Analog sun sensor

• US 5,572,316 A
• Filed: 12/07/1994
• Issued: 11/05/1996
• Est. Priority Date: 12/07/1994
• Status: Expired due to Term

• Current Assignee: EDO Corporation (L3Harris Technologies, Inc.)
• Original Assignee: EDO Corporation (L3Harris Technologies, Inc.)
• Inventors: Bednarek, Todd J., Zaffanella, Carlo E., Savoca, Robert C.
• Primary Examiner(s): Buczinski, Stephen C.
• Application Number:
  US08/350,683
• Time in Patent Office: 699 Days
• Field of Search: 250/203.4, 356/139.03, 356/139.01, 356/141.5, 356/141.2
• US Class Current: 356/139.01
• CPC Class Codes: G01C 21/24 specially adapted for cosmonautical navigation

Abstract

Continuous positional information for an orbiting body such as a spacecraft, satellite, or the like with respect to a reference body, for example, the sun, is provided by a first continuous sensor which continually views the sun from the orbiting body and generates electrical signals which provide two axis information on the orbiting body'"'"'s position. Analog sensors of this type have low accuracy because of transfer function non-linearity, degradation due to environmental aging, or radiation effects and others. A second periodic sensor is directed at the reference body to provide periodic positional updates. These updates are used as references to which the instantaneous output of a continuous sensor are compared so that error associated with the output of the continuous sensor can be eliminated to the accuracy of the calibration. The first continuous sensor preferably utilizes a first and second double triangle detector arranged to form first and second rectangles each having a slot aperture mounted thereon for projecting a line image normal to each rectangle. The first and second double triangle detectors are arranged orthogonally with respect to each other. An algorithm is used to accurately locate the position of the slit shadows on the first and second detectors on the continuous sensor, and thus provide a continuous position for the reference body such as the sun. The second periodic sensor has a patterned detector mask positioned over a very small area detector for producing periodic positional updates which information can be used to correct the continuous sensor errors and provide an accurate analog sun position sensor.

Claims

1. An attitude sensor for providing continuous positional information for an orbiting body such as a spacecraft, satellite or the like with respect to a reference body comprising:

a first continuous sensor continuously viewing a reference body from said orbiting body for generating electrical signals in a predetermined time frame which provide two axis information with respect to the reference body,

a second periodic sensor means directed at said reference body from said orbiting body having patterned mask means covering said periodic sensor means for producing periodic electrical signals over a shorter time frame than said electrical signals generated in said predetermined time frame by said first continuous sensor,

means for combining said electrical signals from said first continuous sensor and said periodic electrical signals from said second periodic sensor means for periodically calibrating the two axis information provided by said first sensor to correct for errors in the two axis information provided by said first sensor.

2. The attitude sensor as claimed in claim 1 wherein said first continuous sensor comprises a pair of double triangle detectors arranged to form a rectangle,

a slit aperture mask mounted in a housing for said first sensor, said aperture mask projecting a line image normal to said rectangle formed by said triangular detectors.

3. The attitude sensor as claimed in claim 1 wherein said second periodic sensor means comprises:

a small area detector means sensitive to radiation emitted by the reference body,

a patterned detector mask spaced in front of said small area detector means having at least one open slot therein.

4. The attitude sensor as claimed in claim 3 wherein said second periodic sensor means includes two separate small area detectors each having a patterned mask, one of said masks comprising a series of spaced parallel horizontal bars for providing the reference body'"'"'s position in elevation, the other of said masks comprising a series of spaced parallel vertical bars for providing the reference body'"'"'s position in azimuth.

5. The attitude sensor as claimed in claim 2 wherein said second periodic sensor means comprises:

a small area detector means sensitive to radiation emitted by the reference body, and

a patterned detector mask spaced in front of said small area detector means.

6. The attitude sensor as claimed in claim 5 wherein said second periodic sensor means includes two separate detectors each having a patterned mask, one of said masks comprising a series of spaced parallel horizontal bars for providing the reference body'"'"'s position in elevation, the other of said masks comprising a series of spaced parallel vertical bars for providing the reference body'"'"'s position in azimuth.

7. The attitude sensor as claimed in claim 1 wherein said first continuous sensor and said second periodic sensors have common detector means, said periodic sensors comprising a single opaque bar in the plane of said common detector means for periodically blocking said common detector means view of said reference body, thereby reducing the detector means signal to zero for a short interval for calibrating said detector means at a known predetermined angular position.