A pointing mechanism (110, 120) comprising: - a deployed boom (112, 122) having a rod shape; - a main body side gimbal (111, 121) configured to connect the deployed boom (112, 122) to a satellite main body and adjust a direction of the deployed boom (112, 122); and - a thruster side gimbal (113, 123) configured to connect the deployed boom (112, 122) to a thruster group (115, 125) comprising a thruster base (114, 124) and a plurality of thrusters, the thruster side gimbal (113, 123) being further configured to adjust a direction of the thruster base (114, 124), wherein the pointing mechanism (110, 120) is adapted to be mounted in a pair on an artificial satellite, each thruster side gimbal (113, 123) being configured to connect respectively to a first thruster group and to a second thruster group and wherein each of the main body side gimbal (111, 121) and the thruster side gimbal (113, 123) is a two-axis gimbal, wherein during orbit raising, when a first operation number which is the number of activated thrusters out of the first thruster group and a second operation number which is the number of activated thrusters out of the second thruster group are different from each other, the direction of the deployed boom to which the first thruster group is connected and the direction of the deployed boom to which the second thruster group is connected are adjusted, a satellite center of gravity, the first thruster group and the second thruster group are projected on a plane having the traveling direction as a normal line during orbit raising, and the satellite center of gravity, the first thruster group and the second thruster group are arranged on the same straight line, so that a ratio of a first distance from the satellite center of gravity to the first thruster group and a second distance from the satellite center of gravity to the second thruster group in the plane is an inverse ratio of the first operation number and the second operation number. - a deployed boom (112, 122) having a rod shape; - a main body side gimbal (111, 121) configured to connect the deployed boom (112, 122) to a satellite main body and adjust a direction of the deployed boom (112, 122); and - a thruster side gimbal (113, 123) configured to connect the deployed boom (112, 122) to a thruster group (115, 125) comprising a thruster base (114, 124) and a plurality of thrusters, the thruster side gimbal (113, 123) being further configured to adjust a direction of the thruster base (114, 124), wherein the pointing mechanism (110, 120) is adapted to be mounted in a pair on an artificial satellite, each thruster side gimbal (113, 123) being configured to connect respectively to a first thruster group and to a second thruster group and wherein each of the main body side gimbal (111, 121) and the thruster side gimbal (113, 123) is a two-axis gimbal, wherein during orbit raising, when a first operation number which is the number of activated thrusters out of the first thruster group and a second operation number which is the number of activated thrusters out of the second thruster group are different from each other, the direction of the deployed boom to which the first thruster group is connected and the direction of the deployed boom to which the second thruster group is connected are adjusted, a satellite center of gravity, the first thruster group and the second thruster group are projected on a plane having the traveling direction as a normal line during orbit raising, and the satellite center of gravity, the first thruster group and the second thruster group are arranged on the same straight line, so that a ratio of a first distance from the satellite center of gravity to the first thruster group and a second distance from the satellite center of gravity to the second thruster group in the plane is an inverse ratio of the first operation number and the second operation number.