Developing an advanced simulation to control a swarm of 20 PocketQube nanosatellites using a Linear Quadratic Regulator (LQR) involves several crucial steps that go beyond the initial scheme. A comprehensive approach requires a deep understanding of orbital mechanics and in particular the challenges presented by the nanosatellite platform. The inherent limitations of nanosatellite power, propulsion, and communications systems require careful orbital selection and maneuver planning to achieve mission objectives efficiently and reliably. This includes optimizing launch windows, understanding atmospheric drag effects in low Earth orbits (LEO), and designing robust attitude control systems to maintain the desired pointing for scientific instruments or communications links. Our article focuses on simulating the attitude control of PocketQube nanosatellites in a swarm using the Matlab/Simulink environment. First, we provided a mathematical model for the relative coordinates of a nanosatellite swarm. Second, we developed a mathematical model of the Linear Quadratic Regulator implementation in the relative navigation. Third, we simulated the attitude control of 20 PocketQube nanosatellites using the Matlab/Simulink environment. Finally, we provided the swarm scenario and attitude control system data. Simulation of an attitude control system for 20 PocketQube nanosatellites using an LQR controller in swarm successfully demonstrated the stabilization capabilities essential for swarm operations in the space environment. A link to the video of the simulation is provided in the Results section.