Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic Radar
The problem of initial orbit determination (IOD) for Low Earth Orbit (LEO) objects using bistatic radar too-short arc (TSA) observations is addressed. For TSA observations, the traditional IOD methods suffer low accuracy. For LEO objects with stable attitude, the high order kinematic parameters can...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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IEEE
2022-01-01
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| Series: | IEEE Access |
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| Online Access: | https://ieeexplore.ieee.org/document/9797707/ |
| _version_ | 1828190325089239040 |
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| author | Jinye Qu Defeng Chen Huawei Cao Tuo Fu Shuo Zhang |
| author_facet | Jinye Qu Defeng Chen Huawei Cao Tuo Fu Shuo Zhang |
| author_sort | Jinye Qu |
| collection | DOAJ |
| description | The problem of initial orbit determination (IOD) for Low Earth Orbit (LEO) objects using bistatic radar too-short arc (TSA) observations is addressed. For TSA observations, the traditional IOD methods suffer low accuracy. For LEO objects with stable attitude, the high order kinematic parameters can be obtained from the time derivatives of the radar echo phase. In this paper, an analytical IOD method is presented using bistatic radar TSA observations, which contain the position measurements (bistatic range, azimuth angle, and elevation angle) and the high order kinematic measurements (bistatic velocity, acceleration, and jerk). As the undetermined target state variables constitute a complex system of equations that can only be solved iteratively, an auxiliary coordinate system based on the bistatic geometry is defined to help reduce the equations to one unary quartic equation. Further, the closed-form expressions of the orbital state are derived. The performance of the proposed method is evaluated using linearization approximations. Numerical simulations are carried out for several typical LEO observation scenarios to demonstrate the performance of the proposed method. |
| first_indexed | 2024-04-12T08:20:25Z |
| format | Article |
| id | doaj.art-e8642ee5182f4c54adcc8253e619b656 |
| institution | Directory Open Access Journal |
| issn | 2169-3536 |
| language | English |
| last_indexed | 2024-04-12T08:20:25Z |
| publishDate | 2022-01-01 |
| publisher | IEEE |
| record_format | Article |
| series | IEEE Access |
| spelling | doaj.art-e8642ee5182f4c54adcc8253e619b6562022-12-22T03:40:36ZengIEEEIEEE Access2169-35362022-01-0110767667677910.1109/ACCESS.2022.31816939797707Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic RadarJinye Qu0https://orcid.org/0000-0003-2821-1590Defeng Chen1https://orcid.org/0000-0002-0138-2149Huawei Cao2https://orcid.org/0000-0003-2192-7115Tuo Fu3https://orcid.org/0000-0001-8826-3048Shuo Zhang4https://orcid.org/0000-0002-9015-549XSchool of Information and Electronics, Beijing Institute of Technology, Beijing, ChinaSchool of Information and Electronics, Beijing Institute of Technology, Beijing, ChinaSchool of Information and Electronics, Beijing Institute of Technology, Beijing, ChinaSchool of Information and Electronics, Beijing Institute of Technology, Beijing, ChinaSchool of Information and Electronics, Beijing Institute of Technology, Beijing, ChinaThe problem of initial orbit determination (IOD) for Low Earth Orbit (LEO) objects using bistatic radar too-short arc (TSA) observations is addressed. For TSA observations, the traditional IOD methods suffer low accuracy. For LEO objects with stable attitude, the high order kinematic parameters can be obtained from the time derivatives of the radar echo phase. In this paper, an analytical IOD method is presented using bistatic radar TSA observations, which contain the position measurements (bistatic range, azimuth angle, and elevation angle) and the high order kinematic measurements (bistatic velocity, acceleration, and jerk). As the undetermined target state variables constitute a complex system of equations that can only be solved iteratively, an auxiliary coordinate system based on the bistatic geometry is defined to help reduce the equations to one unary quartic equation. Further, the closed-form expressions of the orbital state are derived. The performance of the proposed method is evaluated using linearization approximations. Numerical simulations are carried out for several typical LEO observation scenarios to demonstrate the performance of the proposed method.https://ieeexplore.ieee.org/document/9797707/Initial orbit determinationtoo-short arcbistatic radarroot-mean-square error |
| spellingShingle | Jinye Qu Defeng Chen Huawei Cao Tuo Fu Shuo Zhang Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic Radar IEEE Access Initial orbit determination too-short arc bistatic radar root-mean-square error |
| title | Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic Radar |
| title_full | Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic Radar |
| title_fullStr | Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic Radar |
| title_full_unstemmed | Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic Radar |
| title_short | Initial Orbit Determination Method for Low Earth Orbit Objects Using Too-Short Arc Based on Bistatic Radar |
| title_sort | initial orbit determination method for low earth orbit objects using too short arc based on bistatic radar |
| topic | Initial orbit determination too-short arc bistatic radar root-mean-square error |
| url | https://ieeexplore.ieee.org/document/9797707/ |
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