Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual cells, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or rolling along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

According to an aspect of the present invention, there is provided a method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. According to another aspect of the present invention, there is provided system for rendezvous with an orbiting object comprising: a first spacecraft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.

Embodiments of the present disclosure disclose a docking apparatus, a mobile robot, and a docking method for the docking apparatus. The docking apparatus comprises a processor and a plurality of photosensitive devices electrically connected to the processor, wherein the processor determines, from the plurality of photosensitive devices, a photosensitive device receiving a laser light, the laser light being emitted by an opposite-end apparatus to be docked with the docking apparatus. The connection apparatus, according to a position offset between the photosensitive device receiving the laser light and a target photosensitive device, is controlled to move to a docking position calibrated by means of the target photosensitive device, such that the docking apparatus and the opposite-end apparatus are docked with each other. The embodiments help improve the accuracy of docking between the connection apparatus and the opposite-end apparatus.

Exemplary embodiments provided herein include connection systems in which a gripper is actuated through introduction of a material to an interior cavity. Embodiments may include more than one cavity such that deployment and actuation may be separately controlled. Additional cavities may also be used and/or selection of valves between cavities such that actuation and/or deployment may further be controlled.

Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for passively engaging with and securing the target vehicle.

Material transfer interfaces for space vehicles, and associated systems and methods, are disclosed. A representative system includes a coupling mechanism including a support structure, a latch-arm base movably connected to the support structure, and a latch arm pivotably connected to the latch-arm base. Another representative system includes a service valve portion, a coupling portion configured to receive the service valve portion, and a coupling mechanism for coupling the service valve portion to the coupling portion. The coupling mechanism can include latch arms positioned to pivot between a position in which the latch arms are pivoted outwardly and a position in which the latch arms are pivoted inwardly to capture the service valve portion. The latch arm can be carried by a latch-arm base that translates relative to a support structure of the coupling portion. Material transfer interfaces can include self-aligning ports having faces that engage each other with cup-and-cone structures.

Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing device may include a thruster assembly coupled to a boom arm, where the boom arm is configured to alter an orientation of the thruster assembly as the boom arm is rotated about the spacecraft body and a docking device.

A dimpled spherical storage unit is described in the form of a cargo ball. The cargo ball includes a spherical exterior surface and a plurality of dimples in a pattern on the exterior surface. At least a first cover is configured to extend outward from the center of the cargo ball and at least a first thruster is configured to be deployed from the cargo ball.

A docking system for use with in-space structures includes a first connector attached to a first in-space structure. The first connector includes a first housing defining a central axis and an engagement mechanism positioned within the first housing. The engagement mechanism is movable relative to the first housing. The docking system further includes a second connector attached to a second in-space structure. The second connector includes a second housing including a base and a connection member. The engagement mechanism is operable to engage the connection member. The connection member is fixed in position on the second in-space structure and does not move relative to the second in-space structure when the engagement mechanism engages the connection member.

Spacecraft servicing devices and related methods may include a propellant tank configured to store a propellant and to be placed into fluid communication with a portion of the target spacecraft.