The present disclosure relates to an axial flux motor comprising a stator and a rotor. The stator comprises a first motor coil, a second motor coil, a first hall sensor, and a second hall sensor, and the rotor comprises a rotor platform member, an actuator magnet array arranged in an alternating axial polarity arrangement, a trigger magnet array, and a rotating magnetic return path member.

An antenna system is configured for use in Low Earth Orbit (LEO) around Earth. The system has a plurality of antenna satellites coupled together to form a phased array. Each of the plurality of antenna satellites have an antenna body with an antenna and a solar cell. A processing device determines an orientation of the plurality of antenna satellites and position the phased array in the orientation based on an analysis of the solar cell of the antenna bodies facing the sun, the antenna of the antenna bodies facing the Earth, and maintaining a torque equilibrium of the phased array.

A modular and scalable system to transfer space articles between space orbits. In one embodiment, the system employs a rendezvous vehicle which docks with a space article in an initial orbit, the connected stack then docking with a locomotive vehicle which maneuvers to a targeted orbit where the space article is detached. In one feature, the rendezvous vehicle and locomotive vehicle use a common propellant and the space article is a satellite.

A control system for a momentum wheel device is specified, wherein the momentum wheel device is a real momentum wheel device (1) and has a momentum wheel which is driven by a motor, and wherein a simulated momentum wheel device (2) is provided which simulates the behaviour of an ideal momentum wheel on the basis of an ideal physical model (12). The rotational speed of both the real momentum wheel device (1) and of the simulated momentum wheel device (2) can be changed by a torque command (6). A comparator device (11) is provided for comparing the real rotational angle (9) of the real momentum wheel device (1) and the simulated rotational angle (14) of the simulated momentum wheel device (2) and for generating a fault signal (15) corresponding to a deviation between the real rotational angle (9) and the simulated rotational angle (14). The fault signal (15) can be conducted to a control device (3), in order to actuate the motor on the basis of the fault signal (15), for the purpose of reducing the deviation.

Disclosed are systems and method for satellite attitude control, which includes two or more individual thruster unit (ITU) arranged at various locations about a body of the satellite, with each ITU oriented to provide thrust in a unique direction when fired. Additionally or alternatively, each ITU configured for independently controlled firing. In disclosed examples, one or more stabilization surfaces to compensate for changes in altitude of the satellite.

A method for desaturating reaction wheels of a spacecraft having a magnetic dipole is provided. The method includes orienting the spacecraft relative to an external magnetic field to apply a torque to the spacecraft via the magnetic dipole in a direction opposing momentum stored in the reaction wheels; and using the applied torque to unload at least some of the momentum stored in the reaction wheels. A corresponding spacecraft and non-transitory computer-readable medium are also provided.

Systems and methods for describing, simulating and/or optimizing spaceborne systems and missions. Configurations for spaceborne systems are generated and validated based on simulation output.

Omni-directional, extensible grasp mechanisms are disclosed. Such grasp mechanisms may be used as a robotic end effector for docking, grasping, and manipulating space structures, or to interconnect other structures or vehicles. Novel interconnected lattice structures may enable large arrays to be assembled. The grasp mechanisms may be used to create structures from parallel docking linkages. This may enable reconfiguration of multiple docked space vehicles and/or structures without the use of propellant. The grasp mechanisms have the ability to make and break connections multiple times, enabling a nondestructive and reversible docking process.

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.

A spacecraft including a set of thrusters for changing a pose of the spacecraft. At least two thrusters mounted on a gimbaled boom assembly and are coupled together sharing the same gimbal angle. A model predictive controller (MPC) to produce a solution for controlling thrusters of the spacecraft by optimizing a cost function over a receding horizon using a model of dynamics of the spacecraft effecting a pose of the spacecraft and a model of dynamics of momentum exchange devices of the spacecraft effecting an orientation of the spacecraft. A modulator to modulate magnitudes of the thrust of the coupled thrusters determined by the MPC as pulse signals specifying ON and OFF states of each of the coupled thruster, wherein the ON states of the coupled thrusters sharing the same gimbal angle do not intersect in time. A thruster controller to operate the thrusters according to their corresponding pulse signals.