抄録
This paper proposes a method to estimate all state variables of a space probe in a proximity to an asteroid with Wide Field Integration of optic flow. In authors' previous papers, it is assumed that a space probe has an altitude sensor. In this paper, the altitude is estimated from the velocity change between two states before and after thruster firing. For this altitude estimation process, the probe's attitude angle is required. Thus, this paper also addresses a method to evaluate the attitude angle accurately. To demonstrate the validity of the proposed method, a numerical simulation of a spacecraft with two control thrusters is shown.
