Document Type : Review Article
Aerospace engineering, Amirkabir University of Technology
Aerospace Research Institute, Tehran, Iran
Amirkabir Universuty of Technology
For carrying out their missions, many satellites use closed-loop attitude control. For closing the control loop, they use several sensors, such as sun sensors, magnetometer, and star tracker. Sun sensors are not operational during the eclipse; therefore, one of the observed vectors is lost. For this reason, attitude determination in eclipse can be a challenging issue for control engineers. This paper presents a novel idea for producing a new generation of sensors that can measure the induced electric field vector not only in eclipse but also in the whole orbit. This electric field comes from the high velocity of the spacecraft in the magnetic field of the Earth. This vector is always perpendicular to the magnetic field; thus, it is never aligned with the magnetic vector and never causes singularity and accuracy decreasing. The induced electric field is measured by three RC circuits that are actuated by sinusoidal voltage. The dielectrics of the capacitors are made of ferroelectric materials; therefore, the induced voltage affects the permittivity and voltage of the capacitor. By measuring and calibrating this effect in three perpendicular axes can measure the three components of the electric field vector. The theory of the proposed sensor has been developed, and simulation studies validate the results.