CUBESAT Attitude Control Systems and Components for Innovative Space Mission Solutions Lakshya Vaibhav Datta 1 , Ugur Guven 2 Aerospace Engineering Dept., University of Petroleum and Energy Studies PO and Vill. Bidholi, Dehradun, 248007, INDIA 1 lakshyavdatta@gmail.com , 2 drguven@live.com With the advents in space technology, the concept of sending nanosatellites, and specifically Cubesats, has become quite common for universities and research institutions all across the world. One of the most important subsystems of a Cubesat is its Attitude and Orbit Control System. This system is responsible for maintaining the optimum orientation of the Cubesat in orbit with respect to the Earth. Even though the angular motion of the Cubesat does not affect its trajectory; solar winds, solar pressure torques, drag forces due to residual atmosphere or simply motion of internal mechanical parts lead to angular destabilization of the Cubesat while in orbit. There is a growing need to better the available AOCS in order to increase accuracy of experimental data collected by the Cubesat. Better systems will help in better remote sensing and weather forecasting while maintaining continuous communication between the Cubesat and the ground station. Another advantage of a versatile AOCS is the ability to perform complex orbital maneuvers for space debris removal. This paper discusses the importance of the AOCS and the various methodologies used in order to control the orientation of the Cubesat while it is in orbit. The main components of the Attitude and Orbital Control System include Sun sensors, Earth sensors, Momentum wheels, Magnetic torquers, Thrusters, Solar arrays, Trim tab positioners. This paper elaborates on each of the above. Furthermore, it discusses the causes for loss of orientation control while the Cubesat orbits the Earth and ways to reduce these effects for a more controlled and safe operational environment. Specific examples are also given for various case studies. 1. INTRODUCTION The AOCS provides the ground station with all the nanosatellite attitude information and maintains it right from the time it separates from the launch vehicle through its entire operational lifetime and is hence one of the most important subsystems of the nanosatellite [1]. The subsystem provides attitude and orbit control by using a highly momentum biased approach. It basically controls the torque provided by the momentum wheels, reaction wheels and/ or the magnetic torquers and provides accurate motion of the nanosatellites while they are in orbit. Although the approach is highly momentum biased, orbital maneuvers and transfer orbit control is provided by the use of on – board thrusters. Attitude control is the practice of controlling the orientation of the nanosatellite with respect to an inertial frame of reference which in this case happens to be the Earth. [1] The main objectives of the attitude determination and control system are De – tumbling of the satellite after deployment, pointing towards the earth, and pointing towards the sun so that the solar arrays can produce maximum electric power. [1] Controlling the orientation of the nanosatellite requires sensors, actuators and algorithms. The proposed methods of attitude control involve the use of ‘on – the – shelf’ technologies in