Attitude determination and control systems of satellites (adcs) are responsible for orientation of satellite to desired direction and determination of the changed direction. they only operate as designed in the reduced friction and magnetic environment of space. emulating these characteristics of space in a laboratory environment in order to test individual components and integrated adcs systems is a necessary and challenging step in verifying and predicting satellite's behaviour in space. this generic platform is being built for testing passive and active control strategies for satellites. the testbed comprises of the helmholtz cage, hemispherical air bearing and a series of sensors for attitude determination. the satellite will be fixed on the platform and the whole system will be levitated in air using air bearing. the air bearing has an ingenious low-cost design, its hemispherical design interface with satellite casing allows 3 axis movement of the satellite with restricted rotational freedom. electrical circuitry is divided into two sections – transmitting and receiving section. transmitting pcb consists of a magnetometer, accelerometer, gyroscope and temperature sensors. these sensors are interfaced with a controller via i2c interface. complementary filter implemented in the controller combines the sensor data received, predicting the angular displacement of the satellite while suppressing sensor's noise to increase precision. angular displacement and magnetometer data are transmitted to the receiving side over a wireless bluetooth link. this pcb is mounted on air bearing which is placed inside helmholtz cage. copper wires wound over helmholtz cage are used for generating uniform magnetic field per axis. receiving pcb consists of three low power solenoid driving circuits designed for driving helmholtz coils. all these circuits will be powered up using ac mains. transformer, rectifier, and regulators will be used. integration of these circuits with independent microcontroller allows real-time response and accurate control on feedback from magnetometer placed in the setup. pulse width modulation with adaptive duty cycle is used to control excitation of coils. orbit is predicted using sgp4 model and orbital two line elements magnetic field is calculated using international geomagnetic reference field (igrf) model. both these models are implemented on a computer which is interfaced with receiving side controller. thus the setup allows attitude determination and control algorithms to be tested in a simulated magnetic field, near frictionless and torque-free environment. this project involves orbital and magnetic field simulation techniques followed by the design and construction of a helmholtz cage and pcbs at transmitting and receiving side suitable for the testing and evaluation of the attitude determination and control system (adcs) of a satellite.