Abstract: The paper presents the test design and the implementation of the canister modal test of a satellite. The accurate major frequencies of the spacecraft structures can be obtained with the single-point random excitation method, two-point random excitation method and single-point stepped sine excitation method. The first frequency of the large spacecraft structure can be acquired with the single-point random excitation method and be verified with the single-point stepped sine excitation method. The two or more points excitation methods are used to obtain the parameters of higher mode or the structure damping rates, which would make the input energy close to the average value and the response close to the real dynamic state of the spacecraft structures. The study can be a references to the modal test of large spacecraft structures.