Abstract: The active flow control technology is an effective method to improve the aerodynamic characteristics of aerospace vehicles, in which actuators are the core of these control technologies such as plasma actuator, synthetic jet actuator and oscillating jet actuator. Present study proposes a parallel graphene actuator based on the thermo-acoustic effect. The actuator has the advantages of simple structure, low input power, wide controlling frequency and strong structural adaptability. It can adapt to various complex curved wall installations of aircraft environment and variable working conditions, resulting in a good application prospect. Specifically, the thermo-acoustic actuator utilizes the extremely low specific heat capacity and high coefficient of heat conductivity characteristics of graphene materials. Through the Joule heating principle, the graphene films can radiate a periodic sound field to the surrounding air for acoustic excitation control. According to this principle, firstly this paper uses the thermo-acoustic theory to model the sound field of the graphene actuator, adds the principle of combined sound source superposition to the modeling, and optimizes the computation method of acoustic wave phase difference and sound field directivity. Secondly, it improves the circuit connection method of the parallel graphene actuator films so that it effectively increases the sound pressure amplitude of the sound field. Finally, by establishing a sound pressure test platform in a semi-anechoic chamber room and analyzing the influence of input power, frequency, test distance and other factors on output sound pressure, this paper studies and verifies the sound field of the parallel graphene thermo-acoustic actuator.