Starting from the 1990s, the mini/micro-satellites around 50-200 kg become one of the research focuses of space industry. Different from the mini-satellites developed at early ages, modern mini/micro-satellites widely incorporate micro-electronics and micro-mechanisms, emphasizing multi-functionality and system integration. As a result, they have relatively high power/volume ratio. Also, to reduce the fuel consumption, the application of micro-electrical propulsion systems on mini/micro-satellites is increasing, which pushes the requirement for electrical power even higher. It is hard for the surface mounted solar cells and stationary solar arrays which were widely used by micro satellites at early ages to satisfy these elevating power requirements of modern mini/micro-satellites. In response to these requirements, Solar Array Drive Assemblies (SADA) which used to be standard equipments of large spacecrafts have gradually been incorporated in the mini/micro-satellites to rotate the solar arrays for maximum sunlight acquisition, and tremendously reduce the size and mass of the solar arrays. Lately, a new micro-SADA with integrated mechanisms and electronics has been developed by Beijing Institute of Control Engineering. This SADA features: Mechanisms and electronics integrated in one capsule instead of the separate mechanisms and electronic boxes as in large spacecrafts. High torque/weight ratio stepper motor & high precision mini-transmission. Long life high power/weight ratio multi-channel slip ring. High reliability measures against severe mechanical, electrical and thermal conditions. This SADA has gone through functional test, mechanical tests (vibration, acceleration, and shock, etc.), thermal-vacuum cycling test, and electromagnetic compatibility test, and demonstrated excellent functionality. The design as well as the development and test processes is summarized in this paper.