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 satellite module for attitude determination includes a containment body comprising at least one data acquisition board and a connection interface, at least one first-type sensor selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, in communication with the data acquisition board and at least one second-type sensor, different from the first type, selected from a sun sensor, an earth sensor, a stellar sensor, a horizon sensor, and in communication with the data acquisition board. The connection interface may be mounted on a first face of the containment body, the first-type sensor may be mounted on a second face of the containment body, and the second-type sensor may be mounted on a third face of the containment body.

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: The back EMF (BEMF) of a motor is sensed and compared to a target back EMF (BEMF) to generate an error control signal. The circuit supply voltage is also sensed. A PWM motor control signal is generated in response to a comparison of the error control signal to a ramp signal having a variable slope. The variable slope is selected in response to the sensed circuit supply voltage. The motor is then driven in response to the PWM control signal. The sign of the error control signal is used to selectively short one of motor terminals to a reference voltage supply node while the other motor terminal is driven in response to the PWM control signal.

Abstract: An oscillator circuit selectively charges and discharges a capacitor with currents having variable magnitudes. A trimming circuit functions to measure a half period of the oscillator signal. The measured half period is compared to a reference period to generate an error signal. The variable magnitudes of one or the other or both of the current for sourcing or sinking at the capacitor are adjusted in response to the error signal.

Abstract: The back EMF (BEMF) of a motor is sensed and compared to a target back EMF (BEMF) to generate an error control signal. The circuit supply voltage is also sensed. A PWM motor control signal is generated in response to a comparison of the error control signal to a ramp signal having a variable slope. The variable slope is selected in response to the sensed circuit supply voltage. The motor is then driven in response to the PWM control signal. The sign of the error control signal is used to selectively short one of motor terminals to a reference voltage supply node while the other motor terminal is driven in response to the PWM control signal.