SPACECRAFT AND CONTROL DEVICE

A spacecraft, provided with: an engine; a thrust direction control device for controlling the thrust direction, which is the direction of thrust acting on the spacecraft; and a main control device for acquiring a state quantity for the spacecraft during powered descent in which the spacecraft is guided while thrust is generated by the engine and the spacecraft is guided to a target point, and generating an operation signal for operating the thrust direction control device and a combustion control signal for controlling the combustion of the engine in accordance with the acquired state quantity. The acquired state quantity includes a first acceleration parameter and a second acceleration parameter. The first acceleration parameter and the second acceleration parameter are respectively calculated as coefficients A, B, obtained by fitting based on the acceleration of the spacecraft detected at times in the past, assuming that the relationship 1/a = -At + B holds true between the reciprocal 1/a of the acceleration of the spacecraft and time t. The present invention provides a feature for appropriately responding to errors to accurately guide a spacecraft to a desired target point.