A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.

A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.

The PanelSat Launch System consists of PanelSat(s) and it's/their Launcher. It serves to launch one, better several satellites into space, whereby besides unfurling of the thin film solar cell panels off their rolls no further deployment is needed.

PanelSats are small agile spacecraft thought especially for observation and communication services in LEO, which are using their thin film solar cell panels for both, harvesting electric energy as well as for fuel less station keeping, steering, pointing and propulsion.

In contrast to conventional satellites with their 3-axis control design, PanelSats are not locked to only 3 axles and can tilt and point into several directions (depending on the number of panels).

Besides Roller Reefing for fuel less attitude control PanelSats feature Soso Steering (switch on, switch off) which adds even better fuel less agility compared to prior art satellites.

The PanelSat Launch System consists of PanelSat(s) and it's/their Launcher. It serves to launch one, better several satellites into space, whereby besides unfurling of the thin film solar cell panels off their rolls no further deployment is needed.

PanelSats are small agile spacecraft thought especially for observation and communication services in LEO, which are using their thin film solar cell panels for both, harvesting electric energy as well as for fuel less station keeping, steering, pointing and propulsion.

In contrast to conventional satellites with their 3-axis control design, PanelSats are not locked to only 3 axles and can tilt and point into several directions (depending on the number of panels).

Besides Roller Reefing for fuel less attitude control PanelSats feature Soso Steering (switch on, switch off) which adds even better fuel less agility compared to prior art satellites.

Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Described herein are systems and methods for attitude determination using infrared Earth horizon sensors (EHSs) with Gaussian response characteristics. Attitude information is acquired by detecting Earth's infrared electromagnetic radiation and, subsequently, determining the region obscured by Earth in the sensors' fields of view to compute a nadir vector estimation in the spacecraft's body frame. The method can be applied when two sensors, each with known and distinct pointing directions, detect the horizon, which is defined as having their fields of view partially obscured by Earth. The method can be implemented compactly to provide high-accuracy attitude within small spacecraft, such as CubeSat-based satellites.

A satellite deorbiting device including an aerobraking surface including a satellite attitude control device with gravity gradient, the device with gravity gradient including at least one mast carrying the aerobraking surface, a first end of which is secured to the satellite and the second end of which is provided with a mass, such that the mast is oriented in a direction opposing that of the planet around which the satellite orbits.