Thrust nozzle system and method for the orbit and attitude control of a geostationary satellite
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/40
B64G-001/26
B64G-001/10
출원번호
US-0553801
(2014-11-25)
등록번호
US-9878807
(2018-01-30)
우선권정보
FR-13 02782 (2013-11-29)
발명자
/ 주소
Amalric, Joel
출원인 / 주소
Thales
대리인 / 주소
Baker Hostetler LLP
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A thrust nozzle system is provided for a satellite designed to be stabilized in autorotation over a geostationary orbit, the satellite comprising three reference axes X, Y and Z, the Y axis representing the North/South axis and the Z axis corresponding to an Earth pointing direction. The thrust nozz
A thrust nozzle system is provided for a satellite designed to be stabilized in autorotation over a geostationary orbit, the satellite comprising three reference axes X, Y and Z, the Y axis representing the North/South axis and the Z axis corresponding to an Earth pointing direction. The thrust nozzle system comprises a first set of thrust nozzles configured for maintaining the satellite in station, the first set comprising an even number of thrust nozzles using electrical propulsion, with a pre-adjusted orientation, the even number being equal to at least 4, the thrust nozzles being oriented along three spatial components, and having, taken in pairs, different signs of X and Y components.
대표청구항▼
1. A thrust nozzle system for a satellite designed to be stabilized in autorotation over a geostationary orbit, said satellite comprising three reference axes X, Y and Z, the Y axis representing a North/South axis and the Z axis corresponding to an Earth pointing direction, comprising a first set of
1. A thrust nozzle system for a satellite designed to be stabilized in autorotation over a geostationary orbit, said satellite comprising three reference axes X, Y and Z, the Y axis representing a North/South axis and the Z axis corresponding to an Earth pointing direction, comprising a first set of thrust nozzles configured for maintaining the satellite in station, the first set comprising an even number of thrust nozzles using electrical propulsion, with a pre-adjusted orientation, said even number being equal to at least 4, said first set of thrust nozzles comprising a pair of thrust nozzles on either side of the plane XZ, said thrust nozzles being oriented along three spatial components, the two thrust nozzles of each pair having different signs of X components and same signs of Y components, two thrust nozzles of two different pairs having opposite Y signs. 2. The thrust nozzle system according to claim 1, wherein the satellite has a centre of gravity and the position of the fixed thrust nozzles is chosen such that the thrust nozzles pass through a neighbourhood of the centre of gravity of the satellite while conserving a limited torque with respect to the capacity of the flywheels of the satellite. 3. The thrust nozzle system according to claim 2, wherein the position of the thrust nozzles is furthermore chosen in such a manner as to take into account the displacement of the centre of gravity of the satellite over the lifetime of the satellite. 4. The thrust nozzle system according to claim 1, characterized in that it comprises a second set of thrust nozzles comprising at least two thrusters using electrical propulsion, said second set of thrust nozzles being configured for implementing at least the setting into station of the satellite, the thrust nozzles of the second set being oriented substantially along a same satellite axis. 5. The thrust nozzle system according to claim 1, wherein each thrust nozzle of the first set forms a chosen angle of inclination θ with respect to the Y axis. 6. The thrust nozzle system according to claim 5, wherein the thrust nozzles of the first set have angles of inclination θ that are substantially identical with respect to the Y axis. 7. The thrust nozzle system according to claim 1, wherein the thrust nozzles of the first set have different angles of inclination θ with respect to the Y axis. 8. The thrust nozzle system according to claim 1, wherein the satellite is defined by a body comprising a North face, a South Face, a West Face and an East Face according to the direction of said three axis X, Y and Z, said first set of thrust nozzles comprising a thrust nozzle arranged on the edge bounded by the North face and East face of the body of the satellite. 9. The thrust nozzle system according to claim 1, wherein the satellite is defined by a body comprising a North face, a South Face, a West Face and an East Face according to the direction of said three axis X, Y and Z, said first set of thrust nozzles comprising a thrust nozzle arranged on the edge bounded by the South face and East face of the body of the satellite. 10. The thrust nozzle system according to claim 1, wherein the satellite is defined by a body comprising a North face, a South Face, a West Face and an East Face according to the direction of said three axis X, Y and Z, said first set of thrust nozzles comprising a thrust nozzle arranged on the North face in the neighbourhood of the edge bounded by the North face and West face. 11. The thrust nozzle system according to claim 1, wherein the satellite is defined by a body comprising a North face, a South Face, a West Face and an East Face according to the direction of said three axis X, Y and Z, said first set of thrust nozzles comprising a thrust nozzle arranged on the South face in the neighbourhood of the edge bounded by the South face and East face of the body of the satellite. 12. The thrust nozzle system according to claim 1, wherein the satellite is defined by a body comprising a North face, a South Face, a West Face and an East Face according to the direction of said three axis X, Y and Z, said first set of thrust nozzles comprising a thrust nozzle arranged on the East face of the body of the satellite in the neighbourhood of the edge bounded by the South face and East face of the body of the satellite. 13. The thrust nozzle system according to claim 1, wherein the satellite is defined by a body comprising a North face, a South Face, a West Face and an East Face according to the direction of said three axis X, Y and Z, said first set of thrust nozzles comprising a thrust nozzle arranged on the West face of the body of the satellite in the neighbourhood of the edge bounded by the South face and West face of the body of the satellite. 14. The thrust nozzle system according to claim 1, wherein the thrust nozzles of the first set are non-coplanar. 15. The thrust nozzle system according to claim 1, wherein at least one of the thrust nozzles of the first set forms a pivot angle σ a with respect to the YZ plane. 16. The thrust nozzle system according to claim 1, wherein the thrust nozzles of the first set have respective different pivot angles σ a with respect to the YZ plane. 17. The thrust nozzle system according to claim 15, wherein the satellite is defined by a body, said first set of thrust nozzles comprising at least one thrust nozzle arranged in the neighbourhood of an external corner of the body of the satellite. 18. The thrust nozzle system according to claim 1, wherein the satellite comprises flywheels, and in that the first set of thrust nozzles is used to perform a control of an angular momentum vector, in the case of unsaturation of the momentum wheels. 19. A method for the orbit and attitude control of a geostationary satellite, comprising a thrust nozzle system for a satellite designed to be stabilized in autorotation over a geostationary orbit, said satellite comprising three reference axes X, Y and Z, the Y axis representing the North/South axis and the Z axis corresponding to an Earth pointing direction, the thrust nozzle system comprising a first set of thrust nozzles configured for maintaining the satellite in station, the first set comprising an even number of thrust nozzles using electrical propulsion, with a pre-adjusted orientation, said even number being equal to at least 4, said first set of thrust nozzles comprising a pair of thrust nozzles on either side of the plane XZ, said thrust nozzles being oriented along three spatial components, the two thrust nozzles of each pair having different signs of X components and same signs of Y components, two thrust nozzles of two different pairs having opposite Y signs, wherein the method further comprising ignition of the thrust nozzles of the first set independently of one another while the satellite is maintained in station. 20. The method according to claim 19, wherein maintaining the satellite in station is carried out over a given number of control days, and in that the method comprises, for each control day, the placing of one thrust nozzle from the first set of thrust nozzles at a given orbital position, by applying a chosen duration of thrust in such a manner that the net correction of the orbital elements at the end of the day is equal to a target correction vector. 21. The method according to claim 19, further comprising activation of the thrust nozzles of the second set of thrust nozzles in one at least of the following phases from amongst the phases of life of the satellite: repositioning of the satellite, the setting into stable orbit at the end of life of the satellite. 22. The method according to claim 21, further comprising simultaneous ignition of the thrust nozzles of the second set of thrust nozzles.
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