| 摘要 |
A method and system for limiting missile guidance correction within the physical control capabilities of the missile, while fully utilizing missile maneuver and control capabilities. The method and system of the present invention are applied through missile guidance control electronics. First, a dynamic rate limit is calculated to prevent aerodynamic trim limit overshoot, which is directly related to body attitude rate. Second, a dynamic angle of attack limit is calculated to control aerodynamic trim limit based on thrust deflection and/or aerodynamic control surface deflection. Third, a dynamic angular acceleration limit is calculated to balance control moments produced by mechanisms such as thrust deflection and/or aerodynamic control surface deflection with vehicle moments of inertia. Fourth, the dynamic limit on rate of change of angular acceleration is set to maintain control system margins in terms of maximum enforceable moment in excess of the trim moment at the current angle of attack and maximum slew rate of the thrust deflector.
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