A cooperative guidance algorithm against a stationary target simultaneously is presented in this article. First, to achieve impact time consensus for multiple missiles, the look angle profile is formulated as a trigonometric function related to time-to-go and relative range. Second, the guidance law with guaranteed convergence is proposed to nullify the look angle tracking error in a fixed time. The proposed result does not call for precise time-to-go estimations, linearized approximations, or complex numerical algorithms, in contrast to most existing cooperative guidance laws, thus possessing better tractability and adaptability. Finally, to show the effective performance of the designed guidance algorithm, numerical simulations are presented.