Abstract: A cable (130) includes an electrical wire band (134). A parallel electrical wire (133) is formed by arranging a pair of a first electrical wire (131) and a second electrical wire (132) without being twisted together. The electrical wire band is formed by arranging a plurality of parallel electrical wires in a lateral row. In addition, between two adjacent parallel electrical wires, a second electrical wire of one parallel electrical wire is arranged adjacently to a first electrical wire of the other parallel electrical wire. Further, the electrical wire band is wound and accommodated in a spiral spring shape in a cable wrap mechanism (100).

Abstract: A first deployment mechanism (30) deploys a first radiator panel (20) from a state where the first radiator panel (20) is opposed to a north or south face (10) of the body structure of a satellite. A second radiator panel (40) is stacked with the first radiator panel (20) to be opposed to the north or south face (10) of the body structure of the satellite and is sandwiched between the north and south face (10) of the body structure of the satellite and the first radiator panel (20), in a state where the first radiator panel (20) is opposed to the north or south face (10) of the body structure of the satellite. A second deployment mechanism (50) connects the second radiator panel (40) to the north or south face (10) of the body structure of the satellite, and deploys the second radiator panel (40) in a direction P2 opposite to a deployment direction P1 of the first radiator panel from a state where the second radiator panel (40) is opposed to the north or south face (10) of the body structure of the satellite.

Abstract: An artificial satellite includes two pointing mechanisms. The pointing mechanisms respectively include main body side gimbals, deployed booms, thruster side gimbals, and thruster groups. The main body side gimbal connects the deployed boom to a satellite main body and adjusts a direction of the deployed boom. The thruster side gimbal connects the thruster to the deployed boom and adjusts the direction of the thruster. Each gimbal is a two-axis gimbal.

Abstract: An artificial satellite includes two pointing mechanisms. The pointing mechanisms respectively include main body side gimbals, deployed booms, thruster side gimbals, and thruster groups. The main body side gimbal connects the deployed boom to a satellite main body and adjusts a direction of the deployed boom. The thruster side gimbal connects the thruster to the deployed boom and adjusts the direction of the thruster. Each gimbal is a two-axis gimbal.

Abstract: A cable (130) includes an electrical wire band (134). A parallel electrical wire (133) is formed by arranging a pair of a first electrical wire (131) and a second electrical wire (132) without being twisted together. The electrical wire band is formed by arranging a plurality of parallel electrical wires in a lateral row. In addition, between two adjacent parallel electrical wires, a second electrical wire of one parallel electrical wire is arranged adjacently to a first electrical wire of the other parallel electrical wire. Further, the electrical wire band is wound and accommodated in a spiral spring shape in a cable wrap mechanism (100).

Abstract: A first deployment mechanism (30) deploys a first radiator panel (20) from a state where the first radiator panel (20) is opposed to a north or south face (10) of the body structure of a satellite. A second radiator panel (40) is stacked with the first radiator panel (20) to be opposed to the north or south face (10) of the body structure of the satellite and is sandwiched between the north and south face (10) of the body structure of the satellite and the first radiator panel (20), in a state where the first radiator panel (20) is opposed to the north or south face (10) of the body structure of the satellite. A second deployment mechanism (50) connects the second radiator panel (40) to the north or south face (10) of the body structure of the satellite, and deploys the second radiator panel (40) in a direction P2 opposite to a deployment direction P1 of the first radiator panel from a state where the second radiator panel (40) is opposed to the north or south face (10) of the body structure of the satellite.

Abstract: When a first operating number being the number of thrusters in a first thruster group (115) that are operated and a second operating number being the number of thrusters in a second thruster group (125) that are operated are different, a ratio between a first distance D1 in a +Y direction from a satellite gravity center (101) to the first thruster group and a second distance D2 in a ?Y direction from the satellite gravity center to the second thruster group becomes inverse to a ratio between the first operating number and the second operating number.

Abstract: An artificial satellite (100) includes two pointing mechanisms (110, 120). The pointing mechanisms respectively include main body side gimbals (111, 121), deployed booms (112, 122), thruster side gimbals (113, 114), and thruster groups (115, 125). The main body side gimbal connects the deployed boom to a satellite main body (130) and adjusts a direction of the deployed boom. The thruster side gimbal connects the thruster to the deployed boom and adjusts the direction of the thruster. Each gimbal is a two-axis gimbal.

Abstract: A heat source system control device controls a heat source system and has a plurality of heat source units with capacities and/or the load characteristics that are different, a first header which aggregates hot/cold water supplied from the plurality of heat source units, and a header temperature sensor which measures the temperature of the hot/cold water aggregated by the first header. The heat source system control device includes a set temperature memory section storing a set temperature of the hot/cold water in the header, a header temperature detecting section detecting output values from the header temperature sensor, a coefficient of performance memory section storing coefficient of performance information, and a control section performing a control for improving efficiency on the plurality of heat source units based on the respective capacities and/or load characteristics and bringing the temperature of the hot/cold water close to the set temperature.