In order to decrease satellite attitude turnover and guarantee high-accuracy pointing for satellite optical payload,a novel method is designed for horizontal deployment experiment of satellite solar array. A multi-degree-of-freedom balance weight strategy is used to counterbalance the gravity. Firstly,the kinematics model and dynamics model are established. Then,the error analysis is deduced. Finally,the experiment is carried out. The experimental results show that the method can truly simulate the micro-gravity in-orbit environment compared with the previous method. Moreover,it is very strict with mass deviation and centroid deviation of solar array and the system frictions. The results indicate that the model and test methods are correct and meet the test requirements.