High accuracy bank-to-turn autopilot

• US 5,062,583 A
• Filed: 02/16/1990
• Issued: 11/05/1991
• Est. Priority Date: 02/16/1990
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Martin Marietta Corporation
• Inventors: Wood, Stephen D., Lipps, Gary D.
• Primary Examiner(s): Cangialosi, Salvatore
• Application Number:
  US07/480,976
• Time in Patent Office: 627 Days
• Field of Search: 364/433, 364/434, 364/435, 244/3.16, 244/3.15, 244/3.20, 244/3.21
• US Class Current: 244/3.15
• CPC Class Codes: F41G 7/20 based on continuous observation of target position
• CPC Class Codes: F41G 7/22 Homing guidance systems
• CPC Class Codes: G05D 1/12 Target-seeking control

Abstract

In a bank-to-turn autopilot, increased accuracy and insensitivity to tracking noise and glint are achieved by using a yaw LOS rate to drive the roll rate loop and by sending only a body coordinate pitch LOS rate to a pitch channel so as to not introduce errors in the cross plane. By uncoupling the pitch and roll loops, pitch/yaw/roll coupling, large roll transients, and cross plane maneuvers can be minimized. Additionally, body LOS rates are transformed to inertial LOS rates and subsequently back to body LOS rates such that guidance filtering may be performed in a non-rolling frame of reference. This allows the guidance filtering to be separately optimized without regard to destabilizing effects of such filtering due to roll-to-yaw coupling path lags. In other words, servo dynamic path lags are reduced since the guidance filters do not have to track the high frequency roll rates. They only need to process a slowly varying inertial pitch and yaw rates which are then mathematically resolved back to body coordinates. Thus heavier filtering may be performed by the guidance filters while maintaining the same phase margin obtainable using simpler guidance filters in a rolling reference frame. Finally, a minimum-roll implementation is obtained by correcting the sign of the roll rate command with the pitch acceleration command. Roll is thereby constrained within ±90° as opposed to ±180° otherwise.

Claims

1. A method of controlling a guided weapon comprising the steps of:

determining a line-of-sight rotation rate between said guided weapon and a target in terms of first body pitch and yaw components relative to a body of said guided weapon;

transforming said pitch and yaw components into inertial pitch and yaw components relative to an inertial reference frame

filtering said inertial pitch and yaw components;

transforming said inertial pitch and yaw components, after said filtering, back into second body pitch and yaw components; and

commanding a pitch control channel with said second body pitch component and commanding a roll control channel with said second body yaw component.

2. The method of claim 1 wherein the magnitudes of signals in the pitch control channel and the roll control channel are independent of one another.

3. The method of claim 1 wherein the signs of signals in the pitch control channel and the roll control channel are interdependent.

4. The method of claim 3 wherein the sign of a signal in the roll control channel is dependent on the sign of a signal in the pitch control channel.

5. The method of claim 4 further comprising the step of applying a gravity bias to said control channels.

6. The method of claim 5 wherein said gravity bias is roll-resolved so as to be effective in an inertially upward direction regardless of a roll attitude of said guided weapon.

7. A bank-to-turn guided weapon control system comprising:

line-of-sight rate determining means for determining a line-of-sight rate between said guided weapon and a target;

a roll command channel; and

means for coupling only a yaw rate portion of an output of said line-of-sight rate determining means to said roll command channel.

8. The guided weapon control system of claim 7 further comprising:

line-of-sight rate transformation means connected to said line-of-sight rate determining means for performing a transformation on said line-of-sight rate;

guidance filter means connected to said line-of-sight rate transformation means for filtering said line-of-sight rate according to a guidance algorithm; and

line-of-sight rate inverse transformation means connected to said guidance filter means and said means for performing an inverse transformation on said line-of-sight rate.

9. The guided weapon control system of claim 7 further comprising a pitch command channel and wherein said roll command channel includes sign determining means responsive to a sign of a signal in said pitch command channel for controlling the polarity of a signal in said roll command channel.

10. The guided weapon control system of claim 9 further comprising gravity bias means for counteracting gravitational effects on said guided weapon and wherein said roll and pitch command channels each include summing means connected to said gravity bias means for summing a signal from said gravity bias means into a respective one of said channels.

11. The guided weapon control system of claim 10 wherein said gravity bias means is roll resolved so as to be effective in an inertially upward direction regardless of a roll attitude of said guided weapon.

12. The guided weapon of claim 11 wherein said guidance algorithm implements proportional navigational guidance.

13. A bank-to-turn guided weapon, comprising

a pitch control surface for changing a pitch attitude of said guided weapon;

a roll control surface for changing a roll attitude of said guided weapon; and

a bank-to-turn autopilot for changing a yaw attitude of said guided weapon through a combination of changes in said pitch attitude and said roll attitude, said bank-to-turn autopilot comprising yaw rate determining means and pitch rate determining means and a roll command channel, said yaw rate determining means commanding said roll command channel exclusive of any contribution in magnitude from said pitch determining means.