. The launch vehicle according to claim 1, wherein the payload container comprises a heat shield. 32. The launch vehicle according to claim 31, wherein at least a portion of the heat shield is configured for transpiration cooling. 33. The launch vehicle according to claim 1, wherein the vehicle is configured to provide a thrust to weight ratio of greater than 10:1. 34. The launch vehicle according to claim 1, further comprising a propellant pump in fluid communication with the propellant tank and the electrical heater. 35. The launch vehicle according to claim 34, wherein the propellant pump is a pyrotechnically driven pump or is an electrically driven pump. 36. A launch system comprising: 1) a launch tube comprising at least one tube configured for transmission of energy therethrough2) a launch vehicle comprising:a payload container;a propellant tank containing a propellant;an electrical heater in fluid connection with the propellant tank and adapted for electrical heating of the propellant to form an exiting exhaust;a propellant pump in fluid communication with the propellant tank and the electrical heater; andone or more electrical conductors configured to direct flow of electrical current to the electrical heater; and3) an electrical energy source;wherein the launch tube is configured for propulsion of the launch vehicle therethrough. 37. The launch system according to claim 36, wherein the launch tube comprises an inner electrically conductive tube and an outer electrically conductive tube separated by a coaxial insulator tube. 38. The launch system according to claim 37, wherein the inner electrically conductive tube comprises one or more slotted tracks extending at least partially along the length thereof. 39. The launch system according to claim 38, wherein the one or more slotted tracks are configured to receive the electrical conductors of the launch vehicle. 40. The launch system according to claim 37, wherein the ratio of the radius of the outer electrically conductive tube to the radius of the inner electrically conductive tube is 2. 41. The launch system according to claim 36, wherein the launch tube is configured to limit any magnetic field formed by passage therethrough of an electrical current of about 0.2 to about 2 million amps such that the magnet field is at a strength of less than about 1.25 Tesla. 42. The launch system according to claim 36, wherein the launch tube is evacuated of ambient air. 43. The launch system according to claim 36, wherein the launch tube comprises a tube bore surrounded by an insulator tube and an electrically conductive tube, and wherein the launch tube is configured for passage of electrical current through an induced plasma arc within the launch tube bore. 44. The launch system according to claim 43, wherein the electrically conductive tube is separated from the launch tube bore along the length thereof by the insulator tube but is in electrical connection with the launch tube bore proximate a terminal end of the launch tube. 45. The launch system according to claim 44, further comprising a rearward electrically conductive element at an opposing, beginning end of the launch tube. 46. The launch system according to claim 45, wherein the system is configured for passage of electrical current forward through the electrically conductive tube and rearward through the launch tube bore and the one or more electrical conductors of the launch vehicle to the rearward electrically conductive element. 47. The launch system according to claim 43, wherein the induced plasma arc is present forward of the launch vehicle and rearward of the launch vehicle. 48. The launch system according to claim 36, wherein the launch tube comprises two electrically conductive tubes and two insulator tubes. 49. The launch system according to claim 48, wherein the launch tube comprises a tube bore surrounded by an inner insulator tube and an outer insulator tube separated by an inner electrically conductive tube and also comprises an outer electrically conductive tube exterior to the outer insulator tube. 50. The launch system according to claim 49, wherein the inner insulator tube and the inner electrically conductive tube are segmented along at least a portion of the length thereof. 51. The launch system according to claim 50, wherein the segments each include at least one switch configured to pass an electrical current from the launch bore to the inner electrically conductive tube. 52. The launch system according to claim 49, wherein the outer electrically conductive tube is in electrical connection with the launch tube bore proximate a terminal end of the launch tube. 53. The launch system according to claim 49, wherein the launch tube is configured for passage of electrical current through an induced plasma arc within the launch tube bore. 54. The launch system according to claim 53, wherein the system is configured for passage of electrical current forward through the outer electrically conductive tube and rearward through the launch tube bore and the one or more electrical conductors of the launch vehicle. 55. The launch system according to claim 54, wherein the system is configured for passage of the electrical current from the one or more electrical conductors of the launch vehicle through one or more switches positioned along the length of the inner insulator tube and into the inner electrically conductive tube. 56. The launch system according to claim 36, wherein the launch system is configured to be electroantimagnetic. 57. The launch system according to claim 36, wherein the electrical energy source comprises a battery bank. 58. The launch system according to claim 57, wherein the electrical energy source further comprises an inductor. 59. The launch system according to claim 36, wherein the electrical energy source comprises a beaming element configured to deliver a power beam. 60. The launch system according to claim 59, wherein the electrical energy source comprises a tracking element configured to track the launch vehicle in motion through the launch tube. 61. The launch system according to claim 59, wherein the launch tube comprises one or more passages along at least a portion of the length thereof, the one or more passages being configured to permit transmission of the power beam therethrough. 62. The launch system according to claim 59, wherein the power beam comprises a laser beam, a microwave beam, or a millimeter wave beam. 63. A method for launching a payload, the method comprising: providing a launch system according to claim 36; andelectrically heating the propellant in the electrical heater of the launch vehicle to form the exiting exhaust at a velocity sufficient to accelerate the payload through and out of the launch tube. 64. The method of launching a payload according to claim 63, wherein the method comprises electrically heating the propellant in the electrical heater of the launch vehicle to form an expanding gas that accelerates the launch vehicle through the launch tube to a velocity of at least about 2,000 meters per second (m/s) with an acceleration force of about 2 to about 2,000 G's while limiting a magnetic field within the tube to no more than about 2 Tesla. 65. The method of launching a payload according to claim 63, comprising providing an electrical current of about 0.2 amps to about 2 million amps through the at least one electrically conductive tube of the launch tube. 66. The method of launching a payload according to claim 65, wherein the electrical current is provided to a first electrically conductive tube, passes from the first electrically conductive tube through a first sliding contact to the electrical heater of the launch vehicle, and passes from the electrical heater though a second sliding contact to a second electrically conductive tube. 67. The method of launching a payload according to claim 66, wherein the electrical current passes from the first electrically conductive tube to the first sliding contact and passes from the second sliding contact to the second electrically conductive tube via a plasma arc. 68. The method of launching a payload according to claim 65, wherein the electrical current is provided to at least one electrically conductive tube and passes forward through the electrically conductive tube toward a terminal end of the launch tube. 69. The method of launching a payload according to claim 68, wherein the electrical current passes from the at least one electrically conductive tube and into an open bore of the launch tube through which the electrical current passes to a first electrical conductor of the launch vehicle. 70. The method of launching a payload according to claim 69, wherein the electrical current passes through the open bore of the launch tube via a plasma arc. 71. The method of launching a payload according to claim 69, wherein the electrical current passes from the first electrical conductor of the launch vehicle to the electrical heater and passes away from the launch vehicle through a second electrical conductor of the launch vehicle. 72. The method of launching a payload according to claim 71, wherein the electrical current passing away from the launch vehicle moves rearward through the open bore of the launch tube to a rearward electrically conductive element. 73. The method of launching a payload according to claim 65, wherein the electrical current is provided to a first electrically conductive tube and passes forward through the first electrically conductive tube toward a terminal end of the launch tube. 74. The method of launching a payload according to claim 73, wherein the electrical current passes from the first electrically conductive tube and into an open bore of the launch tube through which the electrical current passes to a first electrical conductor of the launch vehicle via a plasma arc. 75. The method of launching a payload according to claim 74, wherein the electrical current passes from the first electrical conductor of the launch vehicle to the electrical heater and passes away from the launch vehicle through a second electrical conductor of the launch vehicle. 76. The method of launching a payload according to claim 75, wherein the electrical current passing away from the launch vehicle passes through one or more switches into a second electrically conductive tube and passes rearward therethrough. 77. The method of launching a payload according to claim 63, wherein the electrical energy source comprises a beaming element configured to deliver a power beam, and wherein the method comprising directing the power beam from the beaming element to the electrical heater of the launch vehicle through one or more passages in the launch tube. 78. The method of launching a payload according to claim 77, comprising tracking the power beam to the position of the launch vehicle as the launch vehicle accelerates through the launch tube such that the power beam is delivered to the launch vehicle at a plurality of positions along the length of the launch tube. 79. The method of launching a payload according to claim 77, wherein the power beam is a laser beam, a microwave beam, or a millimeter beam. 80. The method of launching a payload according to claim 63, comprising directing an energy beam to the atmosphere forward to the payload container after exiting the launch tube such that the energy beam heats the atmosphere forward to the payload container. 81. The method of launching a payload according to claim 80, wherein the atmosphere is explosively heated with a laser beam.
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