Doppler heading attitude reference system

• US 4,070,674 A
• Filed: 10/15/1976
• Issued: 01/24/1978
• Est. Priority Date: 10/17/1973
• Status: Expired due to Term

• Current Assignee: Singer Company (SVP Holdings Ltd.)
• Original Assignee: Singer Company (SVP Holdings Ltd.)
• Inventors: Fiore, John M., Buell, Heinz
• Primary Examiner(s): Hubler, Malcolm F.
• Application Number:
  US05/732,574
• Time in Patent Office: 466 Days
• Field of Search: 343/9, 235/150.25
• US Class Current: 342/117
• CPC Class Codes: F41G 5/12 acoustically influenced
• CPC Class Codes: G01C 21/1652 with ranging devices, e.g. LIDAR or RADAR
• CPC Class Codes: G01S 13/86 Combinations of radar systems with non-radar systems, e.g. sonar, direction finder

Abstract

A doppler radar/inertial system is provided for producing navigational and fire control information for an aircraft, and which includes means for developing vertical reference signals accurately at one location and for then transferring the signals to a second location without incurring errors due to aircraft flexure. The system includes high quality accelerometers and gyroscopes mounted at one location in the aircraft for developing accurate vertical reference signals; and a high quality accelerometer and low cost gyroscope at a second location where accurate vertical reference information is required. The system includes circuitry for comparing the output of the high quality accelerometer at the second location with the accelerometer outputs at the first location, the difference of which is a function of the error in the vertical reference at the second location, as indicated by the low cost gyroscope. The system includes further circuitry which is responsive to the output differential of the accelerometers to correct the error in the reading of the low cost gyroscope at the second location.

Claims

1. A control system for use in an aircraft, or the like comprising:

an inertial heading reference unit mounted on the aircraft and including accelerometer means and associated circuit means for providing first acceleration signals in horizontal coordinates;

a controlled unit mounted on the aircraft remote from the inertial heading reference unit and including accelerometer means for producing second acceleration signals and vertical gyroscope means for producing pitch and roll signals;

transforming circuit means coupled to said controlled unit and responsive to said second acceleration signals and controlled by said pitch and roll signals for transforming said second acceleration signals into second accelerations signals in horizontal coordinates; and

computer means coupled to said heading reference unit and to said transforming circuit means for comparing the first and second acceleration signals in the horizontal coordinates to produce pitch and roll error signals to compensate for pitch and roll errors in said vertical gyroscope.

2. The system defined in claim 1 in which said transforming circuit means includes a train and elevation coordinate resolver and a coordinate pitch and roll resolver to obtain three components of acceleration in horizontal coordinates (A'"'"'_H, A'"'"'_D and A'"'"'_V);

and in which said circuitry associated with said heading reference unit transforms the outputs of the accelerometer means therein to obtain horizontal acceleration signals (A_H, A_D), and in which said computer means compares said acceleration signals (A'"'"'_H, A'"'"'_D) and (A_H, A_D) to produce said pitch and roll error signals.

3. The control system defined in claim 1 in which said inertial heading reference unit comprises a two-gimbal platform, and in which said associated circuitry includes circuitry to correct for tilt errors of the platform about the North axis.

4. The control system defined in claim 1 and which includes a stabilized platform mounted in the aircraft on which said inertial heading reference unit is mounted, and which includes a navigational doppler radar unit having an antenna element mounted on said platform.