This paper describes several results related to the use of the data collected by the GRACE GPS receiver, high precision accelerometer observations and precise attitude data from star trackers in the application of the GRACE Precise Orbit Determination PODD).
Star sensor is one of the precise attitude determination sensors.
OGS and CubeSat point beacon lasers at each other for precise attitude control.
Simulation results show that precise attitude control is accomplished based on the proposed method.
Simulation results for the spacecraft model show precise attitude control and vibration suppression.
These concepts require propulsion systems for precise attitude and orbit control manoeuvrability.
Hence, the satellites can achieve precise attitude control under low power, space, and mass constraints using this proposed method.
Moreover, each Swarm satellite carries three star trackers allowing a precise attitude reconstruction for all latitudes and local times.
To achieve precise attitude stabilization, these small satellites should estimate their attitude rate under the strict constraints of mass, space, and cost.
This research presents a new method for small satellites to precisely estimate angular rate using star blurred images by employing a mission telescope to achieve precise attitude stabilization.
