System and method for manually safing and deorbiting a geostationary spacecraft in an absence of a spacecraft processor
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/10
B64G-001/24
출원번호
US-0898421
(2013-05-20)
등록번호
US-9346564
(2016-05-24)
발명자
/ 주소
Rump, Kurt M.
Noyola, Richard A.
Ardito, Steven E.
Carreno, Adriel O.
출원인 / 주소
The Boeing Company
대리인 / 주소
McDonnell Boehnen Hulbert & Berghoff LLP
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A system and method for controlling de-orbit of a spacecraft is presented. Embedded command modules are commanded directly from a central command and telemetry module. Latch valves, thruster valves, and solar wing drive of the spacecraft are operated in response to inputs to the embedded command mod
A system and method for controlling de-orbit of a spacecraft is presented. Embedded command modules are commanded directly from a central command and telemetry module. Latch valves, thruster valves, and solar wing drive of the spacecraft are operated in response to inputs to the embedded command modules. The spacecraft is maneuvered to a safe disposal orbit in response to commands from the central command and telemetry unit.
대표청구항▼
1. A method, comprising: commanding a plurality of embedded command modules of a spacecraft directly from a central command and telemetry unit;operating latch valves, one or more thrusters, and a solar wing drive of the spacecraft in response to inputs to the plurality of embedded command modules; a
1. A method, comprising: commanding a plurality of embedded command modules of a spacecraft directly from a central command and telemetry unit;operating latch valves, one or more thrusters, and a solar wing drive of the spacecraft in response to inputs to the plurality of embedded command modules; andmaneuvering the spacecraft to a safe disposal orbit in response to commands from the central command and telemetry unit, comprising: commanding the solar wing drive to move one or more solar wings to a peak power orientation;orienting the spacecraft to an orbit-raising attitude to orient a spacecraft x-axis or a spacecraft spin axis substantially orthogonal to a sunline; andfiring one or more sun pointed thrusters of the one or more thrusters to raise an orbit of the spacecraft. 2. The method of claim 1, wherein commanding the plurality of embedded command modules comprises commanding the embedded command modules from a ground-based control center through the central command and telemetry unit. 3. The method of claim 1, further comprising determining that a primary spacecraft processor, a secondary spacecraft processor or a combination thereof has failed. 4. The method of claim 1, further comprising pulsing one or more axial roll thrusters of the one or more thrusters to place the spacecraft in a stable spin about a major axis of inertia. 5. The method of claim 1, further comprising commanding solar wing drive steps to move the one or more solar wings of the spacecraft to a peak power orientation. 6. The method of claim 1, wherein orienting the spacecraft comprises: receiving one or more commands; andafter receiving the one or more commands, reorienting the spacecraft spin axis to an orbit raising attitude with the spacecraft x-axis substantially orthogonal to the sunline, using solar wing current peaks to determine a timing of pulses of the one or more thrusters. 7. The method of claim 1, further comprising using solar wing current peaks to determine when one or more axial thrusters of the one or more thrusters is pointed at a sun or opposite the sun. 8. The method of claim 7, further comprising: determining whether the spacecraft is proximal to a local dawn;after determining that the spacecraft is proximal to the local dawn, determining a first time when a solar wing current peak of a solar wing of the one or more solar wings that is aligned in an axial thrust direction to raise an orbit of the spacecraft; andpulsing the one or more axial thrusters in an axial thrust direction at a time based on the first time. 9. The method of claim 7, further comprising: determining whether the spacecraft is proximal to a local dusk;after determining that the spacecraft is proximal to a local dusk, determining a second time of a solar wing current peak of a solar wing of the one or more solar wings that is aligned in second axial thrust direction opposite an axial thrust direction to raise an orbit of the spacecraft; andpulsing the one or more axial thrusters in the second axial thrust direction at a time based on the second time. 10. The method of claim 7, further comprising: commanding one or more first thrust pulses during a first portion of an orbit when the sunline is about parallel to an orbit velocity vector to achieve a first delta-v in a first orientation substantially toward the sun;commanding one or more second thrust pulses during a second portion of the orbit when the sunline is about parallel to the orbit velocity vector to achieve a second delta-v in a second orientation about opposite to the sun; andincreasing an orbit semi-major axis in relation to an initial spacecraft de-orbit during the first portion or the second portion of the orbit. 11. A system, comprising: one or more solar wings;one or more thrusters;a plurality of embedded command modules operable to be commanded directly from a central command and telemetry unit, wherein the plurality of embedded command modules are configured to: command a solar wing drive to move the one or more solar wings to a peak power orientation;orient the spacecraft to an orbit-raising attitude to orient a spacecraft x-axis or a spacecraft spin axis substantially orthogonal to a sunline; andfire one or more sun pointed thrusters of the one or more thrusters to raise an orbit of the spacecraft; anda plurality of spacecraft devices responsive to inputs from the embedded command modules, the plurality of spacecraft devices comprising one or more latch valves, one or more thruster valves, and the solar wing drive. 12. The system of claim 11, wherein the plurality of embedded command modules are operable to be commanded from a ground-based control center through the central command and telemetry unit. 13. The system of claim 11, wherein the central command and telemetry unit is further operable to determine that a primary spacecraft processor, a secondary spacecraft processor or a combination thereof has a failure and directly command the plurality of embedded command modules via a ground-based control center in response to the failure. 14. The system of claim 11, wherein one or more axial roll thrusters of the one or more thrusters is operable to be pulsed by a command of the plurality of embedded command modules to place the spacecraft in a stable spin about a major axis of inertia. 15. The system of claim 11, wherein the embedded command modules are operable to orient the spacecraft by at least: receiving one or more commands; andafter receiving the one or more commands, reorienting the spacecraft spin axis to an orbit raising attitude with the spacecraft x-axis substantially orthogonal to the sunline, using solar wing current peaks to determine a timing of pulses of the one or more thrusters. 16. The system of claim 11, wherein solar wing current peaks are utilized to determine a timing of reorientation that thruster pulses of the spacecraft used to achieve the orbit-raising attitude. 17. The system of claim 11, further comprising one or more axial thrusters of the one or more thrusters configured to operate based on solar wing current peaks when the axial thrusters are pointed at a sun or opposite the sun. 18. The system of claim 17, wherein the central command and telemetry unit is further operable to: determine whether the spacecraft is proximal to a local dawn;after determining that the spacecraft is proximal to the local dawn, determine a first time when a solar wing current peak of a solar wing of the one or more solar wings that is aligned in a first axial thrust direction to raise an orbit of the spacecraft; andpulse the one or more axial thrusters in the first axial thrust direction at a time based on the first time. 19. The system of claim 17, wherein the central command and telemetry unit is further operable to: determine whether the spacecraft is proximal to a local dusk;after determining that the spacecraft is proximal to a local dusk, determining a second time when a solar wing current peak of a solar wing of the one or more solar wings that is aligned in a second axial thrust direction opposite an axial thrust direction to raise an orbit of the spacecraft; andpulse the one or more axial thrusters in the second axial thrust direction at a time based on the second time. 20. The system of claim 17, wherein the central command and telemetry unit is further operable to: command one or more first thrust pulses during a first portion of an orbit when the sunline is about parallel to an orbit velocity vector to achieve a first delta-v in a first orientation substantially toward the sun,command one or more second thrust pulses during a second portion of the orbit when the sunline is about parallel to the orbit velocity vector to achieve a second delta-v in a second orientation about opposite to the sun, andincrease an orbit semi-major axis in relation to an initial spacecraft de-orbit during either the first portion or the second portion of the orbit.
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이 특허에 인용된 특허 (7)
Zwang Michael B., Embedded command module with matrix switch drive capability.
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