[특허]Thrust apparatuses, systems, and methods

The Boeing Company

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특허 상세정보

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Thrust apparatuses, systems, and methods

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/00 B64G-001/40 B64G-001/42 F03H-001/00
출원번호	US-0533934 (2014-11-05)
등록번호	US-9834324 (2017-12-05)
발명자 / 주소	Stickelmaier, John F. Perkins, Julie M. Kreiner, Kurt B. Nguyen, Philip D.
출원인 / 주소	The Boeing Company
대리인 / 주소	Kunzler, PC
인용정보	피인용 횟수 : 0 인용 특허 : 4

초록
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Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the a...

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1. A thrust system for a vehicle, comprising: at least three electrical power controllers;at least four electrical switches each configured to receive electrical power from two of the at least three electrical power controllers and at least one of the at least four electrical switches comprising an output electrically connected with an input of another of the at least four electrical switches to provide electrical power to the other of the at least four electrical switches; andat least three thrusters each configured to receive electrical power from at least one of the at least four electrical switches;wherein the at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters. 2. The system of claim 1, wherein the switches are operable to allow electrical power from the at least three electrical power controllers to be concurrently supplied to the at least three thrusters, with each electrical power controller supplying power to a respective one of the at least three thrusters. 3. The system of claim 1, wherein one of the at least three electrical power controllers is a redundant power controller, and wherein in a first mode a first of the at least three electrical power controllers supplies electrical power to a first of the at least three thrusters, a second of the at least three electrical power controllers supplies electrical power to a second of the at least three thrusters, and the redundant power controller supplies no electrical power to the first and second thrusters, and wherein in a second mode one of the first and second electrical power controllers supplies no electrical power to the first and second thrusters, respectively, and the redundant power control supplies electrical power to one of the first and second electrical power controllers. 4. The system of claim 1, wherein: each electrical power controller comprises a first power output and a second power output;each electrical switch comprises a first power input, a second power input, and at least one of a first power output and a second power output;the first power output of a first of the electrical power controllers is electrically coupled to the first power input of a first of the electrical switches, and the second power output of the first of the electrical power controllers is electrically coupled to the first power input of a second of the electrical switches;the first power output of a second of the electrical power controllers is electrically coupled to the first power input of a third of the electrical switches, and the second power output of the second of the electrical power controllers is electrically coupled to the second power input of a fourth of the electrical switches; andthe first power output of a third of the electrical power controllers is electrically coupled to the second power input of the third of the electrical switches, and the second power output of the third of the electrical power controllers is electrically coupled to the second power input of the second of the electrical switches. 5. The system of claim 4, wherein: the first power output of the second of the electrical switches is electrically coupled to the first power input of the fourth of the electrical switches;the first power output of the third of the electrical switches is electrically coupled to the second power input of the first of the electrical switches;the first power output of the first of the electrical switches is electrically coupled to a first of the thrusters, and the second power output of the first of the electrical switches is electrically coupled to a second of the thrusters; andthe first power output of the fourth of the electrical switches is electrically coupled to a third of the thrusters, and the second power output of the fourth of the electrical switches is electrically coupled to a fourth of the thrusters. 6. The system of claim 5, wherein: the first of the electrical switches is actuatable to either (i) route electrical power from the first power input of the first of the electrical switches to the first power output of the first of the electrical switches and route electrical power from the second power input of the first of the electrical switches to the second power output of the first of the electrical switches, or (ii) route electrical power from the first power input of the first of the electrical switches to the second power output of the first of the electrical switches and route electrical power from the second power input of the first of the electrical switches to the first power output of the first of the electrical switches;the second of the electrical switches is actuatable to either (i) route electrical power from the first power input of the second of the electrical switches to the first power output of the second of the electrical switches, or (ii) route electrical power from the second power input of the second of the electrical switches to the first power output of the second of the electrical switches;the third of the electrical switches is actuatable to either (i) route electrical power from the first power input of the third of the electrical switches to the first power output of the third of the electrical switches, or (ii) route electrical power from the second power input of the third of the electrical switches to the first power output of the third of the electrical switches; andthe fourth of the electrical switches is actuatable to either (i) route electrical power from the first power input of the fourth of the electrical switches to the first power output of the fourth of the electrical switches and route electrical power from the second power input of the fourth of the electrical switches to the second power output of the fourth of the electrical switches, or (ii) route electrical power from the first power input of the fourth of the electrical switches to the second power output of the fourth of the electrical switches and route electrical power from the second power input of the fourth of the electrical switches to the first power output of the fourth of the electrical switches. 7. The system of claim 5, wherein the switches are configured such that the first power outputs of the first, second, and third electrical power controllers supply power only to the first and second thrusters, and the second power outputs of the first, second, and third electrical power controllers supply power only to the third and fourth thrusters. 8. The system of claim 1, wherein each of the three thrusters is an ion propulsion thruster. 9. The system of claim 1, wherein each of the three thrusters is enabled for maximum thrust output. 10. The system of claim 1, wherein the at least four electrical switches are configured such that each of the at least three electrical power controllers supplies electrical power to only one of the at least three thrusters at a time. 11. A thrust system for a vehicle, comprising: at least three electrical power controllers;at least four electrical switches each communicable in power receiving communication with two of the electrical power controllers and at least one of the at least four electrical switches comprising an output electrically connected with an input of another of the at least four electrical switches to provide electrical power to the other of the at least four electrical switches;at least four thrusters each communicable in power receiving communication with one of the electrical switches; anda system controller operably coupled to the electrical power controllers and four thrusters to control electrical power supply from the electrical power controllers to the thrusters, wherein in a first mode the system controller operates the electrical switches and thrusters to nonconcurrently supply power to each of the four thrusters from less than three electrical power controllers, and in a second mode the system controller operates the electrical switches and thrusters to concurrently supply power to each of three of the four thrusters from a respective one of the three electrical power controllers. 12. The system of claim 11, wherein in a third mode the system controller operates the electrical switches and thrusters to nonconcurrently supply power to each of the four thrusters from less than three electrical power controllers, wherein one of the electrical power controllers supplying power to the thrusters in the third mode does not supply power to the thrusters in the first mode. 13. The system of claim 11, wherein the vehicle comprises a satellite, the system further comprising the satellite.

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Thrust apparatuses, systems, and methods

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Thrust apparatuses, systems, and methods

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