Methods, apparatus, and articles of manufacture to minimize command dynamics of a satellite are disclosed. An example apparatus includes a steering law module to calculate a first set of vectors to maneuver a space vehicle, and calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane. The apparatus further includes an attitude controller to generate an attitude command based on the first and the second sets of vectors to prevent an unplanned rotation by the space vehicle.

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.

Systems and methods disclosed provide for attitude control of a body, the body including a plurality of thrusters and a plurality of gimballed rotors. Operations performed include: receiving a command vector representing a desired torque on the body, generating a Jacobian matrix that, when applied to a combined gimbal rate and thrust command vector, generates the command vector, generating components of a weighted pseudo inverse of the Jacobian matrix and using the components with the command vector in order to generate the combined gimbal rate and thrust command vector. Generating components of the weighted pseudo inverse of the Jacobian matrix can include generating a weighting matrix including a plurality of diagonal elements, the plurality of diagonal elements representing at least the plurality of gimballed rotors and the plurality of thrusters.

An attitude determination and control system (ADCS) may include relatively large momentum wheels (i.e., reaction wheels) for improved momentum storage and magnetic torque rods that enable low power sun pointing and dissipate angular momentum imparted during deployment or by differential drag on the space vehicle. The momentum wheels, magnetic torque rods, or both may be algorithmically selected and driven to perform various maneuvers.

A gyroscopic module comprises at least one gyroscopic rotor rotatably mounted to a support, wherein the at least one gyroscopic rotor is driven by at least one first power source and at least one gimbal frame is coupled to the support of the at least one gyroscopic rotor. The gyroscopic module comprises at least one slew bearing coupled to the at least one gimbal frame to change an orientation of the at least one gyroscopic rotor, wherein the at least one slew bearing is driven by at least one second power source mounted to the at least one gimbal frame.

Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.

Embodiments of three parameter isolators including rolling seal damper assemblies are provided. In one embodiment, the three parameter isolator includes first and second isolator end portions, which are opposed along a working axis. A main spring and a tuning spring are mechanically coupled in parallel between the first and second isolator end portions. A rolling seal damper assembly is further mechanically coupled between the first and second isolator end portions in parallel with the main spring and in series with the tuning spring. The rolling seal damper assembly includes a first hydraulic chamber, a second hydraulic chamber fluidly coupled to the first hydraulic chamber, and first and second rolling diaphragm seals partially bounding the first and second hydraulic chambers, respectively. In certain implementations, the rolling seal damper assembly also contains a thermal compensator piston to which the first rolling diaphragm seal is attached.

A satellite propelled by laser ablation comprises: a device for managing the attitude and the orbit of the satellite; a device for capturing and potentially for processing the target spaceborne body; a device for external communication; a laser ablation propulsion device comprising one or more lasers and a module for managing the one or more lasers that is suitable for determining the one or more laser beams to be generated on the captured target spaceborne body according to the movement desired for the satellite; and a device for visually inspecting the target spaceborne body.

Embodiments of three parameter isolators including rolling seal damper assemblies are provided. In one embodiment, the three parameter isolator includes first and second isolator end portions, which are opposed along a working axis. A main spring and a tuning spring are mechanically coupled in parallel between the first and second isolator end portions. A rolling seal damper assembly is further mechanically coupled between the first and second isolator end portions in parallel with the main spring and in series with the tuning spring. The rolling seal damper assembly includes a first hydraulic chamber, a second hydraulic chamber fluidly coupled to the first hydraulic chamber, and first and second rolling diaphragm seals partially bounding the first and second hydraulic chambers, respectively. In certain implementations, the rolling seal damper assembly also contains a thermal compensator piston to which the first rolling diaphragm seal is attached.

An inertial actuation magnetohydrodynamic wheel (2) comprising a torus-shaped fluid ring (3) filled with a conductive liquid, at least one effective area (24, 26, 28) for setting the liquid into motion, and at least one magnetohydrodynamic pump (4, 6, 8). The ratio of the set back distance of any magnetic conduction element (24, 26, 28) of the air gap of any electromagnetic pump (4, 6, 8) over the internal size of the fluid ring (3) is greater than or equal to 0.5 and the fluid ring (3) comprises at least two distinct effective areas (24, 26), for setting the conductive liquid into motion, angularly spaced apart by at least 120.