The purpose of this paper is to develop an attitude determination and control system (ADCS) for pico and nano-satellite at sub-orbital task. The actuator of this system is momentum wheel which made by commercial-off-the-shelf (COTS) components. And data of geomagnetic, gyroscope and earth sensor is integrated to determine the attitude. A hybrid rocket is expected to be the carrier of satellite, probing the irregularities of ionosphere at 100km to 300km altitude. After satellite detached form carrier, this module provides de-spin and instruments pointing ability. In this research, mechanical structure, circuit and control software have been developed. A torque test has performed to determine capacity of momentum wheel, and a rotation test has performed for validation of attitude control and de-spin process.