IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0341159
(2014-07-25)
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등록번호 |
US-9783323
(2017-10-10)
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발명자
/ 주소 |
- Nicholas, Andrew C.
- Creamer, Nelson
- Finne, Theodore T.
- Herrero, Federico A.
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출원인 / 주소 |
- The United States of America, as represented by the Secretary of the Navy
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대리인 / 주소 |
U.S. Naval Research Laboratory
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인용정보 |
피인용 횟수 :
0 인용 특허 :
3 |
초록
▼
A method and system is described for determining attitude for a satellite. A two-axis ram sensor head measures neutral winds and provides a density of the neutral winds. A three-axis magnetometer measures a geomagnetic field. A measurement interface module calculates attitude information, which incl
A method and system is described for determining attitude for a satellite. A two-axis ram sensor head measures neutral winds and provides a density of the neutral winds. A three-axis magnetometer measures a geomagnetic field. A measurement interface module calculates attitude information, which includes three-axis attitude knowledge of a satellite relative to a local-vertical local-horizontal orbit frame, based on the combined ram measurements and magnetic field measurements, and provides the attitude information to a satellite that comprises the attitude sensor system.
대표청구항
▼
1. An attitude sensor system, comprising: a ram sensor device configured to measure neutral winds;a magnetometer device configured to measure a geomagnetic field; anda measurement interface module configured to: determine a horizontal wind direction based on measurements from the ram sensor device a
1. An attitude sensor system, comprising: a ram sensor device configured to measure neutral winds;a magnetometer device configured to measure a geomagnetic field; anda measurement interface module configured to: determine a horizontal wind direction based on measurements from the ram sensor device and magnetometer device,determine attitude information based on the horizontal wind direction, andprovide attitude information to a satellite comprising the attitude sensor system, wherein the satellite is configured to adjust an attitude of the satellite based on the attitude information. 2. The attitude sensor system of claim 1, wherein the ram sensor device is a two-axis ram sensor head. 3. The attitude sensor system of claim 1, further comprising: a ram sensor electronics module configured to power and operate the ram sensor device. 4. The attitude sensor system of claim 1, wherein the magnetometer device is a three-axis magnetometer. 5. The attitude sensor system of claim 1, wherein the measurement interface module is further configured to: process the measurements from the magnetometer device;calibrate the magnetometer device; andprovide a magnetic field vector. 6. The attitude sensor system of claim 1, further comprising: a sensor head configured to receive thermosphere molecules;a charged ion filter, coupled to the sensor head, configured to deflect ions in the thermosphere molecules out of the flow field, thereby filtering neutral molecules in the thermosphere molecules;a thermionic cathode chamber, coupled to the charged ion filter, configured to ionize the neutral molecules;a free drift vacuum chamber, coupled to the thermionic cathode chamber, configured to accelerate the ionized molecules generated by the thermionic cathode chamber through a charged grid and onto a focal plane array; anda detector, coupled to the free drift vacuum chamber, configured to register a location and intensity of a flow field for two-axis angle and density determination. 7. The attitude sensor system of claim 1, wherein the measurement interface module is configured to provide continuous attitude knowledge relative to a local orbit frame by combining the measurements from the ram sensor device and magnetometer device. 8. The attitude sensor system of claim 1, wherein the attitude sensor system is further configured to provide a real-time estimate of a local crosswind director, a neutral density, a bias of the magnetometer device, a scale factor, and an internal misalignment. 9. The attitude sensor system of claim 1, wherein the ram sensor device is further configured to: measure a ram direction comprising a spacecraft velocity direction and a local wind direction. 10. The attitude sensor system of claim 1, wherein the measurement interface module is further configured to: generate a magnetic field vector based on the geomagnetic field measured by the magnetometer device. 11. The attitude sensor system of claim 1, wherein the ram sensor device and the measurement interface module are configured based on a predetermined mission orbital altitude and solar cycle period. 12. An attitude sensor system, comprising: a ram sensor device configured to measure neutral winds;a magnetometer device configured to measure a geomagnetic field; anda measurement interface module configured to: combine measurements from the ram sensor device and magnetometer device to calculate attitude information,provide a horizontal wind direction from the measurements from the ram sensor device and magnetometer device based on a comparison of an angle between a measured ram vector and a measured field vector and an angle between a predicted ram vector and a predicted field vector from a known orbit location of a satellite and a geomagnetic field model, andprovide attitude information to the satellite, wherein the satellite is configured to adjust an attitude of the satellite based on the attitude information. 13. The attitude sensor system of claim 1, wherein the attitude information comprises three-axis attitude knowledge of the satellite relative to a local-vertical local-horizontal orbit frame. 14. The attitude sensor system of claim 1, wherein the measurement interface module is configured to provide the attitude information to the satellite that comprises the attitude sensor system. 15. The attitude sensor system of claim 1, wherein the ram sensor device is configured to provide a density of the neutral winds. 16. A method for determining attitude, the method comprising: measuring neutral winds with a ram sensor device;measuring a geomagnetic field with a magnetometer device;determining a horizontal wind direction measurements from the ram sensor device and magnetometer device;determining attitude information based on the horizontal wind direction; andproviding attitude information to a satellite, wherein the satellite adjusts an attitude of the satellite based on the attitude information. 17. The method of claim 16, further comprising: providing a density of the neutral winds with the ram sensor device. 18. The method of claim 16, wherein the attitude information comprises three-axis attitude knowledge of the satellite relative to a local-vertical local-horizontal orbit frame.
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