Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

The disclosure describes various aspects of a space-based radioisotope production system and methods use. In one aspect, a propellant is accelerated by decay energy to yield thrust. The decay energy is provided by activating a target material. In one aspect, a radioisotope rocket thruster may be recharged or “reactivated” in a space-borne charging station. The activated isotopes may also be used generate electricity. The space-borne charging station may also be used for irradiating other items in space for any number of purposes.

Systems and methods for refueling a chemical propulsion system are provided. The systems can include multiple pressurant reservoirs to supply pressure to one or more fuel tanks. During a refueling operation, pressurant is released, fuel is added to the fuel tank, and then the fuel tank is repressurized using pressurant from a secondary pressurant tank. In other configurations, during a refueling operation pressurant is cooled to depressurize the fuel tank, fuel is added to the fuel tank, and then the pressurant is heated to repressurize the fuel tank. The systems and methods can be used to refuel operationally deployed space craft.

Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

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 first spacecraft comprises a drive mechanism. A second spacecraft comprises a valve for filling/draining the second spacecraft. The coupling assembly comprises a first connector comprising an actuating member configured to engage and open the valve and a coupling member configured to couple to the drive mechanism. A second connector comprises a stop portion and a bore for transferring fluid. Operation of the drive mechanism rotates the coupling member and the second connector together to screw the second connector onto the valve until the stop portion engages the valve, the actuating member being prevented from moving relative to the second connector to open the valve whilst the lock is in the locked state. Once the stop portion engages the valve, operation of the drive mechanism to exert a torque on the coupling member greater than a predetermined torque level moves the lock to an unlocked state wherein the actuating member is moveable relative to the second connector to engage and open the valve.

A method for capturing and deorbiting space debris includes: providing a space debris capturing device; deploying the space debris capturing device in planetary orbit; determining, via an onboard global positioning system unit, the position and orbit velocity of the space debris capturing device; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device, the second database is smaller than the first database; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device, the third database is smaller than the second database; transferring the space debris capturing device to a position within a capture range of a first space debris target of the third database; capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; repeating the transferring, capturing, and jettisoning steps for all but a final one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

Systems and methods are provided for scheduling objects having pair-wise and cumulative constraints. The systems and methods presented can utilize a directed acyclic graph to increase or maximize a utilization function. The objects can comprise satellites in a constellation of satellites. In some implementations, the satellites are imaging satellites, and the systems and methods for scheduling can use human collaboration to determine events of interest for acquisition of images. In some implementations, dominant edges are removed from the directed acyclic graph. In some implementations, dynamic weights are assigned to nodes associated with downlink events in the directed acyclic graph.

A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises one or more electromagnets spaced apart and suspended on a frame that may include means for compensating for any out of plane misalignments during capture. The client spacecraft includes a striker plate that covers an area, nominally larger than the footprint of the capture mechanism, that is sized to accommodate a capture envelope determined by the rendezvous and proximity sensing systems. The electromagnets attract the striker plate to capture the client spacecraft in order to provide on-orbit servicing. The docking system has multiple degrees of freedom that are independent of the capture system; docking is accomplished by mechanically coupling the two spacecrafts together, post capture. During docking, electrical and fluid transfer connections may also be accomplished. The servicing spacecraft further comprises a manipulator arm that may be configured to position/align the captured client spacecraft for docking, thereby permitting a very flexible, larger, capture envelope, and reducing operational complexity.

A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises a plurality of capture arms attached to a grounding structure. In one embodiment, the capture arms are kinematically linked and are free to rotate with respect to the grounding structure using a single actuator, thereby synchronizing the rotation of the arms for any angular displacement of the actuator, thus the arms form a circle that is concentric with the boom axis. In a second embodiment, there are two sets of capture arms, with the arms in each set kinematically linked and independently actuated; thus, the two sets cooperatively form different grasping geometries. Further, the docking mechanism is configured to enable the host spacecraft to dock with the client spacecraft. The servicing spacecraft may also be configured to carry a robotic arm and a suite of end-effectors that can be automatically changed out on-orbit. The suite of end-effectors may include one configured with the disclosed capture mechanism, and another may be configured with the disclosed docking mechanism.