System for aligning the inertial unit of a carried vehicle on that of a carrier vehicle

• US 5,150,856 A
• Filed: 10/29/1991
• Issued: 09/29/1992
• Est. Priority Date: 10/29/1990
• Status: Expired due to Fees

• Current Assignee: Aerospatiale Societe Nationale Industrielle
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Gaide, Pierre
• Primary Examiner(s): Jordan, Charles T.
• Application Number:
  US07/783,903
• Time in Patent Office: 336 Days
• Field of Search: 244/3.1, 244/3.15, 244/3.2, 244/3.21
• US Class Current: 244/3.2
• CPC Class Codes: F41G 7/007 Preparatory measures taken before the launching of the guided missiles
• CPC Class Codes: G01C 21/183 Compensation of inertial measurements, e.g. for temperature effects
• CPC Class Codes: G01C 25/005 initial alignment, calibration or starting-up of inertial devices

Abstract

The system may be used, for example, to initialize the inertial unit of a missile from the inertial unit of a vehicle carrying the missile. According to the invention, a servo-control circuit is provided for slaving data in the missile inertial unit on data from the carrier inertial unit, together with a Kalman filter connected in parallel with said servo-control circuit and designed to identify harmonization errors between the two inertial units.

Claims

1. A system comprising:

a first moving vehicle provided with a first inertial navigation unit in operation and referenced on a first intrinsic reference axis system tied to a system of terrestrial axes;

a second vehicle provided with a second inertial navigation unit that is to be put into operation, said unit being referenced to a second intrinsic reference axis system similar to said first intrinsic reference axis system, said second vehicle being carried by said first vehicle and being stationary on average relative to said first vehicle;

a closed loop servo-control circuit enabling said second inertial navigation unit to be provided at the instant it is put into operation with angle data delivered by said first inertial navigation unit relative to said first system of reference axes, said servo-control circuit then delivering rotation commands that are applied to said second inertial navigation unit for the purpose of refining its angular initialization;

subtracter means receiving velocity or acceleration data from said first and second inertial navigation units each of which units delivers said data parallel to two non-vertical axes in the corresponding ones of said first and second calculation reference axis systems, said subtracter means delivering velocity or acceleration difference data parallel to the two corresponding non-vertical axes of said first calculation reference axis system; and

a Kalman filter simultaneously receiving said rotation commands from said servo-control circuit and said velocity or acceleration difference data, and calculating estimates of the angle offsets of the axes of said second calculation reference system as corrected by the preceding servo-control relative to the corresponding axes of said first calculation reference axis system, said Kalman filter applying said estimates to said second inertial navigation unit after the servo-control performed by said servo-control circuit has finished and after the Kalman filter has itself converged.

2. A system according to claim 1, wherein said servo-control circuit slaves the angle data delivered by said second inertial navigation unit on the angle data delivered by said first inertial navigation unit.

3. A system according to claim 1, in which each of said first and second calculation reference axis systems includes a vertical axis, wherein said servo-control circuit slaves firstly the position of the vertical axis of said second calculation reference axis system on the position of the vertical axis of said first calculation reference axis system, and secondly the heading data delivered by said second inertial navigation unit on the heading data delivered by said first inertial navigation unit.

4. A system according to claim 1, including a supervisor associated with said Kalman filter.

5. A system according to claim 1, including calculation means between said first inertial navigation unit and said subtracter means, said calculation means serving to correct the velocity or acceleration error due to the lever arm between said first and second inertial navigation units.

6. A system according to claim 1, including second calculation means receiving the error estimates from the Kalman filter and changing the coordinates thereof to transform them from said first reference axis system to a third axis system tied to said first vehicle.

7. A system according to claim 6, including a memory for storing said error estimates after the change of coordinates.