Method of attitude determination using earth and star sensors

• US 5,412,574 A
• Filed: 05/14/1993
• Issued: 05/02/1995
• Est. Priority Date: 05/14/1993
• Status: Expired due to Fees

• Current Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Parks, Thomas R., Bender, Douglas J., Brozenec, Thomas F.
• Primary Examiner(s): Teska, Kevin J.
• Assistant Examiner(s): NGUYEN, TAN QUANG
• Application Number:
  US08/061,095
• Time in Patent Office: 718 Days
• Field of Search: 364/455, 364/459, 244/164, 244/171, 250/206.2, 356/141, 356/142, 356/143, 356/152
• US Class Current: 701/222
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/361 using star sensors
• CPC Class Codes: B64G 1/365 using horizon or Earth sensors
• CPC Class Codes: G01C 21/025 with the use of startrackers
• CPC Class Codes: G01S 3/7867 Star trackers navigation using star trackers G01C21/025

Abstract

A method of attitude measurement for an artificial satellite (100) utilizes one or more star trackers (12) together with an earth sensor (30). Periodic updates of satellite orbital information, either propagated onboard or from a ground station are combined with earth and star position coordinate data to provide a continuous and accurate measurement of the spacecraft body 3-axis attitude. The method can be used for ground-based attitude determination or onboard closed loop control systems.

Claims

1. A system for determining the 3-axis attitude of a spacecraft in a preselected orbit, comprising:

star sensing means on said spacecraft for sensing the positions of stars relative to said sensing means, and for producing first signals representing said star positions, said star sensing means including star trackers each having a field of vision aligned in a preselected direction and position with respect to said spacecraft, each of said star trackers including

(1) acquiring means for acquiring star position information describing stars within said field of vision.

(2) tracking means for tracking said stars within said field of vision.

(3) a star catalog.

(4) means for identifying said stars within said field of vision using said star position information and said star catalog, and

(5) digitizing means for digitizing said star position information into digitized representations of the positions of said stars relative to said spacecraft and said spacecraft orbit, respectively;

terrestrial body sensing means on said spacecraft for sensing the position of a terrestrial body relative to said spacecraft, and for producing second signals representing said terrestrial body position; and

processing means for processing said first and second signals and for determining said 3-axis attitude of said spacecraft.

2. The system of claim 1 wherein each of said star trackers further comprises averaging the normalizing means for averaging and normalizing said digitized representations of said star positions to determine an averaged and normalized representation of said star positions relative to said spacecraft and said spacecraft orbit, respectively.

3. The system of claim 2 wherein said first signals comprise said digitized averaged and normalized representation of said star positions relative to said spacecraft and said spacecraft orbit, respectively.

4. A spacecraft attitude control system for determining the 3-axis attitude of a spacecraft in a preselected orbit, consisting essentially of:

star sensing means on said spacecraft for sensing the positions of stars relative to said sensing means, and for producing first signals representing said star positions;

cross-link sensing means on said spacecraft for sensing the position of a preselected RF beacon relative to said spacecraft, and for producing second signals representing said beacon position; and

processing means for processing said first and second signals and for determining said 3-axis attitude of said spacecraft.

5. The system of claim 4 wherein said cross-link sensing means is an autotrack sensor that is an RF receiver, using an RF source.

6. The system of claim 5 wherein said RF receiver measures the position of said RF source relative to said spacecraft and said spacecraft orbit, respectively.

7. A method of determining the three axis attitude of a spacecraft in a preselected orbit, using star trackers on said spacecraft, an on-board star catalog and terrestrial sensor on said spacecraft, comprising the steps of:

(A) measuring the position of a terrestrial body with respect to said spacecraft, using said terrestrial sensor;

(B) generating a first set of coordinate data using said orbit, said first set of coordinate date defining the position of said terrestrial body relative to said spacecraft orbit;

(C) measuring the positions of each of a plurality of stars with respect to said star trackers, using said star trackers;

(D) generating a second set of coordinate data using the positions measured in step (C), said second set of coordinate data defining the positions of said stars relative to said spacecraft;

(E) identifying each star measured in step (C), using said star trackers and said on-board star catalog, to generate a third set of coordinate data, said third set of coordinate data defining the positions of said stars relative to said spacecraft orbit; and

(F) determining said attitude of said spacecraft using the position measured in step (A) and the first, second and third sets of coordinate data respectively generated in steps (B), (D) and (E).

8. The method of claim 7 wherein step (A) is performed by the substep of measuring the nadir of said terrestrial body.

9. The method of claim 7 wherein step (A) is performed by the substeps of measuring the azimuth and elevation of a preselected ground station having a location of known longitude and latitude on said terrestrial body.

10. The method of claim 7 wherein step (B) is performed by the substeps of generating said first set of coordinate data, using information regarding said spacecraft orbit and a fourth set of coordinate data, said fourth set of coordinate data having an almanac of the position of said terrestrial body relative to time.

11. The method of claim 7 wherein said first set of coordinate data is defined as a position vector, relative to said spacecraft orbit, having the following representation:

##EQU14##

12. The method of claim 7 wherein step (C) is performed by acquiring and tracking said plurality of stars as said stars pass through the field of vision of said star tracker.

13. The method of claim 7 wherein step (D) is performed by transforming a fifth set of coordinate data into said second set of coordinate data, said fifth set of coordinate data defining the positions measured in step (C).

14. The method of claim 7 wherein step (E) is performed by transforming a sixth set of coordinate data into said third set of coordinate data, said sixth set of coordinate data defining the positions of said identified in step (E) relative to said terrestrial body.

15. The method of claim 7 wherein step (F) is performed by the substeps of averaging and normalizing the second set of coordinate data in step (D) to determine an averaged and normalized representation of said second set of coordinate data.

16. The method of claim 7 wherein step (F) is performed by the substeps of averaging and normalizing the third set of coordinate data in step (E) to determine an averaged and normalized representation of said third set of coordinate data.

17. The method of claim 7 wherein step (F) is performed by the substep of defining a set of spacecraft attitude variables in terms of said measurement from step (A) and said first, second and third sets of coordinate data, said attitude variables defining the roll pointing error, the pitch pointing error, and the yaw pointing error of said spacecraft, respectively.

18. The method of claim 17 wherein step (F) is performed by the substep of forming a system of equations using said set of spacecraft attitude variables, said averaged and normalized set of coordinate data in claim 16 and said averaged and normalized set of coordinate data in claim 17.

19. The method of claim 18 wherein step (F) is performed by the substep of solving said system of equations to determine a set of values for said attitude variables.

20. The method of claim 19 wherein step (F) is performed by the substep of determining said attitude of said spacecraft from said values for said attitude variables.

21. A method of determining the three axis attitude of a spacecraft in a preselected orbit, using star trackers on said spacecraft, an on-board star catalog and a terrestrial sensor on said spacecraft, comprising the steps of:

(A) measuring the position of a terrestrial body with respect to said spacecraft, using said terrestrial sensor by measuring the nadir of said terrestrial body;

(B) generating a first set of coordinate data using information regarding said spacecraft orbit and a second set of coordinate data, said second set of coordinate data having an almanac of the position of said terrestrial body relative to time, said first set of coordinate data defining the position of said terrestrial body relative to said spacecraft orbit;

(C) measuring the positions of each of a plurality of stars with respect to said star trackers, using said star trackers by acquiring and tracking said plurality of stars as said stars pass through the field of vision of said star trackers;

(D) generating a third set of coordinate data using the positions measured in step (C) by transforming a fourth set of coordinate data into said third set of coordinate data, said fourth set of coordinate data defining the positions measured in step (C), said third set of coordinate data defining the positions of said stars relative to said spacecraft;

(E) identifying each star measured in step (C), using said star tracker and said on-board star catalog by tracking said stars and comparing tracking information to information contained in said star catalog;

(F) generating a fifth set of coordinate data using the identification of each star from (E), said fifth set of coordinate data defining the positions of said stars relative to said spacecraft orbit;

(G) averaging and normalizing the third set of coordinate data in step (D) to determine a single averaged and normalized representation of said third set of coordinate data;

(H) averaging and normalizing the fifth set of coordinate data in step (F) to determine a single average and normalized representation of said fifth set of coordinate data;

(I) defining a set of spacecraft attitude variables in terms of said measurement from step (A) and said first, third and fifth sets of coordinate data, said attitude variables defining the roll pointing error, the pitch pointing error, and the yaw pointing error of said spacecraft, respectively;

(J) forming a system of equations using said set of spacecraft attitude variables and said averaged and normalized representations of said third and fifth sets of coordinate data in steps (G) and (H), respectively;

(K) determining a set of value data for said attitude variables by solving the system of equations in step (J); and

(L) determining said attitude of said spacecraft from the set of value data in step (K).

22. The method of claim 21 wherein step (D) is performed by the substeps of transforming said fourth set of coordinate data into said third set of coordinate data by using a first direction cosine transformation matrix, said first transformation matrix having the following notation:

##EQU15## where j=1, . . . , n (where n=the number of star trackers),

α

_AZ,_j =the azimuth mounting angle,

ε

_EL,_j =the elevation mounting angle, and

δ

_R,_j =the rotation mounting angle of said star tracker relative to said spacecraft.

23. The method of claim 21 wherein step (F) is performed by the substeps of transforming a sixth set of coordinate data into said fifth set of coordinate data using a second direction cosine transformation matrix, said sixth set of coordinate data defining the positions of said stars identified in step (E) relative to said terrestrial body, said second transformation matrix having the following notation:

##STR2## where i=the orbit inclination,

Ω

=the right ascension of the ascending node, and

θ

.sub. = the angle proportional to the time of day.

24. The method of claim 21 wherein step (G) is performed by the substeps of averaging and normalizing said third set of coordinate data to determine an averaged and normalized representation of said third set of coordinate data, using the equation:

##EQU16## where j=the number of star trackers;

k=the number of stars measured and identified by each star tracker;

s_avg,j =said averaged and normalized representation of said third set of coordinate data; and

s_k,j =the measurement of each said star, respectively.

25. The method of claim 21 wherein step (H) is performed by the substeps of averaging and normalizing said fifth set of coordinate data to determine an averaged and normalized representation of said fifth set of coordinate data, using the equation:

##EQU17## where j=the number of said star trackers;

k=the number of stars measured and identified by each star tracker;

r_avg,j =said averaged and normalized representation of said fifth set of coordinate data; and

r_k,j =said position of each said star relative to said spacecraft orbit.

26. The method of claim 21 wherein step (I) is performed by the substeps of defining a set of spacecraft attitude variables in terms of said measurement from step (A) and said first, third and fifth sets of coordinate data, said attitude variables defining arguments in a third direction cosine transformation matrix, said third transformation matrix being a transformation from coordinates relative to said spacecraft orbit to coordinates relative to said spacecraft and having the following notation:

##EQU18## where φ

=the roll pointing error;

θ

=the pitch pointing error, and

Ψ

=the yaw pointing error of said spacecraft, respectively.

27. The method of claim 26 wherein step (J) is performed by the substeps of forming a system of linear equations using said third matrix and said averaged and normalized representations of said third and fifth sets of coordinate data in steps (G) and (H), respectively.

28. The method of claim 27 wherein step (K) is performed by the substeps of determining a set of value data for said attitude variables by solving the system of linear equations in step (J) using least squares approximation.

29. A system for determining the 3-axis attitude of a spacecraft in a preselected orbit, comprising:

star sensing means on said spacecraft for sensing the position of stars relative to said sensing means, and for producing first signals representing said star positions;

earth sensing means on said spacecraft for sensing the position of the earth relative to said spacecraft, and for producing second signals representing said earth position, said earth sensing including a carbon dioxide band sensor for measuring the position of said earth relative to said spacecraft by measuring the nadir of the earth, said earth sensing producing said first signals, said first signals being digitized representations of said earth position relative to said spacecraft and said spacecraft orbit, respectively; and

,

processing means for processing said first and second signals and for determining said 3-axis attitude of said spacecraft.

30. A system for determining the 3-axis attitude of a spacecraft in a preselected orbit, comprising:

star sensing means on said spacecraft for sensing the position of said stars relative to said sensing means, and for producing first signals representing said star positions; and

earth sensing means on said spacecraft for sensing the position of the earth relative to said spacecraft, and for producing second signals representing said earth position, said earth sensing means comprising RF ground beacon sensor for measuring the position of the earth relative to said spacecraft measuring the azimuth and elevation of a preselected ground station having known longitude and latitude location values on said earth, said earth sensing means producing said first signals that are digitized representations of said earth position relative to said spacecraft and said spacecraft orbit, respectively.

31. A system for determining the 3-axis attitude of a spacecraft in a preselected orbit, comprising:

star sensing means on said spacecraft for sensing the positions of stars relative to said sensing means, and for producing first signals representing said star positions;

terrestrial body sensing means on said spacecraft for sensing the position of a terrestrial body relative to said spacecraft, and for producing said second signals representing said terrestrial body position; and

,

processing means for processing said first and second signals for determining said 3-axis attitude of said spacecraft, said processing means including

(1) collecting and averaging means for collecting and averaging said first and second signals, and,

(2) estimating means for estimating a set of attitude variables using the least squares approximations of said attitude variables, said attitude variables defining said 3-axis attitude of said spacecraft.