Use of iteration to improve the correction of AGC dependent channel-to-channel gain imbalance

• US 5,241,316 A
• Filed: 09/26/1991
• Issued: 08/31/1993
• Est. Priority Date: 09/26/1991
• Status: Expired due to Term

• Current Assignee: OL Security LLC (Intellectual Ventures LLC)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Pringle, Richard C.
• Primary Examiner(s): Sotomayor, John B.
• Application Number:
  US07/765,799
• Time in Patent Office: 705 Days
• Field of Search: 342/62, 342/92, 342/194, 342/151, 342/152, 342/174
• US Class Current: 342/62
• CPC Class Codes: G01S 7/34 Gain of receiver varied automatically during pulse-recurrence period, e.g. anti-clutter gain control
• CPC Class Codes: H03G 3/3036 in high-frequency amplifiers or in frequency-changers H03G3/3052, H03G3/32, H03G3/34 take precedence

Abstract

A method and apparatus that uses iteration to achieve a better prediction of the values of the commands needed to balance the gains of Σ+Δ and Σ-Δ channels of a radar guidance system, when an imbalance occurs due to a change caused by the AGC circuitry. An improved method of measuring channel-to-channel gain imbalance versus AGC measurements is provided, which produces modified input values that are used as commands that correct the mismatch during missile flight so that residual error is minimized and more accurate guidance is achieved. The present method is implemented by measuring the gain imbalance at predetermined AGC points during system calibration, and iterating these measurements to produce a relatively small channel-to-channel gain imbalance at the ΔAGC amplifiers. The measured imbalance is then converted to ΔAGC commands and applied to the ΔAGC amplifiers. The resulting gain imbalance is measured and this value is added to the originally measured value. This iterated value is again converted to ΔAGC commands and applied to the ΔAGC amplifiers, and again the imbalance is measured, and is added to the first measurement. This procedure is repeated until a satisfactory level of error is measured which produces the proper correction factor that balances the channel-to-channel gains for each value of AGC. These correction factors are stored in a lookup table and are subsequently applied to the missile during flight. The improved apparatus of the present invention comprises a ΔAGC controller containing a lookup table that contains the correction factors determined using the above method and an amplifier control circuit that responds to the correction factors to apply modified gain factors to the ΔAGC amplifiers. These correction factors are applied to the ΔAGC amplifiers during operation of the guidance system to achieve more accurate missile guidance.

Claims

1. In a radar guidance system for use in a missile, the radar guidance system having automatic gain control (AGC) circuitry that comprises a controller having a lookup table, and wherein the controller is coupled to controllable gain control amplifiers, a method of balancing the gains of Σ

+Δ and

Σ

-Δ

channels of the radar guidance system when an imbalance occurs due to a change caused by the controllable gain control amplifiers, said method comprising the steps of;

activating the missile and radar guidance system;

measuring the gain imbalance at predetermined AGC points during radar guidance system calibration subsequent to activation of the missile and providing a set of correction factors indicative thereof;

iterating the correction factors by applying the correction factors to the controllable amplifiers to determine a final set of correction factors that balances the Σ

+Δ and

Σ

-Δ

channels of the radar guidance system for each possible AGC value;

storing the final set of correction factors in the lookup table;

applying the final set of correction factors to the controllable amplifiers in response to changes in the AGC values to more accurately guide the missile.

2. In a radar guidance system for use in a missile, the radar guidance system having automatic gain control (AGC) circuitry that comprises a controller having a lookup table, and wherein the controller is coupled to controllable gain control amplifiers, a method of balancing the gains of Σ

+Δ and

Σ

-Δ

channels of the radar guidance system when an imbalance occurs due to a change caused by the controllable gain control amplifiers, and wherein the channel-to-channel gain correction provided to the controllable amplifiers substantially equals a desired value, said method comprising the steps of;

activating the missile and radar guidance system;

measuring the gain imbalance at a plurality of predetermined AGC points during radar guidance system calibration subsequent to activation of the missile and computing a set of correction factors indicative thereof;

iterating the correction factors by applying the correction factors to the controllable amplifiers a predetermined number of times to determine a final set of correction factors that balances the Σ

+Δ and

Σ

-Δ

channels of the radar guidance system for each possible AGC value;

storing the final set of correction factors in the lookup table;

applying the final set of correction factors to the controllable amplifiers in response to changes in the AGC values to more accurately guide the missile.

3. In a radar guidance system having automatic gain control (AGC) circuitry that comprises a controller having a lookup table, and wherein the controller is coupled to controllable amplifiers, a method of balancing the gains of Σ

+Δ and

Σ

-Δ

channels of the radar guidance system when an imbalance occurs due to a change caused by the AGC circuitry, said method comprising the steps of;

activating the missile and radar guidance system;

calibrating the system by measuring gain imbalance value between the Σ

+Δ and

Σ

-Δ

channels for a selected one of a plurality of predetermined AGC input values;

computing a gain correction factor for the selected predetermined AGC input value and applying the gain correction factor to the controllable amplifiers;

remeasuring the resulting gain imbalance value in response to the applied gain correction factor and adding this value to the previously measured gain correction factor;

repeating the computing and remeasuring steps for the selected AGC input value until a desired level of error is measured, thus providing a gain correction factor that balance the channel-to-channel gains for the selected AGC value; and

repeating the above calibrating, computing, and remeasuring steps for each AGC input value of the plurality of predetermined AGC input values to produce a final set of gain correction factors, and wherein the channel-to-channel gain correction provided by the controllable amplifiers in response to the final set of correction factors substantially balances the Σ

+Δ and

Σ

-Δ

channels of the radar guidance system;

storing the final set of correction factors in the lookup table; and

applying the final set of correction factors to the controllable amplifiers in response to changes in the AGC values during missile flight to more accurately guide the missile.