CubeSat technology has been widely studied in the last 20 years, especially for missions in Low-Earth-Orbit (LEO). It represents an interesting alternative to multisatellite missions with bigger spacecrafts thanks to their superior agility and low cost. When these nanosatellites are operating to achieve a docking mission, it is essential to carefully plan rendezvous maneuvers and proximity operations to ensure mission safety and success. The aim of this research is to design and evaluate the performance of guidance and control algorithms for orbital rendezvous maneuvers. Zero-Effort-Mission/Zero-Effort-Velocity (ZEM-ZEV) guidance and Linear Quadratic Regulator (LQR) control are investigated to achieve position and attitude control for two 3U CubeSats in different scenarios.