The theme is topical because of the ongoing Russian lunar program. Four more launches of Luna-25 to Luna-28 are planned for the next several years. Only in 8 out of 14 cases, the soft Moon landing was provided. This fact prompts researchers to seek after new ways of solving this problem. The article deals with a power-efficient control algorithm that controls landing engine thrust at the final phase of spacecraft landing from a given hovering point to the point of contact with the Moon’s surface. Initially not supposed to be used for solution of terminal control tasks, the power-efficient algorithm can be applied here, which can be explained by availability of an auxiliary system in it that provides reaching specified motion parameters within a specified period. At the final phase of soft Moon landing, the proposed algorithm treats the spacecraft as a material point that moves by the attractive force of the Moon and the opposite vertical force of the landing engine thrust. It is supposed that to form the thrust the vertical velocity is measured by a Doppler velocimeter and the altitude by a multibeam vertical-building radio altimeter, throughout the whole motion interval. W hen calculating the parameters of spacecraft motion under the conditions of the Moon’s gravitational field at the final phase of spacecraft contact with the Moon’s surface by the mentioned algorithm, there is a possibility of some overcorrection, which is inadmissible. To exclude it, a well-known approach is used when the motion is considered on the assumption of absence of the Moon’s gravitational field. In this case the control will be implemented without overcorrection, but to obtain the actual engine thrust it is necessary to add the force opposite to the direction of the Moon’s attraction force, acting upon the spacecraft, to the algorithm-generated signal at every control step. The author has mathematically modeled the algorithm. The results of modeling proved the appropriateness of the problem statement and allow finding the boundary of the algorithm applicability: to exclude reversing of the landing engine thrust the initial spacecraft hovering altitude should be less than 647 m. The algorithm can also be used for controlling automatic landing of vertical takeoff aircraft.