Antenna stabilization error correction system for radar

• US 5,485,156 A
• Filed: 09/21/1994
• Issued: 01/16/1996
• Est. Priority Date: 09/21/1994
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Original Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Inventors: Weist, William C., Hermann, Phillip R., Manseur, Arezki, Brandao, Ruy L.
• Primary Examiner(s): Lobo, Ian J.
• Application Number:
  US08/310,117
• Time in Patent Office: 482 Days
• Field of Search: 342/77, 342/75, 343/757
• US Class Current: 342/77
• CPC Class Codes: G01S 13/86 Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
• CPC Class Codes: G01S 13/87 Combinations of radar systems, e.g. primary radar and secondary radar
• CPC Class Codes: G01S 7/02 of systems according to group G01S13/00
• CPC Class Codes: G01S 7/4026 Antenna boresight
• CPC Class Codes: G01S 7/403 in azimuth, i.e. in the horizontal plane
• CPC Class Codes: G01S 7/4034 in elevation, i.e. in the vertical plane
• CPC Class Codes: H01Q 1/18 Means for stabilising antennas on an unstable platform

Abstract

A radar utilizes an antenna stabilization error correction system to automatically estimate and correct attitude sensor errors in pitch, roll and elevation. The radar system includes an antenna, an antenna positioner, a transmitter receiver, a signal processor, an antenna controller and stabilization processor and the antenna stabilization error correction system. As part of the normal signal processor sub function, ground clutter signals are extracted from the received signals. These signals are the primary input to the antenna stabilization error correction system. Other inputs are received from the signal processor, antenna controller and stabilization processor and an external aircraft radio altimeter. The antenna stabilization error correction system processes the signals and estimates pitch, roll and elevation errors which are passed back to the antenna controller and stabilization processor.

Claims

1. A radar system comprising:

antenna controller and stabilization processor means connected to an aircraft attitude sensor;

antenna positioner means connected to said antenna controller and stabilization processor means;

antenna means connected to said antenna positioner means for transmitting signals, for receiving signals and for receiving ground clutter;

transmitter/receiver means connected to said antenna means;

signal processor means connected to said transmitter/receiver means, said antenna controller and stabilization processor means and an aircraft radio altimeter;

antenna stabilization error correction system connected to said signal processor means, said antenna controller and stabilization processor means and said aircraft radio altimeter means, wherein said antenna stabilization error correction system estimates pitch, roll and elevation errors and transmits corrected signals to said antenna controller and stabilization processor means;

said antenna stabilization error correction system includes compute incremental component means for computing .increment.Pe, .increment.R, .increment.Ee and .increment.T, wherein Pe is pitch error, Re is roll error, Ee is elevational error and T is time, compute slew rate limit means connected to said compute incremental component means, integrate means connected to said compute slew rate limit means for integrating .increment.Pe, .increment.Re, .increment.Ee and for providing Pe, Re, Ee, and magnitude limit means connected to said integrate means; and

said signal processor means extracting ground clutter signals from signals received from said transmitter/receiver means and sending said ground clutter signals to said antenna stabilization error correction system.

2. A radar system as claimed in claim 1 wherein said antenna controller and stabilization processor means provides closed loop drive signals to said antenna positioner means and said closed loop drive signals maintain azimuth and elevation positions of said antenna means that are consistent with desired azimuth and elevation positions computed from inputs to said antenna controller and stabilization processor means.

3. A radar system as claimed in claim 2 wherein said inputs to said antenna controller and stabilization processor means are command tilt angle from said signal processor means, pitch and roll from said aircraft attitude sensor and pitch, roll and elevation errors generated by said antenna stabilization error correction system.

4. A radar system as claimed in claim 3 wherein said antenna positioner means mechanically positions beam axis of said antenna means.

5. A radar system as claimed in claim 4 wherein said antenna means couples electromagnetic energy from said transmitter/receiver means to and from an observed object.

6. A radar system comprising:

antenna controller and stabilization processor means connected to an aircraft attitude sensor;

antenna positioner means connected to said antenna controller and stabilization processor means;

antenna means connected to said antenna positioner means for transmitting signals, for receiving signals and for receiving ground clutter;

transmitter/receiver means connected to said antenna means;

signal processor means connected to said transmitter/receiver means, said antenna controller and stabilization processor means and an aircraft radio altimeter; and

,

antenna stabilization error correction system connected to said signal processor means, said antenna controller and stabilization processor means and said aircraft radio altimeter means, wherein said signal processor means extracts ground clutter signals from signals received from said transmitter/receiver means and sends said ground clutter signals to said antenna stabilization error correction system and wherein said antenna stabilization error correction system estimates stabilization error, Θ

e, wherein ##EQU3## where N is number of qualified clutter patches;

where Z is aircraft altitude;

where R_i is slant range to clutter patch i;

where K is dependent upon said antenna means specific to said radar system application;

where .increment.dB_i is estimated clutter power changes in a particular clutter patch i;

where .increment.Θ

ct is a small perturbation in antenna tilt; and

,

where Θ

ct is average commanded tilt angle about which tilt angle is perturbed.

7. A radar system as claimed in claim 6 wherein said antenna stabilization error correction system comprises:

compute incremental component means for computing .increment.Pe, .increment.Re, .increment.Ee, and .increment.T, wherein Pe is pitch error, Re is roll error, Ee is elevation error and T is time;

computer slew rate limit means connected to said compute incremental component means;

integrate means connected to said compute slew rate limit means for integrating .increment.Pe, .increment.Re, .increment.Ee, and for providing Pe, Re and Ee; and

magnitude limit means connected to said integrate means.

8. A radar system comprising:

antenna controller and stabilization processor means connected to an aircraft attitude sensor;

antenna positioner means connected to said antenna controller and stabilization processor means;

antenna means connected to said antenna positioner means for transmitting signals, for receiving signals and for receiving ground clutter;

transmitter/receiver means connected to said antenna means;

signal processor means connected to said transmitter/receiver means, said antenna controller and stabilization processor means and an aircraft radio altimeter;

antenna stabilization error correction system connected to said signal processor means, said antenna controller and stabilization processor means and said aircraft radio altimeter means, wherein said antenna stabilization error correction system estimates pitch, roll and elevation errors and transmits corrected signals to said antenna controller and stabilization processor means;

said antenna stabilization error system estimates stabilization error, Θ

e, wherein ##EQU4## Where N is number of qualified clutter patches;

where Z is aircraft altitude;

where R_i is slant range to clutter patch i;

where K is dependent upon said antenna means specific to said radar system application;

where .increment.dB_i is estimated clutter power changes in a particular clutter patch i;

where .increment.Θ

ct is a small perturbation in antenna tilt; and

,

where Θ

ct is average commanded tilt angle about which tilt angle is perturbed.