METHOD AND APPARATUS FOR SATELLITE ORBIT INTERPOLATION USING PIECEWISE HERMITE INTERPOLATING POLYNOMIALS

• US 20020065587A1
• Filed: 11/30/2000
• Published: 05/30/2002
• Est. Priority Date: 11/30/2000
• Status: Active Grant

• Current Assignee: HMD Global Oy
• Original Assignee: Nokia Mobile Phones UK Limited (Nokia Corporation)
• Inventors: Piché, Robert, Syrjärinne, Paula
• Granted Patent: US 6,424,890 B1
• Time in Patent Office: Days
• US Class Current: 701/13
• CPC Class Codes: B64G 1/244 Spacecraft control systems

Abstract

A method and corresponding apparatus and system for determining the position of a satellite at any instant of time between two sampling instants, based on information in at least one ephemeris message provided by the satellite, the information allowing the computation of the satellite positions at the two sampling instants. The method includes the steps of: computing the satellite positions at two sampling instants using parameters provided in one or more ephemeris messages with suitable times of ephemeris; and for each of the three dimensions of motion, constructing a polynomial of at least third degree by choosing the coefficients of the polynomial so that it interpolates the satellite position at each of the two sampling instants. Typically, the method also calls for computing the satellite velocities at each of the sampling instants, and choosing the coefficients of the polynomial for each of the three dimensions of motion so as to provide a polynomial that not only interpolates the satellite position at the two sampling instants, but has a first derivative that interpolates the satellite velocity at the two sampling instants. The polynomial and its derivative can then be evaluated at any desired time between the sampling instants to determine the spacecraft position and velocity, respectively, at the desired time. The method also provides for determining at least a fifth degree polynomial by using values of the spacecraft acceleration, at each of the sampling instants, calculated from the ephemeris information. The polynomial is typically a Hermite interpolating polynomial.

Claims

1. A method for determining the position of a satellite at any instant of time between two sampling instants, based on information in at least one navigation message provided by the satellite, the information allowing the computation of the satellite positions at the two sampling instants, the method comprising the steps of:

a) setting the first sampling instant;

b) computing the satellite position at the first sampling instant using parameters provided in a navigation message with a suitable time of validity;

c) setting a next sampling instant later than the first sampling instant;

d) computing the satellite position at the second sampling instant again using parameters provided in a navigation message with a suitable time of validity; and

e) for each of the three dimensions of motion, constructing a polynomial of at least third degree by choosing the coefficients of the polynomial so that the polynomial interpolates the satellite position at each of the sampling instants.

2. The method of claim 1, further comprising the steps of:

a) computing the satellites velocities at each of the sampling instants based on the same parameters as were used in computing the satellite positions at the sampling instant; and

b) choosing the coefficients of the polynomial for each of the three dimensions of motion so as to provide a polynomial that not only interpolates the satellite position at each of the sampling instants, but is such that its first derivative interpolates the satellite velocity at each of the sampling instants.

3. The method of claim 2, wherein the polynomial is a Hermite interpolating polynomial.

4. The method of claim 2, wherein, to obtain an approximate spacecraft position at a desired instant of time between the two sampling instants, the polynomial is evaluated at the desired instant of time.

5. The method of claim 4, wherein the derivative of the polynomial is evaluated at an instant of time between the two sampling instants so as to determine the spacecraft velocity at the instant of time.

6. The method of claim 2, wherein the polynomial is of at least fifth degree, and further comprising the steps of:

a) calculating the satellite acceleration at each of the sampling instants based on the same parameters as were used in computing the satellite positions at the sampling instant; and

b) choosing the coefficients of the polynomial for each of the three dimensions of motion so as to provide a polynomial corresponding to the two sampling instants that interpolates the satellite position at the two sampling instants, and further is such that its first derivative interpolates the satellite velocity at the two sampling instants and its second derivative interpolates the satellite acceleration at the two sampling instants.

7. The method of claim 6, wherein the second derivative of the polynomial is evaluated at an instant of time between the two sampling instants so as to determine the spacecraft acceleration at the instant of time.

24. The method of claim 1, wherein any navigation message is an ephemeris message, and further wherein any time of validity is a time of ephemeris.

8. An apparatus for determining the position of a satellite at any instant of time between two sampling instants, based on information in at least one navigation message provided by the satellite, the information allowing the computation of the satellite positions at the two sampling instants, the method comprising the steps of:

a) means for setting the first sampling instant;

b) means for computing the satellite position at the first sampling instant using parameters provided in a navigation message with a suitable time of validity;

c) means for setting a next sampling instant later than the first sampling instant;

d) means for computing the satellite position at the second sampling instant again using parameters provided in a navigation message with a suitable time of validity; and

e) means, for each of the three dimensions of motion, for constructing a polynomial of at least third degree by choosing the coefficients of the polynomial so that the polynomial interpolates the satellite position at each of the sampling instants.

9. The apparatus of claim 8, further comprising:

a) means for computing the satellites velocities at each of the sampling instants based on the same parameters as were used in computing the satellite positions at the sampling instant; and

b) means for choosing the coefficients of the polynomial for each of the three dimensions of motion so as to provide a polynomial that not only interpolates the satellite position at each of the sampling instants, but is such that its first derivative interpolates the satellite velocity at each of the sampling instants.

10. The apparatus of claim 9, wherein the polynomial is a Hermite interpolating polynomial.

11. The apparatus of claim 9, further comprising means for evaluating the polynomial at a desired instant of time between the two sampling instants.

12. The apparatus of claim 9, further comprising means for evaluating the first derivative of the polynomial at an instant of time between the two sampling instants so as to enable determining the spacecraft velocity at the instant of time.

13. The apparatus of claim 9, wherein the polynomial is of at least fifth degree, and further comprising:

a) means for calculating the satellite acceleration at each of the sampling instants based on the same parameters as were used in computing the satellite positions at the sampling instant; and

b) means for choosing the coefficients of the polynomial for each of the three dimensions of motion so as to provide a polynomial corresponding to the two sampling instants that interpolates the satellite position at the two sampling instants, and further is such that its first derivative interpolates the satellite velocity at the two sampling instants and its second derivative interpolates the satellite acceleration at the two sampling instants.

14. The apparatus of claim 13, further comprising means for evaluating the second derivative of the polynomial at an instant of time between the two sampling instants so as to determine the spacecraft acceleration at the instant of time.

16. The system of claim 15, further comprising:

a) means for computing the satellites velocities at each of the sampling instants based on the same parameters as were used in computing the satellite positions at the sampling instant; and

b) means for choosing the coefficients of the polynomial for each of the three dimensions of motion so as to provide a polynomial that not only interpolates the satellite position at each of the sampling instants, but is such that its first derivative interpolates the satellite velocity at each of the sampling instants.

17. The system of claim 16, wherein the polynomial is a Hermite interpolating polynomial.

18. The system of claim 16, further comprising means for evaluating the polynomial at a desired instant of time between the two sampling instants.

19. The system of claim 16, further comprising means for evaluating the first derivative of the polynomial at an instant of time between the two sampling instants so as to enable determining the spacecraft velocity at the instant of time.

20. The system of claim 16, wherein the polynomial is of at least fifth degree, and further comprising:

c) means for calculating the satellite acceleration at each of the sampling instants based on the same parameters as were use d in computing the satellite positions at the sampling instant; and

d) means for choosing the coefficients of the polynomial for each of the three dimensions of motion so as to provide a polynomial corresponding to the two sampling instants that interpolates the satellite position at the two sampling instants, and further is such that its first derivative interpolates the satellite velocity at the two sampling instants and its second derivative interpolates the satellite acceleration at the two sampling instants.

21. The system of claim 20, further comprising means for evaluating the second derivative of the polynomial at an instant of time between the two sampling instants so as to determine the spacecraft acceleration at the instant of time.

22. The system of claim 15, wherein at least some of means for computing the satellite position at a sampling instant are located in a facility external to the receiver, a facility that is in wireless communication with the receiver.

23. The system of claim 15, wherein at least some of the means for constructing, for each of the three dimensions of motion, a polynomial of at least third degree are located in a facility external to the receiver, a facility that is in wireless communication with the receiver.

25. The apparatus of claim 8, wherein any navigation message is an ephemeris message, and further wherein any time of validity is a time of ephemeris.

26. The system of claim 15, wherein any navigation message is an ephemeris message, and further wherein any time of validity is a time of ephemeris.

15. A system for determining the position of a satellite at any instant of time between two sampling instants, based on information in at least one navigation message provided by the satellite, the information allowing the computation of the satellite positions at the two sampling instants, the method comprising the steps of:

a) the satellite, for providing the ephemeris message;

b) a receiver, for receiving the ephemeris message;

c) means for setting the first sampling instant;

d) means for computing the satellite position at the first sampling instant using parameters provided in a navigation message with a suitable time of validity;

e) means for setting a next sampling instant later than the first sampling instant;

f) means for computing the satellite position at the second sampling instant again using parameters provided in a navigation message with a suitable time of validity; and

g) means, for each of the three dimensions of motion, for constructing a polynomial of at least third degree by choosing the coefficients of the polynomial so that the polynomial interpolates the satellite position at each of the sampling instants.