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precision landing

The proposed disturbance rejection optimal guidance method integrates two essential components: real-time nominal trajectory generation and robust neighboring optimal feedback control. These components enable two synergistic functions: adaptive optimal steering and disturbance attenuation. Adaptive optimal steering addresses modeled disturbances using an augmented dynamics model, while disturbance attenuation mitigates the effects of unmodeled disturbances on system state.

New Guidance System Makes Reusable Rockets Land with Greater Precision

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