Enhanced compound steering law for general low thrust mission
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-003/00
B64G-001/10
B64G-001/24
출원번호
US-0658634
(2012-10-23)
등록번호
US-8930048
(2015-01-06)
발명자
/ 주소
Batla, Fawwad M.
Ho, Yiu-hung M.
출원인 / 주소
The Boeing Company
대리인 / 주소
Vista IP Law Group LLP
인용정보
피인용 횟수 :
2인용 특허 :
7
초록▼
The disclosed method involves calculating, with at least one processor, a desired orbit for the spacecraft. The method further involves calculating a velocity change required to achieve an orbit eccentricity, a velocity change required to achieve a semi-major axis, and a velocity change required to
The disclosed method involves calculating, with at least one processor, a desired orbit for the spacecraft. The method further involves calculating a velocity change required to achieve an orbit eccentricity, a velocity change required to achieve a semi-major axis, and a velocity change required to achieve an orbit inclination; all of which correspond to the desired orbit for the spacecraft. Also, the method involves calculating the direction of the vector sum of the velocity change required to achieve the orbit eccentricity, the velocity change required to achieve the semi-major axis, and the velocity change required to achieve the orbit inclination. Further, the method involves activating at least one propulsion device of the spacecraft in the direction of the vector sum in order to change the current orbit of the spacecraft to the desired orbit for the spacecraft, thereby changing the orbit eccentricity, the semi-major axis, and the orbit inclination simultaneously.
대표청구항▼
1. A method for application of a compound steering law for general low thrust mission for a spacecraft, the method comprising: calculating, with at least one processor, a desired orbit for the spacecraft;calculating, with the at least one processor, a velocity change required to achieve an orbit ecc
1. A method for application of a compound steering law for general low thrust mission for a spacecraft, the method comprising: calculating, with at least one processor, a desired orbit for the spacecraft;calculating, with the at least one processor, a velocity change required to achieve an orbit eccentricity that corresponds to the desired orbit for the spacecraft; calculating, with the at least one processor, a velocity change required to achieve a semi-major axis that corresponds to the desired orbit for the spacecraft; calculating, with the at least one processor, a velocity change required to achieve an orbit inclination that corresponds to the desired orbit for the spacecraft; calculating, with the at least one processor, a direction of a vector sum of the velocity change required to achieve the orbit eccentricity, the velocity change required to achieve the semi-major axis, and the velocity change required to achieve the orbit inclination; andactivating at least one propulsion device of the spacecraft in the direction of the vector sum in order to change a current orbit of the spacecraft to the desired orbit for the spacecraft, thereby changing the orbit eccentricity, the semi-major axis, and the orbit inclination simultaneously. 2. The method of claim 1, wherein the spacecraft is one of a satellite, a pseudo satellite, a rocket, a launch vehicle, and a space plane. 3. The method of claim 1, wherein the at least one propulsion device is at least one of a chemical propulsion system and an electrical propulsion system (EPS), wherein the chemical propulsion system comprises at least one of a liquid propulsion system (LPS), a solid propulsion system, and a gaseous propulsion system. 4. The method of claim 3, wherein the EPS is a xenon-ion propulsion system (XIPS). 5. The method of claim 3, wherein the LPS employs at least one of a monopropellant and a bipropellant. 6. The method of claim 1, wherein the method is performed during a transfer orbit mission for the spacecraft. 7. The method of claim 1, wherein a transition orbit mission changes from at least one of a lower Earth orbit (LEO), a medium Earth orbit (MEO), geosynchronous Earth orbit (GEO), a highly elliptical orbit (HEO), an inter-planetary orbit, and a lunar orbit mission to at least one of a target LEO, MEO, GEO, HEO, inter-planetary orbit, and lunar orbit for the spacecraft. 8. The method of claim 1, wherein a transition orbit mission changes an initial geo-synchronous eccentric orbit of the spacecraft to a target orbit for the spacecraft. 9. The method of claim 1, wherein a transition orbit mission changes an initial sub-synchronous eccentric orbit of the spacecraft to a target orbit for the spacecraft. 10. The method of claim 1, wherein a transition orbit mission changes an initial super-synchronous eccentric orbit of the spacecraft to a target orbit for the spacecraft. 11. The method of claim 1, wherein the method is performed during an on-station mission for the spacecraft. 12. The method of claim 1, wherein the method is performed with a fixed transfer orbit duration (TOD) in order to maximize payload capacity. 13. The method of claim 1, wherein the method is performed with a variable TOD in order to minimize the TOD for a fixed payload capacity. 14. A method for application of a compound steering law for general low thrust mission for a spacecraft, the method comprising: calculating, with at least one processor, a desired orbit for the spacecraft;calculating, with the at least one processor, a velocity change required to achieve an orbit eccentricity that corresponds to the desired orbit for the spacecraft; calculating, with the at least one processor, a velocity change required to achieve a semi-major axis that corresponds to the desired orbit for the spacecraft; calculating, with the at least one processor, a velocity change required to achieve an orbit inclination that corresponds to the desired orbit for the spacecraft; calculating, with the at least one processor, a direction of a vector sum of the velocity change required to achieve the orbit eccentricity, the velocity change required to achieve the semi-major axis, and the velocity change required to achieve the orbit inclination,wherein the at least one processor uses at least one weighting factor for the calculating of the direction of the vector sum;activating at least one propulsion device of the spacecraft in the direction of the vector sum in order to change a current orbit of the spacecraft to the desired orbit for the spacecraft, thereby changing the orbit eccentricity, the semi-major axis, and the orbit inclination simultaneously. 15. The method of claim 14, wherein the at least one propulsion device is at least one of a chemical propulsion system and an electrical propulsion system (EPS), wherein the chemical propulsion system comprises at least one of a liquid propulsion system (LPS), a solid propulsion system, and a gaseous propulsion system. 16. The method of claim 15, wherein the EPS is a XIPS. 17. The method of claim 15, wherein the LPS employs at least one of a monopropellant and a bipropellant. 18. The method of claim 14, wherein the method is performed during a transfer orbit mission for the spacecraft. 19. The method of claim 14, wherein the method is performed during an on-station mission for the spacecraft. 20. A system for application of a compound steering law for general low thrust mission for a spacecraft, the system comprising: at least one processor configured for calculating a desired orbit for the spacecraft,wherein the at least one processor is further configured for calculating a velocity change required to achieve an orbit eccentricity that corresponds to the desired orbit for the spacecraft, a velocity change required to achieve a semi-major axis that corresponds to the desired orbit for the spacecraft, and a velocity change required to achieve an orbit inclination that corresponds to the desired orbit for the spacecraft;wherein the at least one processor is further configured for calculating a direction of a vector sum of the velocity change required to achieve the orbit eccentricity, the velocity change required to achieve the semi-major axis, and the velocity change required to achieve the orbit inclination; andat least one propulsion device on the spacecraft configured for activating in the direction of the vector sum in order to change a current orbit of the spacecraft to the desired orbit for the spacecraft, thereby changing the orbit eccentricity, the semi-major axis, and the orbit inclination simultaneously.
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이 특허에 인용된 특허 (7)
Koppel Christophe,FRX, Method and a system for putting a space vehicle into orbit, using thrusters of high specific impulse.
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