Two gimbal error averaging astro-inertial navigator

• US 5,396,326 A
• Filed: 04/03/1989
• Issued: 03/07/1995
• Est. Priority Date: 04/03/1989
• Status: Expired due to Fees

• Current Assignee: Northrop Corporation Los Angeles CA
• Original Assignee: Northrop Grumman Corporation
• Inventors: Knobbe, Edward J., Bose, Carl L.
• Primary Examiner(s): Buczinski, Stephen C.
• Application Number:
  US07/333,382
• Time in Patent Office: 2,164 Days
• Field of Search: 356/141, 356/152, 356/255, 356/139.01, 356/139.03, 33/320, 33/321, 33/324, 33/326, 73/514, 73/517 A
• US Class Current: 356/255
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems
• CPC Class Codes: G01C 21/185 for gravity
• CPC Class Codes: G01S 3/7867 Star trackers navigation using star trackers G01C21/025
• CPC Class Codes: G02B 7/00 Mountings, adjusting means, or light-tight connections, for optical elements

Abstract

A strapped down astro-inertial navigator includes a roll outer gimbal, a pitch inner gimbal and a platform coupled to the inner gimbal. An instrument cluster which includes X-axis, Y-axis and Z-axis ring laser gyros (RLGs) and associated accelerometers is mounted to the platform. Also hard mounted to the platform is a stellar sensor which includes a telescope and a solid state focal plane array which views stellar reference objects. In an astro-inertial mode of operation one or more stellar objects are tracked for a period of time. The roll and the pitch gimbals are employed to point the telescope and, periodically, to observe and average out the effects of star sensor and horizontal accelerometer errors. The star sensor error observability is accomplished by periodically rotating the inner and outer gimbals through 180° and the stellar objects once again tracked. Due to the 180° rotation boresight errors within the stellar tracker are observed and compensated for. The 180° rotation also serves to reorient the accelerometer input axes by 180°, thereby also beneficially causing accelerometer errors to average out. In a free inertial mode of operation the inner and outer gimbals are both continuously rotated through plus and minus 360° but at different rotational rates to provide 3 axis error averaging of both gyro and accelerometer errors.

Claims

1. A two gimbal inertial navigation apparatus comprising:

a first gimbal mounted for rotation about a first axis,

means for rotating said first gimbal through at least 360°

about said first axis,

a second gimbal mounted for rotation on said first gimbal about a second axis perpendicular to said first axis,

a platform rigidly coupled to said second gimbal along a strapdown axis which is substantially perpendicular to said platform, and

an instrument cluster for sensing accelerations along an X-axis, a Y-axis and a Z-axis, said instrument cluster being coupled to said platform, said instrument cluster comprising;

an X-axis gyroscope,

a Y-axis gyroscope,

a Z-axis gyroscope,

an X-axis accelerometer,

a Y-axis accelerometer,

a Z-axis accelerometer;

means for compensating for navigation errors resulting from gyro and accelerometer errors during free inertial navigation by rotating said two gimbals, and

means for performing three axis gyro and accelerometer error averaging based on data from rotating said two gimbals.

2. Inertial navigation apparatus as defined in claim 1 and further comprising means for imaging stellar objects, said imaging means being coupled to said platform and having an optical axis substantially parallel to said strapdown axis.

3. Inertial navigation apparatus as defined in claim 2 wherein said means for imaging stellar objects comprises a solid state imaging device.

4. Inertial navigation apparatus as defined in claim 3 wherein said means for imaging stellar objects comprises a CCD or a CID imager.

5. Inertial navigation apparatus as defined in claim 1 wherein said X-axis gyroscope, said Y-axis gyroscope and said Z-axis gyroscope are each a laser gyroscope.

6. A two gimbal strapdown astro-inertial navigator comprising

a roll axis gimbal coupled to a roll gimbal torque motor for rotating said roll axis gimbal through at least 360°

,

a pitch axis gimbal coupled to said roll axis gimbal and also coupled to a pitch gimbal torque motor for rotating said pitch axis gimbal through at least 360°

,

a platform coupled to said pitch axis gimbal along a strapdown axis, said strapdown axis being substantially perpendicular to said platform,

an instrument cluster coupled to said platform, said instrument cluster comprising

an X-axis laser gyroscope,

a Y-axis laser gyroscope,

a Z-axis laser gyroscope,

an X-axis accelerometer,

a Y-axis accelerometer,

a Z-axis accelerometer

said instrument cluster further comprising solid state imaging means for imaging stellar objects, said solid state imaging means having an optical axis which is substantially colinear with said strapdown axis,

means for compensating for navigation errors resulting from gyro and accelerometer errors during free inertial navigation by rotating said two gimbals, and

means for performing three axis gyro and accelerometer error averaging based on data from rotating said two gimbals.

7. An astro-inertial navigator as set forth in claim 6 and further comprising:

a roll resolver coupled to said roll axis gimbal for indicating an amount of rotation of said roll axis gimbal about a roll axis; and

a pitch resolver coupled to said pitch axis gimbal for indicating an amount of rotation of said pitch axis gimbal about a pitch axis.

8. An astro-inertial navigator as set forth in claim 6 wherein said solid state imaging means comprises a CCD or a CID imager optically coupled to a telescope.

9. A method, while star tracking, of substantially cancelling fixed errors of an X-axis accelerometer and a Y-axis accelerometer both of which are coupled to a platform, comprising the steps of:

orienting the platform in space such that an input axis of the X-axis accelerometer points along an X-axis and an input axis of the Y-axis accelerometer points along a Y-axis;

operating the X-axis accelerometer and the Y-axis accelerometer for a first predetermined interval of time, each of the accelerometers generating an output signal which includes a first error component;

rotating the platform in space such that the input axis of the X-axis accelerometer points along the X-axis in an opposite direction and the input axis of the Y-axis accelerometer points along the Y-axis in an opposite direction;

operating the X-axis accelerometer and the Y-axis accelerometer for a second predetermined interval of time, each of the accelerometers generating an output signal which includes a second error component, the second error component having a sign opposite that of the first error component and a magnitude substantially equal to that of the first error component; and

averaging the first and second error components such that a total error component over the first and the second predetermined intervals of time is substantially cancelled.

10. A method, while star tracking, of substantially compensating a boresight error of a star sensor which provides position related information to an astro-inertial navigator, the star sensor being coupled to a platform stabilized by a roll gimbal and a pitch gimbal, the platform being strapped down to the pitch gimbal along a strapdown axis which is substantially parallel with an optical axis of the star sensor, comprising the steps of:

orienting the roll gimbal and the pitch gimbal to point the star sensor optical axis at a predetermined stellar object;

determining a first angular misalignment between the optical axis and the stellar object, the first angular misalignment including a first component related to an attitude reference error of the navigator and a second component related to an angular misalignment of the optical axis relative to the strapdown axis;

rotating both the roll gimbal and the pitch gimbal by 180°

; and

determining a second angular misalignment between the optical axis and the stellar object, the second angular misalignment including a first component related to the attitude reference error of the navigator and a second component related to the angular misalignment of the optical axis relative to the strapdown axis, the second component after the step of rotating being of substantially equal magnitude and opposite sign to the second component before the step of rotating whereby the second component due to the angular misalignment of the optical axis relative to the strapdown axis is observed and compensated for.

11. A method of compensating for navigation errors resulting from gyro and accelerometer errors during free inertial navigation of a two gimbal inertial navigator having an instrument cluster supporting platform strapped down to an inner gimbal, comprising the steps of continuously rotating the inner gimbal through plus and minus 360°

at a first rotational rate while simultaneously rotating an outer gimbal through plus and minus 360°

at a second rotational rate while performing three axis gyro and accelerometer error averaging.

12. A method as set forth in claim 11 wherein the second rotational rate is approximately an order of magnitude faster than the first rotational rate.

13. A method as set forth in claim 12 wherein the the first rotational rate is approximately 6°

per second and the second rotational is approximately 0.6°

per second.

14. Apparatus for compensating for navigation errors resulting from gyro and accelerometer errors during free inertial navigation of a two gimbal inertial navigator having an instrument cluster supporting platform strapped down to an inner gimbal, comprising

means for continuously rotating the inner gimbal through plus and minus 360°

at a first rotational rate, and

means for simultaneously rotating an outer gimbal through plus and minus 360°

at a second rotational rate, and

means for performing three axis gyro and accelerometer error averaging.

15. Apparatus as in claim 14 wherein the second rotational rate is approximately an order of magnitude faster than the first rotational rate.

16. Apparatus as in claim 14 wherein the first rotational rate is approximately 6°

per second and the second rotational is approximately 0.6°

per second.

17. Apparatus for substantially compensating a boresight error of a star sensor, while star tracking, which provides position related information to an astro-inertial navigator, the star sensor being coupled to a platform stabilized by a roll gimbal and a pitch gimbal, the platform being strapped down to the pitch gimbal along a strapdown axis which is substantially parallel with an optical axis of the star sensor, comprising:

means for orienting the roll gimbal and the pitch gimbal to point the star sensor optical axis at a predetermined stellar object,

means for determining a first angular misalignment between the optical axis and the stellar object, the first angular misalignment including a first component related to an attitude reference error of the navigator and a second component related to an angular misalignment of the optical axis relative to the strapdown axis,

means for rotating both the roll gimbal and the pitch gimbal by 180°

, and

means for determining a second angular misalignment between the optical axis and the stellar object, the second angular misalignment including a first component related to the attitude reference error of the navigator and a second component related to the angular misalignment of the optical axis relative to the strapdown axis, the second component after the step of rotating being of substantially equal magnitude and opposite sign to the second component before the step of rotating whereby the second component due to the angular misalignment of the optical axis relative to the strapdown axis is observed and compensated for.

18. Apparatus for substantially cancelling fixed errors of an X-axis accelerometer and a Y-axis accelerometer, while star tracking, both of said accelerometers being coupled to a platform, comprising:

means for orienting the platform in space such that an input axis of the X-axis accelerometer points along an X-axis and an input axis of the Y-axis accelerometer points along a Y-axis,

means for operating the X-axis accelerometer and the Y-axis accelerometer for a first predetermined interval of time, each of the accelerometers generating an output signal which includes a first error component,

means for rotating the platform in space such that the input axis of the X-axis accelerometer points along the X-axis in an opposite direction and the input axis of the Y-axis accelerometer points along the Y-axis in an opposite direction,

means for operating the X-axis accelerometer and the Y-axis accelerometer for a second predetermined interval of time, each of the accelerometers generating an output signal which includes a second error component, the second error component having a sign opposite that of the first error component and a magnitude substantially equal to that of the first error component, and

means for averaging the first and second error components such that a total error component over the first and the second pre-determined intervals of time is substantially cancelled.