A cooperative missile aerodynamic control (CMAC) law is proposed to realize cooperative impact by employing squeeze mode condition. Firstly, this paper demonstrates the implications of the squeeze mode condition and its effects on the missile aerodynamic parameters. Moreover, this paper simplifies these parameters using fitting functions, and introduces a novel variable for missile guidance control. Secondly, because of the variational velocity and the squeeze mode condition, time-to-go is difficult to be estimated analytically as it is highly nonlinear. Thus, the neural network is employed to fit the relationship of time-to-go with respect to different engagement conditions and the squeeze mode condition. Next, the CMAC law is devised to attain the desired impact time by regulating the squeeze mode condition. We can regulate drag by using squeeze mode condition to achieve cooperative guidance. The simulation outcomes compellingly demonstrate the efficacy of the CMAC law, showcasing smooth trajectory and lower command.