A propulsion method includes: providing a pair of synchronized rotors rotatably mounted on a frame with a bearing having a bearing outer race, bearing balls, and bearing inner race; providing a plurality of permanent magnets mounted on the pair of synchronized rotors; rotating the pair of synchronized rotors such that one of the pair of synchronized rotors rotates in a clockwise direction and the other of the pair of synchronized rotors rotates in a counterclockwise direction; loading an outer portion of the outer bearing race, bearing ball, and inner bearing race of each of the bearings, a load on the outer portion of the bearings corresponding to an attractive force between the permanent magnets of the pair of synchronized rotors. A thrust is imparted on the frame in a direction corresponding to a direction of loading of the inner bearing race.

Provided are an artificial satellite and a method of controlling the same. The artificial satellite includes a main body flying along an orbit of a planet, an optical payload arranged on the main body to photograph a ground surface of the planet, and a pair of solar cell panels rotatably arranged on both sides of the main body in a first direction, wherein the first direction and a flight direction of the main body form an acute angle with each other.

Cell-based space systems with nested-ring structures that interlock and can change configuration to support a mission are provided. The cells may self-assemble into a larger structure to carry out a mission. Multiple rotatable rings may be included in a cell, with a payload/control section in the center. The rings may provide power and/or data to trams that move about the rails. Trams may interlock with other cells, carry sensors or other devices, etc. Cells may be stowed in a cell stack that is deployable. Such cell-based systems may have various applications in space, on Earth, other celestial bodies, and underwater.

A service satellite having a body, a controller and a docking unit including a telescopic arm, mounted on a 6-DOF parallel manipulator, and two additional gripping arms. The telescopic arm, deployed from the 6-DOF manipulator, is equipped with a pair of rapid closure digits. The telescopic arm facilitates capturing the launch adaptor ring of a client spacecraft, even during tumbling. The 6-DOF parallel manipulator has force sensors and can accommodate post capturing relative motion through active compliance control and controlled de-tumbling, for avoiding generation of high forces in the telescopic arm. After relative rate annihilation, the telescopic arm retracts and the client ring is secured to the 6-DOF manipulator with the help of a pair of clamps. After the ring is secured, two additional gripping arms secure a rigid connection with the launcher ring so that the docking connection comprises three equally spaced connections.

A control system for a spacecraft for determining a resultant torque that is exerted upon a spacecraft by one or more magnetic torque rods is disclosed. The spacecraft is configured to revolve around a celestial body in an orbit. A magnetic field of the celestial body is predictable, and a direction of the magnetic field located around the orbit is fixed. The control system includes the one or more magnetic torque rods, one or more processors in electronic communication with the one or more magnetic torque rods, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the one or more magnetic torque rods to exert the resultant torque upon the spacecraft.

A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom is provided. Power transmitters can be coordinated as a phased array and the power generated by the phased array is transmitted to one or more power receivers to achieve remote wireless power generation and delivery. In many embodiments, a reference signal is distributed within the space-based solar power station to coordinate the phased array. In several embodiments, determinations of the relative locations of the antennas in the array are utilized to evaluate the phase shift and/or amplitude modulation to apply the reference signal at each power transmitter.

A reaction wheel detects an angular momentum. A satellite controller selects a target thruster based on the detected angular momentum. A power supply apparatus changes adjustment electric power for the target thruster. A flow rate adjustment apparatus supplies a propellant to the target thruster at a flow rate corresponding to the adjustment electric power. This changes a thrust of the target thruster. When a discharge current of the target thruster does not become a target current, the power supply apparatus further changes the adjustment electric power for the target thruster.

This disclosure relates to a satellite attitude control apparatus, comprising a spherical inertial body (1), which is arranged to be rotated in space in a desired rotational mode, one or more rotational feedback sensors. The apparatus further comprises a set of supports (3) and/or actuators (2), whereas one or more actuator is used to create rotational momentum to the spherical inertial body through friction. A set of three or more actuators and supports is used in order to keep the inertial body in place. Three or more supporting elements (supports and actuators) are used in combination with magnetic attraction or four or more supporting elements are used in case magnetic attraction is not in use. Supports can be passive or semi-active in order to reduce friction.

Provided is a reaction wheel assembly ruggedized for use in kinetically launched satellites. An example reaction wheel assembly may include a shaft mounted to a body of a satellite, a wheel mounted to the shaft, wherein a center of a gravity of the wheel is co-aligned with the shaft, and a support device mounted to the body of the satellite. The reaction wheel assembly may include bearings for holding the shaft to the body of the satellite and allowing a rotation of the wheel. The support device can be engaged to support the wheel to reduce a load on the shaft and the bearing, the load being caused by an acceleration of the satellite during a kinetic launch of the satellite. After the satellite is launched into space, the support device can be disengaged from supporting the wheel to allow the wheel to spin.

An attitude control apparatus (20) includes an ideal thrust direction calculator (22), an ideal attitude calculator (24), a target attitude calculator (26), and a torque calculator (28). The ideal thrust direction calculator (22) calculates an ideal thrust direction of a thruster. The target attitude calculator (26) calculates a target attitude that is the attitude of a satellite in which a deviation from an ideal attitude is minimized within a movement limitation of an attitude control actuator (14) while a panel surface faces the sun. The torque calculator (28) calculates a torque for turning the satellite from an actual attitude to the target attitude and transmits a torque instruction to the attitude control actuator (14).