On the basis of aerodynamic calculation and accelerometer-based method for estimating the angle of attack of the guided munitions, this paper studies the angle of attack identification of a miniature guided munition. By establishing an aerodynamic model, the aerodynamic and balanced angle of attack data under the typical flight conditions of the guided munitions are calculated out. Based on the aerodynamic characteristics, an angle of attack identification model is established, and a layout scheme of the missile-board inertial measurement units is proposed. Combined with the test data, the angle of attack identification results of the guided munitions are calculated out. The comparison with the simulation results shows that, the angle of attack identification based on flight test data is consistent with the aerodynamic simulation results, which proves that the proposed angle of attack identification method is reasonable and feasible.