This paper presents an optimum control scheme of firing time and firing phase angle by taking impact point deviation as optimum\nobjective function which takes account of the difference of longitudinal and horizontal correction efficiency, firing delay, roll rate,\nflight stability, and so forth. Simulations indicate that this control scheme can assure lateral impulse thrusters are activated at time\nand phase angle when the correction efficiency is higher. Further simulations show that the impact point dispersion is mainly\ninfluenced by the total impulse deployed, and the impulse, number, and firing interval need to be optimized to reduce the impact\npoint dispersion of rockets. Live firing experiments with two trajectory correction rockets indicate that the firing control scheme\nworks effectively.
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