Real time position correction to ground generated spacecraft ephemeris

• US 5,862,495 A
• Filed: 09/18/1996
• Issued: 01/19/1999
• Est. Priority Date: 09/18/1996
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Howley, Brian J., Bergesen, John E., Small, Hunt W.
• Primary Examiner(s): JORDAN, CHARLES T
• Application Number:
  US08/714,329
• Time in Patent Office: 853 Days
• Field of Search: 701/13, 701/14, 701/15, 701/16, 701/117, 701/120, 701/122, 701/226, 701/300, 701/301, 701/302, 244/135 A, 244/161, 244/186, 244/177, 244/194, 244/195, 244/164, 244/183, 244/167, 244/158 R, 244/165, 244/169, 73/178 R, 342/352, 342/354, 342/355, 342/413
• US Class Current: 701/13
• CPC Class Codes: G01S 19/27 creating, predicting or correcting ephemeris or almanac data within the receiver

Abstract

Real time correction to ground generated satellite ephemeris implements a reference trajectory management module (334), an error estimation module (336), an parameter calculation module (338) and a position information management module (340). The reference trajectory management module (334) accesses reference trajectory data such as ground generated ephemeris data which is uplinked to a spacecraft through a communications unit (312). The position information management module (340) accesses and interprets position information such as Global Positioning System (GPS) measurement data to provide measured spacecraft positions. The parameter calculation module (338) calculates spacecraft position and velocity from the reference trajectory data. The error estimation module (336) compares the measured and calculated positions to provide a position difference, smoothes the position difference to filter anomalous data, and provides a correction term for the determination of corrected spacecraft orbital parameters such as position and velocity. The time rate of change of the correction term may be used to provide additional correction to the orbital parameters.

Claims

1. In a system including a processor and a memory a method for real time on-board determination of corrected spacecraft orbital parameters, said method comprising:

obtaining a reference trajectory for the spacecraft based upon reference trajectory data provided from a source external to the spacecraft;

obtaining a measured position of the spacecraft corresponding to a first time;

calculating a position of the spacecraft along the reference trajectory which corresponds to the first time;

comparing the measured position and the calculated position corresponding to the first time;

determining a position error as a result of the camparison between the measured position and the calculated position corresponding to the first time;

determining an in-track component of the position error as a portion of the position error that is parallel to the reference trajectory;

determining a time correction term based upon the in-track component of the position error; and

calculating corrected orbital parameters on-board the spacecraft using the determined time correction term.

2. The method of claim 1, wherein the calculation of corrected orbital parameters includes computing the position of the spacecraft along the reference trajectory using a first time plus the time correction term.

3. The method of claim 2, wherein the calculation of corrected orbital parameters includes computing the velocity of the spacecraft using the first time plus the time correction term.

4. The method of claim 3, further comprising:

iteratively calculating the time correction term using a position error which is determined at discrete time intervals.

5. The method of claim 4, further comprising:

determining a rate of change of the time correction term.

6. The method of claim 5, further comprising:

using the rate of change of the time correction term to correct a calculated spacecraft position component of the calculated corrected spacecraft orbital parameters.

7. The method of claim 6, further comprising:

using the rate of change of the time correction term to correct a calculated spacecraft velocity component of the calculated corrected spacecraft orbital parameters.

8. An apparatus for accurately determining the orbital parameters of a spacecraft using reference trajectory data and position information, the apparatus comprising:

a position information management module, for providing a measured spacecraft position corresponding to a first time;

a reference trajectory management module, for obtaining a reference trajectory for the spacecraft from a source external to the spacecraft;

a parameter calculation module, in communication with the reference trajectory management module, for determining the position of the spacecraft along the reference trajectory which corresponds to the first time; and

an error estimation module, in communication with the position information management module, the reference trajectory management module, and the parameter calculation module, for comparing the measured position and the calculated position corresponding to the first time, determining a position error as the difference between the measured position and the calculated position corresponding to the first time, determining an in-track component of the position error as a portion of the position error that is parallel to the reference trajectory, providing time correction terms based upon the in-track component of the position error, and for calculating corrected orbital parameters based on the time correction terms.

9. A system for on-board accurate determination of orbital parameters of a spacecraft using reference trajectory data and position information, the system comprising:

a communications unit, for obtaining a reference trajectory for the spacecraft from a source external to the spacecraft;

a position information receiver, for receiving position information including a measured position of the spacecraft which corresponds to a first time;

a memory, in communication with the communications unit and the position information receiver, for storing the reference trajectory and the position of the spacecraft which corresponds to the first time; and

a central processing unit connected to the memory for determining a position of the spacecraft along the reference trajectory which corresponds to the first time, comparing the measured position and the determined position which correspond to the first time, wherein the comparison includes determining a position error as the difference between the measured position and the determined position corresponding to the first time, determining an in-track component of the position error as a portion of the position error that is parallel to the reference trajectory. and determining corrected orbital parameters based upon the comparison and the determined in-track component of the position error.