Deep space positioning system

• US 9,382,020 B1
• Filed: 08/27/2014
• Issued: 07/05/2016
• Est. Priority Date: 08/27/2014
• Status: Active Grant

• Current Assignee: United States of America as represented by the Administrator of NASA
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Vaughan, Andrew T., Riedel, Joseph E.
• Primary Examiner(s): Benedik, Justin
• Application Number:
  US14/470,438
• Time in Patent Office: 678 Days
• US Class Current: 1/1
• CPC Class Codes: B64G 1/10 Artificial satellites; Systems of such satellites; Interplanetary vehicles space shuttles B64G1/14
• 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 1/369 using gyroscopes as attitude sensors
• CPC Class Codes: B64G 1/52 Protection, safety or emergency devices; Survival aids
• CPC Class Codes: B64G 1/646 Docking or rendezvous systems refueling in space B64G1/4024
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: B64G 3/00 Observing or tracking cosmonautic vehicles

Abstract

A single, compact, lower power deep space positioning system (DPS) configured to determine a location of a spacecraft anywhere in the solar system, and provide state information relative to Earth, Sun, or any remote object. For example, the DPS includes a first camera and, possibly, a second camera configured to capture a plurality of navigation images to determine a state of a spacecraft in a solar system. The second camera is located behind, or adjacent to, a secondary reflector of a first camera in a body of a telescope.

Claims

1. An apparatus, comprising:

a first camera configured to capture at least one navigation image, and a second camera configured to capture at least one other navigation image, to determine a state of at least one object in a solar system,

wherein the second camera is located behind a secondary reflector of the first camera, or has an optical path through a mirror on the secondary reflector, in a body of a telescope, or mounted adjacent to the first camera.

2. The apparatus of claim 1, wherein

the second camera is mounted adjacent to the first camera using a distinct optical path.

3. The apparatus of claim 1, further comprising:

a mirror configured to rotate around a body of a telescope when the plurality of navigation images are being captured.

4. The apparatus of claim 3, wherein the mirror is configured to protect the first camera and a second camera when the mirror is in a closed state.

5. The apparatus of claim 3, further comprising:

an antenna attached to rear of the mirror.

6. The apparatus of claim 3, further comprising:

a sun shade configured to surround a majority of the mirror to protect the mirror, and prevent a glare during the capture of the navigation image.

7. An apparatus of claim 1, wherein the at least one object comprises the apparatus, a spacecraft, a natural object, or a combination thereof.

8. An apparatus of claim 1, wherein the first camera comprises a narrow angle camera, and the second camera comprises a wide angle camera.

9. An apparatus of claim 1, wherein the at least one navigation image captured by the first camera is used to locate at least one star.

10. An apparatus of claim 1, wherein the at least one other navigation image by the second camera is used to locate at least one target.

11. The apparatus of claim 1, further comprising:

a plurality of accelerometers affixed to a mirror, and configured to detect external forces at different angle on the mirror to determine the attitude rate of the spacecraft.

12. The apparatus of claim 11, wherein the plurality of accelerometers are configured to be calibrated when the spacecraft turns or when the mirror is slewed.