A spacecraft servicing system to provide in-orbit servicing through the umbilical connectors of a spacecraft. In one embodiment, a manipulator arm maneuvers a servicer umbilical to form an electrical connection between a servicer spacecraft and an umbilical connector of a client spacecraft, the umbilical connector conventionally used solely for ground-based operations. In one feature, the electrical connection is used to provide power or software upgrades to the client spacecraft.

A spacecraft servicing system to provide in-orbit servicing through the umbilical connectors of a spacecraft. In one embodiment, a manipulator arm maneuvers a servicer umbilical to form an electrical connection between a servicer spacecraft and an umbilical connector of a client spacecraft, the umbilical connector conventionally used solely for ground-based operations. In one feature, the electrical connection is used to provide power or software upgrades to the client spacecraft.

A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure

A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks. The system is constructed in a modular configuration in which two redundant integrated fluid modules may be mounted to the vehicle, each of the modules capable of supporting the upper stage functions.

A system and method for protecting an electronics module on a spacecraft in space are described. The system includes a non-radiation hardened electronics module electrically connected to a power supply, with a switch connected between the power supply and the electronics module. The switch can disconnect the electronics module from the power supply in response to an event signal. A sensor which is capable of detecting a solar proton event is connected to the switch. The sensor emits the event signal upon detection of the solar proton event.

Described herein is a thrust system for a vehicle that includes at least three electrical power controllers, at least four electrical switches each configured to receive electrical power from at least one of the at least three electrical power controllers, and at least three thrusters each configured to receive electrical power from at least one of the at least three electrical switches. The at least four electrical switches are operable to switch a supply of electrical power from any of the at least three electrical power controllers to any one of the at least three thrusters.

Provided herein are various improvements to launch vehicle payload systems, such as employed to launch and deploy secondary payloads into orbit. In one example, a system includes a fairing configured to encase a payload within an envelope of a primary fairing of a launch vehicle, and a mount system configured to adapt a mounting port for the payload to a mounting port associated with the launch vehicle. The system also includes a fairing door configured to be commanded open for deployment of the payload after the primary fairing has open.

A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

The disclosure relates to space science and space transportation, in particular, to the area of commercial exploitation of outer space, and, namely—to the structure of multiple-mission geospatial transportation complex and method of operation thereof, based on the principle of non-rocket ‘planet surface to planned circular orbit’ payload insertion. A general planetary geospatial transportation complex, according to a first variant includes a general planetary vehicle encircling the planet along the line of the planet surface cross-section by the plane parallel to plane of the equator, fastened, on launch overpass of specified altitude, and represents a linear bearing structure encircling the planet, comprising pressure hull with the special endless linear flywheels, equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives. For a general planetary geospatial transportation complex, it is distinctive that the present intended use is to solve the set of geospatial problems in industrial-scale volumes, for instance, for the purpose of relocation of ecologically harmful portion of earth-based manufacturing into near space and non-rocket space industrialization, as well as stabilization of the global climate.

Systems and methods for powering an electrical thruster (112) of a vehicle (100). The methods comprise providing an unregulated high voltage output current of a high voltage solar array (122) directly to an electric propulsion system (104) of the vehicle. The electric propulsion system generates a converted high voltage current by converting a voltage level of the unregulated high voltage output current. The converted high voltage current is supplied directly to an anode of the electrical thruster. A regulated low voltage current is also generated by regulating a low voltage output of a low voltage solar array (124). The regulated low voltage current is used to supply power to at least one electronic component of the electrical thruster.