Attitude Control Loop Design of Missile With Front Lateral Thruster Using Dynamic Inversion and Greedy Algorithm

초록

In this paper, we design an attitude control loop for a missile with an impulse-type one-off front lateral thruster. This thruster is simpler and less expensive than a divert attitude control system (DACS) and has a faster response than aerodynamic control, especially at high altitude and low velocity. The proposed control loop utilizes the dynamic inversion technique to calculate the required pitching and yawing moment commands for attitude control. It then selects the proper amount of unexpired front lateral thrusters to fire for tracking the moment commands as closely as possible using front lateral thruster firing logic. However, errors are inevitable due to the discreteness of the impulse-type one-off front lateral thrusters. The performance of the proposed attitude control loop is analyzed through six-degrees-of-freedom equations of motion of a missile with various modeling parameters. © ICROS 2023.

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