For high-precision attitude control of nanosatellites in Very Low Earth Orbits (VLEO), the authors are developing an independent external control flap system that generates control torques through aerodynamic interactions while ensuring minimal atmospheric drag and efficient internal space usage. Preliminary results from ground-based experiments for surface-particle interactions and simulations using atmospheric models demonstrate promising attitude control accuracy and sufficient safety margins. The possibility of operating nanosatellites in VLEO opens up new standards in payload performance, such as higher resolution for earth observation and lower latency for communication, while at the same time keeping the size of the satellite in the nano class. The disadvantageous influence of the increased density in the VLEO, disturbing the satellite’s attitude and orbit, is counteracted by the use of the control flap system in combination with an electric thruster. The proposed nanosatellite platform is based partially on the successfully operated SOMP2b satellite, which contains several subsystems with commercial off-the-shelf components and thus benefits significantly from the lower radiation exposure in VLEO. In addition, depending on the geometry of the satellite system, a quasi-aerostable system with active damping is provided. Consequently, the position of the satellite is passively stable around an equilibrium point, although the amplitudes and frequency of the oscillation are readjusted using the control flap system. The concept shall not utilize solar panels as control flaps in order to allow a larger variety of possible surface materials as well as to minimise the compromise between power supply and attitude control. The system has been tested in simulations using atmospheric models (HWM14, JB2008, NRLMSISE00) and surface-particle interaction derived from first laboratory experiments replicating approximate VLEO flow conditions. Initial results from these preliminary tests demonstrate promising attitude control accuracy and sufficient safety margins before reaching saturation limits. Additionally, they enable the investigation of satellite behaviour during different attitude maneuvers, as well as the selection of suitable surface materials for the control flaps. The presentation will critically reflect the simulation and lab-based experiment results, as well as the implementation on the new VLEO nanosatellite platform and identify further development requirements.