Abstract: A method of releasing artificial satellites into Earth's orbit includes providing an orbital transport spacecraft able to move at orbital height and comprising a cargo area, hooking a plurality of satellites in said cargo area, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height, releasing said orbital transport spacecraft at orbital height, when said space launcher reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft, releasing satellites in sequence from the cargo area. The release of each satellite from the cargo area occurs in a respective predetermined direction and upon the orbital transport spacecraft has reached a respective predetermined position.

Abstract: 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.

Abstract: A method for the safe release of artificial satellite in Earth orbit includes the steps of providing an orbital transport spacecraft able to move at orbital height and comprising a plurality of PODs for releasing satellites transported by the orbital transport spacecraft, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft to release the orbital transport spacecraft from the space launcher, in case of failure to release the orbital transport spacecraft or in case of breakdown of the orbital transport spacecraft after releasing from the space launcher, activating a safety subsystem of the orbital transport spacecraft to generate a POD activation sequence to release the satellites.

Abstract: The invention relates to a method for the safe release of artificial satellite in Earth orbit comprising providing an orbital transport spacecraft (1) able to move at orbital height and comprising a plurality of PODs (11) for releasing satellites (12) transported by the orbital transport spacecraft (1), housing said orbital transport spacecraft (1) in a space launcher (100) configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft (1) to release the orbital transport spacecraft (1) from the space launcher (100), in case of failure to release the orbital transport spacecraft (1) or in case of breakdown of the orbital transport spacecraft (1) after releasing from the space launcher (100), activating a safety subsystem (21) of the orbital transport spacecraft (1) to generate a POD (11) activation sequence to release the satellites (12).

Abstract: A method of releasing artificial satellites into Earth's orbit includes providing an orbital transport spacecraft able to move at orbital height and comprising a cargo area, hooking a plurality of satellites in said cargo area, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height, releasing said orbital transport spacecraft at orbital height, when said space launcher reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft, releasing satellites in sequence from the cargo area. The release of each satellite from the cargo area occurs in a respective predetermined direction and upon the orbital transport spacecraft has reached a respective predetermined position.

Abstract: 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.

Abstract: A method for using a device for coupling with a space satellite before the satellite is launched for the purpose of de-orbiting the satellite and/or returning it to Earth. The device includes: controller for controlling the device; propulsion system operatively connected with the controller; receiver for receiving control signals operatively connected with the controller; powering system for electrically powering the device; coupler for mechanically coupling the device with the satellite before the satellite is launched. The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.

Abstract: A device for coupling with a space satellite before the satellite is launched for the purpose of de-orbiting said satellite and/or returning it to Earth. The device includes: controller for controlling the device; propulsion system operatively connected with the control means; receiver for receiving control signals operatively connected with the control means; powering system for electrically powering the device; coupler for mechanically coupling the device with the satellite before the satellite is launched. The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.

Abstract: A method for using a device for coupling with a space satellite before the satellite is launched for the purpose of de-orbiting the satellite and/or returning it to Earth. The device includes: controller for controlling the device; propulsion system operatively connected with the controller; receiver for receiving control signals operatively connected with the controller; powering system for electrically powering the device; coupler for mechanically coupling the device with the satellite before the satellite is launched. The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.

Abstract: A device for coupling with a space satellite before the satellite is launched for the purpose of de-orbiting said satellite and/or returning it to Earth. The device includes: controller for controlling the device; propulsion system operatively connected with the control means; receiver for receiving control signals operatively connected with the control means; powering system for electrically powering the device; coupler for mechanically coupling the device with the satellite before the satellite is launched. The propulsion system is enabled by the controller on receipt of control signals for deorbiting the satellite and transferring it to a given orbit.