Three axis earth/star sensor

• US 5,189,295 A
• Filed: 08/30/1991
• Issued: 02/23/1993
• Est. Priority Date: 08/30/1991
• Status: Expired due to Fees

• Current Assignee: EDO Corporation (ITT, Inc.)
• Original Assignee: EDO Corporation (ITT, Inc.)
• Inventors: Falbel, Gerald
• Primary Examiner(s): Nelms, David C.
• Application Number:
  US07/753,105
• Time in Patent Office: 543 Days
• Field of Search: 250/203.1, 250/203.4, 250/203.6, 250/206.1, 250/206.2, 250/353, 356/144, 356/145, 356/146, 244/3.16, 244/3.17, 244/3.18, 244/158
• US Class Current: 250/206.2
• CPC Class Codes: G01C 21/025 with the use of startrackers
• CPC Class Codes: G01S 3/7864 T.V. type tracking systems
• CPC Class Codes: G01S 3/7867 Star trackers navigation using star trackers G01C21/025
• CPC Class Codes: G01S 5/163 Determination of attitude using inertial means G01C9/00; control of attitude G05D1/49

Abstract

An earth sensor primarily for use at geosynchronous altitude measures Pitch, Roll, as well as Yaw. Pitch and Roll are obtained from the sun illuminated earth crescent viewed through a pinhole by a CID video camera. A circular mask positioned in front of the pinhole blacks out the center 10 degrees of the earth. A beam splitter receives visible radiation from the earth crescent through the pinhole and combines it with energy from a lens system aimed at Polaris and beta Ursa Minor and/or gamma Cepheus and projects radiation from such polar stars onto the CID detector. Yaw is obtained by sensing the position of the pole star Polaris.

Claims

1. A three axis earth/star sensor mounted in a spacecraft is placed in an equatorial orbit around the earth for measuring Pitch, Roll and Yaw, while viewing Polaris, beta Ursa Minor and gamma Cepheus when in the field of view of the orbiting sensor comprising:

a pinhole aperture in said sensor for viewing the earth from said sensor'"'"'s equatorial orbit of the earth;

a beam splitter in alignment with said aperture for reflecting radiation from the earth coming through said pinhole and transmitting light from Polaris, beta Ursa Minor and gamma Cepheus when in the field of view of said beam splitter;

a visible light detector means in alignment with said beam splitter for receiving visible radiation from the earth through said pinhole and visible radiation from Polaris, beta Ursa Minor and gamma Cepheus when in the field of view of said detector means being applied thereto by said beam splitter; and

means for deriving Pitch, Roll and Yaw signals generated by said visible light detector means while orbiting the earth.

2. The sensor as claimed in claim 1 having an occulting mask in alignment with said pinhole aperture.

3. The sensor as claimed in claim 2 wherein said visible light detector means comprises a CID video camera.

4. The method of determining the Pitch, Roll and Yaw orientation of a body in equatorial orbit around the earth comprising the steps of:

viewing the sun illuminated earth crescent through a pinhole by a light sensitive detector means for obtaining Pitch and Roll information;

viewing visible radiation from at least two polar stars by said light sensitive detector means for obtaining Yaw information at all times and Pitch and Roll information in combination with a clock which star determined Pitch and Roll information can be averaged with the Pitch and Roll information obtained from the sun illuminated earth or used as the only Pitch and Roll information when the sun goes behind the earth during orbit;

comparing the Pitch and Roll information obtained from the Polar stars with Pitch and Roll information from the sun illuminated earth by the light sensitive detector means for determining the station of the body in orbit.

5. The method as claimed in claim 4 wherein the step of viewing the sun illuminated earth crescent includes blocking out the center 10°

of the earth.

6. The method as claimed in claim 4 wherein the step of viewing visible radiation from a polar star is provided through a field of view angle of at least 34°

by 34°

.

7. The method as claimed in claim 4, including the step of placing said body in geosynchronous orbit around the earth.