Integrated guidance system and method for providing guidance to a projectile on a trajectory

• US 5,442,560 A
• Filed: 07/29/1993
• Issued: 08/15/1995
• Est. Priority Date: 07/29/1993
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Kau, Shing P.
• Primary Examiner(s): ZANELLI, MICHAEL J
• Application Number:
  US08/099,076
• Time in Patent Office: 747 Days
• Field of Search: 364/453, 364/423, 364/462, 364/516, 364/559, 364/455, 33/321, 244/165, 244/79, 244/80
• US Class Current: 701/220
• CPC Class Codes: F41G 7/007 Preparatory measures taken before the launching of the guided missiles
• CPC Class Codes: G01C 21/16 by integrating acceleration or speed, i.e. inertial navigation

Abstract

An inertial measurement unit is provided which includes a core inertial measurement unit having accelerometers and gyroscopes aligned along x, y and z axes to provide signals to an onboard computer to determine position of the vehicle upon which they are mounted while in movement. A fourth accelerometer is pivoted perpendicular to the direction of the gravitational field for measuring the gravitational field about the axis upon which it is mounted to provide a reference set of data to an onboard computer prior to movement of the vehicle upon which the system is mounted.

Claims

1. An inertial measurement apparatus comprising:

an inertial measurement unit strapped down within a flight vehicle, said inertial measurement unit comprised of at least three gyroscope means for measuring rotational movement of said flight vehicle along x (roll), y (pitch) and z (yaw) axes thereof and at least three accelerometer means for measuring translational motion of said flight vehicle along each of said axes; and

separate, pivotally mounted accelerometer means for preflight measurement of the gravitational field acting on said flight vehicle along predetermined directions of a sensitive axis of said separate accelerometer means for calibration of bias and scale factor errors, said separate accelerometer means being locked in position for use of said preflight measurement as a matching reference for inflight data being generated by said inertial measurement unit when said flight vehicle is in flight to enhance targeting accuracy of said inertial measurement unit.

2. An apparatus as in claim 1 wherein said separate accelerometer means is pivotally mounted about the y (pitch) axis of said flight vehicle.

3. An apparatus as in claim 2 wherein said flight vehicle is an intercontinental missile having said apparatus mounted therein.

4. An apparatus as in claim 2 wherein said separate accelerometer means is of greater accuracy after preflight measurement than said at least three accelerometer means in said inertial measurement unit.

5. An apparatus as in claim 1 wherein said separate accelerometer means is pivotally mounted about the x (roll) axis of said flight vehicle.

6. An apparatus as in claim 5 wherein said flight vehicle is an interceptor missile launchable from an erectable launcher, with said missile having said apparatus mounted therein.

7. An apparatus as in claim 5 wherein said separate accelerometer means is of greater accuracy after preflight measurement than said at least three accelerometer means in said inertial measurement unit.

8. An apparatus as in claim 1 wherein said separate accelerometer means is of greater accuracy after preflight measurement than said at least three accelerometer means in said inertial measurement unit.

9. An apparatus as in claim 1 wherein said at least three gyroscope means comprises three ring-laser gyroscopes.

10. An apparatus as in claim 1 wherein said separate accelerometer means is connected to a stepping motor for pivoting said separate accelerometer means.

11. An apparatus as in claim 1 further comprising computing means connected to said inertial measurement unit and to said separate accelerometer means for receiving data therefrom to calculate change in position of said flight vehicle wherein said apparatus is to be mounted for guidance thereof, and for calibrating said data based on data input from said separate accelerometer means prior to flight of said flight vehicle.

12. A method of improving the measurement accuracy of a strapdown inertial measurement unit in a flight vehicle, said inertial measurement unit comprising at least three gyroscope means mounted for measuring rotational movement of said flight vehicle along the x(roll), y(pitch) and z(yaw) axes thereof, and at least three accelerometer means mounted for measuring translational motion of said flight vehicle along each of said axes, the method comprising:

pivoting a separate, pivotally mounted accelerometer means for preflight measurement of the gravitational field along a predetermined axis of the flight vehicle for calibration of bias and scale factor errors; and

locking in position said separate accelerometer means for use of said preflight measurement to correct for errors in measurement data generated by said inertial measurement unit when said flight vehicle is in flight to enhance targeting accuracy of said inertial measurement unit.

13. A method as in claim 12 wherein said preflight measurement is conducted about the y(pitch) axis of said flight vehicle, with said flight vehicle being an intercontinental missile.

14. A method as in claim 12 wherein said preflight measurement is conducted about the x(roll) axis of said flight vehicle, with said flight vehicle being an interceptor missile, and said preflight measurement being conducted with said interceptor missile on a launcher prior to erection thereof.