A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

Integrated chemical propellant and cold gas propulsion systems and methods are provided. A storage or fuel tank containing the chemical propellant is pressurized by a pressurant. The chemical propellant is selective passed to a propellant thruster through a first port of the storage tank and a propellant valve. The pressurant is selectively passed to a cold gas thruster through a second port of the storage tank and a cold gas valve. In addition, a pressurant tank can be provided. Pressurant contained within the pressurant tank can be selectively placed in communication with the pressurant contained within the storage tank via a pressurant valve, or can be selectively passed to the cold gas thruster through the cold gas thruster valve. Systems can also include bi-propellant thrusters, with a first and second chemical compounds and volumes of pressurant stored in first and second storage tanks respectively.

Integrated chemical propellant and cold gas propulsion systems and methods are provided. A storage or fuel tank containing the chemical propellant is pressurized by a pressurant. The chemical propellant is selective passed to a propellant thruster through a first port of the storage tank and a propellant valve. The pressurant is selectively passed to a cold gas thruster through a second port of the storage tank and a cold gas valve. In addition, a pressurant tank can be provided. Pressurant contained within the pressurant tank can be selectively placed in communication with the pressurant contained within the storage tank via a pressurant valve, or can be selectively passed to the cold gas thruster through the cold gas thruster valve. Systems can also include bi-propellant thrusters, with a first and second chemical compounds and volumes of pressurant stored in first and second storage tanks respectively.

A single-person spacecraft includes a pressurized crew enclosure, an external equipment bay, and an overhead crown assembly.

An electrodeless plasma thruster with close ring-shaped gas discharge chamber (1,10) can include a gas discharge chamber (1,10) close ring shaped in fluid communication with a propellant storage system (10,70). An antenna (3,30) can be positioned on the exterior of the gas discharge tube (1,10). A guide tube (2,20) can be coupled with the gas discharge chamber (1,10) at a first end and have a second open end. A magnetic system (7,50) can be positioned on the second end of the guide tube (2,20). The magnetic system (7,50) can be electrically coupled with a power supply. The power supply can be electrically coupled with a power converter (11,80) and a control module (12,90).

A control system configured to execute a safing mode sequence for a spacecraft is disclosed. The control system includes one or more star trackers that each include a field of view to capture light from a plurality of space objects surrounding the celestial body. The control system also includes one or more actuators, one or more processors in electronic communication with the one or more actuators, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to determine a current attitude of the spacecraft, and re-orient the spacecraft from a current attitude into a momentum neutral attitude.

A spacecraft has a flat antenna array having an edge and a middle portion. A reconfigurable reaction-momentum wheel is coupled to the antenna array to roll and/or pitch the antenna array in small magnitudes. The reconfigurable reaction-momentum has a reaction operating state or mode (high-torque, low momentum) and a momentum operating state or mode (low-torque, high momentum). A thruster is coupled to the antenna array to move the antenna array.

A spacecraft reaction control system comprising: a spacecraft having a center of mass; a length of tether extending from said spacecraft and offset from said spacecraft's center of mass and means for controllably changing said extension of said offset such that a variable force is exerted upon said spacecraft by said tether, said force being offset from said center of mass.

A spacecraft reaction control system comprising: a spacecraft having a center of mass; a length of tether extending from said spacecraft and offset from said spacecraft's center of mass and means for controllably changing said extension of said offset such that a variable force is exerted upon said spacecraft by said tether, said force being offset from said center of mass.