Satellite camera image navigation

• US 4,688,092 A
• Filed: 05/06/1986
• Issued: 08/18/1987
• Est. Priority Date: 05/06/1986
• Status: Expired due to Term

• Current Assignee: Space Systems/Loral Incorporated (Loral Space and Communications Incorporated)
• Original Assignee: Ford Aerospace & Communications Corporation
• Inventors: Hanson, Charles W., Kamel, Ahmed A., Savides, John, Graul, Donald W.
• Primary Examiner(s): Britton, Howard W.
• Application Number:
  US06/860,142
• Time in Patent Office: 469 Days
• Field of Search: 358/109, 358/103, 358/107, 358/140, 358/160, 358/180, 370/104, 382/45, 33/320
• US Class Current: 348/147
• CPC Class Codes: G01C 11/02 Picture taking arrangements specially adapted for photogrammetry or photographic surveying, e.g. controlling overlapping of pictures
• CPC Class Codes: G09B 9/52 for teaching control of an outer space vehicle

Abstract

Pixels within a satellite camera (1, 2) image are precisely located in terms of latitude and longitude on a celestial body, such as the earth, being imaged. A computer (60) on the earth generates models (40, 50) of the satellite'"'"'s orbit and attitude, respectively. The orbit model (40) is generated from measurements of stars and landmarks taken by the camera (1, 2), and by range data. The orbit model (40) is an expression of the satellite'"'"'s latitude and longitude at the subsatellite point, and of the altitude of the satellite, as a function of time, using as coefficients (K) the six Keplerian elements at epoch. The attitude model (50) is based upon star measurements taken by each camera (1, 2). The attitude model (50) is a set of expressions for the deviations in a set of mutually orthogonal reference optical axes (x, y, z) as a function of time, for each camera (1, 2). Measured data is fit into the models (40, 50) using a walking least squares fit algorithm. A transformation computer (66 ) transforms pixel coordinates as telemetered by the camera (1, 2) into earth latitude and longitude coordinates, using the orbit and attitude models (40, 50).

Claims

1. Apparatus for locating any pixel within a satellite camera image in terms of latitude and longitude, said apparatus comprising:

a satellite in orbit around a celestial body;

an imaging camera on board the satellite for taking images of scenes on the celestial body, wherein each image is divided into a plurality of pixels;

modeling means which uses measurements taken by the cameras to generate an estimate of the satellite'"'"'s orbit and an estimate of the camera'"'"'s attitude; and

coupled to said modeling means, means for transforming pixel locations as announced by the camera into latitude and longitude coordinates with respect to the celestial body.

2. The apparatus of claim 1 wherein

the modeling means is located external to the satellite;

the estimates of the satellite'"'"'s orbit and attitude are slowly moving functions of time; and

the orbit and attitude estimates are periodically updated by measurements taken by the camera and telemetered to the modeling means.

3. The apparatus of claim 1 wherein the orbit estimate is first generated, and then the attitude estimate is generated, said attitude estimate being based solely on observations of stars made by the camera.

4. The apparatus of claim 1 wherein the modeling means simultaneously generates the estimates of the satellite orbit and camera attitude.

5. The apparatus of claim 1 further comprising a second instrument, wherein the modeling means generates an estimate of the satellite'"'"'s orbit, an estimate of the camera'"'"'s attitude, and an estimate of the second instrument'"'"'s attitude.

6. The apparatus of claim 1 wherein the attitude estimate is an expression of the motion of a set of mutually orthogonal reference axes as a trigonometric series in time.

7. The apparatus of claim 1

wherein the orbit estimate is an expression of the satellite'"'"'s latitude and longitude at the subsatellite point, and of the altitude of the satellite, as a function of time, comprising coefficients which are the six Keplerian elements at epoch;

wherein the Keplerian elements at epoch are estimated using a walking least squares fit based upon star and celestial body landmark location data measured by the camera and telemetered to the modeling means.

8. The apparatus of claim 1 wherein the transforming means performs, in the following order, the following three transformations:

a mirror transformation transforming pixel coordinates determined by the camera into pointing coordinates of a scanning mirror associated with the camera;

an attitude transformation transforming the pointing coordinates into orbit-based pointing angles, said attitude transformation taking into account the attitude estimate; and

an orbital transformation transforming the orbit-based pointing angles into latitude and longitude on said celestial body, said orbital transformation taking into account said orbit estimate.

9. Apparatus of claim 1 wherein the estimate of the satellite'"'"'s orbit is generated from measurements of stars and celestial body landmarks taken by the camera, and by measurements of the satellite'"'"'s altitude above the celestial body.

10. The apparatus of claim 9 wherein the celestial body is the earth, the modeling means and transforming means are located on the earth, and the measurements of the satellite'"'"'s altitude are obtained by sending a signal from the earth to the satellite and back to the earth.