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.

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.

A fluid transfer interface is provided. The fluid transfer interface includes one or more of first and second interface portions. The first interface portion includes a first portion of a fluid connector and one or more ferromagnetic surfaces. The second interface portion includes an extendable second portion of the fluid connector and one or more electropermanent magnets, laterally disposed around the second portion of the fluid connector, configured to be magnetized or demagnetized in unison. The one or more electropermanent magnets are further configured to provide attraction force to the one or more ferromagnetic surfaces when magnetized and couple the first interface portion to the second interface portion and provide no attraction force to the one or more ferromagnetic surfaces when demagnetized and allow the first interface portion to be decoupled from the second interface portion.

A combined launch vehicle and satellite system relates to the satellite combined with the launch vehicle's upper stage to provide a more efficient system that includes tank separation technology which allows the satellite system to shed tanks that have used up all the propellants stored therein. The method separation of the tank set is enabled by using a merman band or pneumatic type of separation system; wherein the three bottom tanks are emptied first during the process, followed by the separation of the emptied tanks herein the fuel is completely filled in the second set of tanks. The first pair of tanks is then separated after the fuel is emptied. Similarly, the plumbing lines are also separated. The separation of the used components is achieved herein and the satellite is ready for orbit insertion.

The instant application describes improvements to application Ser. Nos. 18/262,667 and 19/255,877. These improvements include advancements in internal small pipe geometry, the inclusion of hydrophilic surface coatings to all forms of the invention, and improvements in complex internal tunnel geometry. Additional iterations of the inventions include spaceship-based, dirigible-based, and elevation-based systems. Practical application models for real world deployment are also discussed as are possible installations for educational purposes.

A system for managing propellant and pressurant for in-space propulsion of a spacecraft is provided. The system includes a conformal fuel tank having an ullage operatively connected for pressurization and a propellant management device (PMD) to wick propellant to a liquid port of the conformal fuel tank. The system further includes a pneumatic circuit including a tank pressurant vent valve for adjustment of operating pressure prior to refueling operations; a vent to release excess pressurant; a pressurant metering vent valve to provide control and safety relief for the pressurant; a check valve to prevent backflow; a pressurant cat bed for decomposing propellant into pressurant; a repressurizing valve to release pressurant once cooled; a burst disk to provide overpressure safety relief; a series of propellant extraction valves to intake a predetermined quantity of propellant for decomposition; and a pressure regulator that delivers proper pressure to a series of thrusters.

A pressurization method for increasing a pressure within a propellant tank containing hydrogen peroxide H.sub.2O.sub.2. The pressurization method includes irradiating at least some of the hydrogen peroxide H.sub.2O.sub.2 with ultraviolet light emitted by at least one ultraviolet light source. With the UV light, a photolysis is actively provoked which causes the irradiated hydrogen peroxide H.sub.2O.sub.2 to at least partially decompose into water H.sub.2O and gaseous oxygen O.sub.2. Also a filling method for at least partially filling a receiving propellant tank with the pressurization method, a tank assembly, a filling system, and a spacecraft.

To facilitate on-orbit servicing, such as for a refueling operation, techniques are presented for a servicing satellite to cut through the multi-layer insulation blanket of a client satellite to provide access to the client satellite without releasing unacceptable quantities of foreign object debris from the multi-layer insulation. The serving satellite includes a sealing tool, such as a pair of heater rollers, that apply pressure and heat to the insulating blanket to melt the inner layers and seal the outer layers together. The servicing satellite can then use a cutting tool to cut the sealed region and access the client satellite.

A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.

A satellite refueling system has a refueling satellite carrying fuel, a fuel hose connected to the fuel carried by the refueling satellite, with a maneuverable end effector at a deployed end of the fuel hose, the end effector comprising a fuel supply nozzle connected to the fuel hose, a plurality of thrusters on the end effector providing thrust in a plurality of directions, an imaging device on the end effector capturing images in an immediate environment of the end effector, and computerized circuitry operating individual ones of the plurality of thrusters in response to the images captured by the imaging device. The refueling satellite deploys the fuel hose, and the computerized circuitry operates the thrusters to maneuver the end effector, bringing the fuel supply nozzle to a location to deliver fuel.