초록 ▼

A method and system for application of a compound steering law for efficient low thrust transfer orbit trajectory for a spacecraft are disclosed. The method involves calculating, with at least one processor, a desired orbit for the spacecraft. The method further involves calculating a velocity chang

A method and system for application of a compound steering law for efficient low thrust transfer orbit trajectory for a spacecraft are disclosed. The 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 and a velocity change required to achieve a semi-major axis, both 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 and the velocity change required to achieve the semi-major axis. Further, the method involves firing at least one thruster 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 and the semi-major axis simultaneously.

대표청구항 ▼

1. A method for application of a compound steering law for efficient low thrust transition orbit trajectory 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 t

1. A method for application of a compound steering law for efficient low thrust transition orbit trajectory 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 direction of a vector sum of the velocity change required to achieve the orbit eccentricity and the velocity change required to achieve the semi-major axis; andfiring at least one thruster 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 and the semi-major axis 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 2, wherein the EPS is a xenon-ion propulsion system (XIPS). 4. The method of claim 2, wherein the LPS employs at least one of a monopropellant and a bipropellant. 5. The method of claim 1, wherein the spacecraft employs at least one of a liquid propulsion system (LPS) and an electrical propulsion system (EPS). 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 the 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 the transition orbit mission changes an initial geo-synchronous eccentric orbit of the spacecraft to a target geo-synchronous circular orbit for the spacecraft. 9. The method of claim 1, wherein the transition orbit mission changes an initial sub-synchronous eccentric orbit of the spacecraft to a target geo-synchronous circular orbit for the spacecraft. 10. The method of claim 1, wherein the transition orbit mission changes an initial super-synchronous eccentric orbit of the spacecraft to a target geo-synchronous circular 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 efficient low thrust transition orbit trajectory 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 direction of a vector sum of the velocity change required to achieve the orbit eccentricity and the velocity change required to achieve the semi-major axis;calculating, with the at least one processor, a factor w that is a function of an absolute value of the velocity change required to achieve the semi-major axis divided by the velocity change required to achieve the orbit eccentricity;calculating, with the at least one processor, a factor x that is a function of an orbit true anomaly angle of the current orbit for the spacecraft; andfiring at least one thruster of the spacecraft in the direction of the vector sum times the factor x in order to change a current orbit of the spacecraft to the desired orbit for the spacecraft, thereby changing the orbit eccentricity and the semi-major axis simultaneously. 15. The method of claim 14, wherein the spacecraft employs at least one of a LPS and an EPS. 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 efficient low thrust transition orbit trajectory 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, and a velocity change required to achieve a semi-major axis 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 and the velocity change required to achieve the semi-major axis; andat least one thruster on the spacecraft is configured for firing 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 and the semi-major axis simultaneously.