ORBIT COVARIANCE, ESTIMATION AND ANALYSIS TOOL

• US 20120046863A1
• Filed: 08/12/2011
• Published: 02/23/2012
• Est. Priority Date: 08/12/2010
• Status: Abandoned Application

• Current Assignee: Navy The USA As Represented By The Secretary of The
• Original Assignee: The Government of The US As Represented By The Secretary of The Navy
• Inventors: Middour, Jay W., Hope, Alan Scott, Fein, Jacques, Brown, Bryan, Binning, Patrick, Melvin, Peter, Soyka, Mark, Davis, Mark
• Application Number:
  US13/208,368
• Publication Number:
  US 20120046863A1
• Time in Patent Office: Days
• US Class Current: 701/531
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 3/00 Observing or tracking cosmonautic vehicles
• CPC Class Codes: G01S 19/393 Trajectory determination or predictive tracking, e.g. Kalman filtering

Abstract

Improved orbit/covariance estimation and analysis (OCEAN) system and method are presented utilizing ground station observations collected from satellites passing overhead to estimate the positions, velocities, and other parameters of multiple satellites using weighted least squares (WLS) batch and/or Kalman filter smoothing (KFS) estimation algorithms to estimate each parameter, with or without a priori knowledge of the errors involved with each observed parameter.

Claims

1. A system for estimating the position, velocity and other parameters of a plurality of orbiting bodies, comprising:

at least one processor configured to compute an estimated position, velocity, and other parameters of each orbiting body of the plurality of orbiting bodies, simultaneously, at least partially by a Kalman filter smoothing process using at least one of electromagnetic and optical emissions of the orbital bodies and ground stations.

2. The system of claim 1, wherein the at least one processor is configured to compute the estimated position, velocity, and other parameters of each orbital body of the plurality of orbital bodies, simultaneously, at least partially by a weighted least squares batch estimation process using the at least one of electromagnetic and optical emissions of the orbital bodies and ground stations.

3. The system of claim 2, wherein the at least one processor is configured to compute the estimated position, velocity, and other parameters of each orbital body of the plurality of orbital bodies, simultaneously, using a de-weighting scheme of the weighted least squares batch estimation process to solve for a single pass of data.

4. The system of claim 2, wherein the at least one processor is configured to allow a user to select one or both of the Weighted Least Squares batch estimation process and the Kalman filter smoothing process to compute the estimated position, velocity, and other parameters of each orbital body of the plurality of orbital bodies.

5. The system of claim 1, comprising force models to account for different forces acting on the orbiting bodies, the force models including models for space vehicle thrusting, the Earth oblateness change rate, solid Earth tides, ocean tides, indirect oblateness due to lunar gravity, general relativity accelerations, and the MSIS atmosphere for aerodynamic drag;

and

wherein the at least one processor is configured to compute the estimated position, velocity, and other parameters of each orbital body of the plurality of orbital bodies, simultaneously, at least partially according to at least one of the force models.

6. The system of claim 1, wherein the at least one processor is configured to compute estimated anomalistic accelerations for the orbital bodies.

7. The system of claim 1, wherein the at least one processor is configured to read an a-priori initial condition file to obtain an initial guess of each orbital body'"'"'s position, velocity and other parameters.

8. The system of claim 1, comprising at least one user-specified model for at least one of drag, solar radiation, albedo and spacecraft attitude;

and

wherein the at least one processor is configured to compute the estimated position, velocity, and other parameters of each orbital body of the plurality of orbital bodies, simultaneously, at least partially according to the at least one user-specified model.

9. The system of claim 1, wherein the at least one processor is configured to compute at least one tracking measurement error.

10. The system of claim 1, comprising a data simulator component implemented using the at least one processor, the data simulator component operative to simulate tracking measurements to model position, navigation and timing determination, and prediction performance.

11. A computer-implemented method for estimating the position, velocity and other parameters of a plurality of orbiting bodies, the method comprising:

using at least one processor, computing an estimated position, velocity, and other parameters of each orbiting body of the plurality of orbiting bodies, simultaneously, at least partially by a Kalman filter smoothing process using at least one of electromagnetic and optical emissions of the orbital bodies and ground stations.

12. The method of claim 11, comprising:

using the at least one processor, computing the estimated position, velocity, and other parameters of each orbital body of the plurality of orbital bodies, simultaneously, at least partially by a weighted least squares batch estimation process using the at least one of electromagnetic and optical emissions of the orbital bodies and ground stations.

13. The method of claim 12, comprising:

using the at least one processor, computing the estimated position, velocity, and other parameters of each orbiting body of the plurality of orbiting bodies, simultaneously, using a de-weighting scheme of the weighted least squares batch estimation process to solve for a single pass of data.

14. The method of claim 12, comprising allowing a user to select one or both of the weighted least squares batch estimation process and the Kalman filter smoothing process for computing the estimated position, velocity, and other parameters of each orbiting body of the plurality of orbital bodies.

15. The method of claim 11, comprising:

storing force models to account for different forces acting on the orbiting bodies, the force models including models for space vehicle thrusting, the Earth oblateness change rate, solid Earth tides, ocean tides, indirect oblateness due to lunar gravity, general relativity accelerations, and the MSIS atmosphere for aerodynamic drag; and

using the at least one processor, computing the estimated position, velocity, and other parameters of each orbital body of the plurality of orbital bodies, simultaneously, at least partially according to at least one of the force models.

16. The method of claim 11, comprising:

using the at least one processor, computing estimated anomalistic accelerations for the orbiting bodies.

17. The method of claim 11, comprising:

using the at least one processor, reading an a-priori initial condition file to obtain an initial guess of each orbiting body'"'"'s position, velocity and other parameters.

18. The method of claim 11, comprising:

storing at least one user-specified model for at least one of drag, solar radiation, albedo and spacecraft attitude; and

using the at least one processor, computing the estimated position, velocity, and other parameters of each orbiting body of the plurality of orbital bodies, simultaneously, at least partially according to the at least one user-specified model.

19. The method of claim 11, comprising:

using the at least one processor, computing at least one tracking measurement error.

20. The method of claim 11, comprising:

using the at least one processor, simulating tracking measurements to model position, navigation and timing determination, and prediction performance.

21. A system to estimate and refine the knowledge of spatial and temporal states of the components of a satellite system space and ground segments for the purposes of providing a terrestrial navigation accuracy set of information, comprising:

at least one processor configured to compute an estimated position, velocity, and other parameters of each orbiting body of the plurality of orbiting bodies by at least one of a Kalman filter smoothing process and a weighted least squares batch estimation process using at least one of electromagnetic and optical emissions of the orbiting bodies and ground stations;

the at least one processor configured to receive a plurality of carrier phase-based Iridium pseudorange measurements created by at least one ground receiver and reformatted by an operations center; and

the at least one processor configured to process the received carrier phase based Iridium measurements to create an updated precision position and timing estimate for a plurality of Iridium satellites, the precision position and timing estimate for the plurality of Iridium satellites including an updated estimate for the position and timing of the Iridium satellites and a high precision prediction of where the satellites will be, the precision position and timing estimate being suitable for creating orbital and timing parameters for uplinking to the Iridium constellation for re-broadcasting to Iridium augmentation service users.