Abstract: Fixed-wing UAVs face a higher risk of collision with the carrier aircraft during deployment due to their unfolded wings. Taking the non-folding fixed-wing UAV as the object, the deployment window and flight control strategies were investigated. Numerical simulation techniques combined with six-degree-of-freedom motion simulation were employed to investigate the effects of Mach numbers, angles of attack, sideslip angles and centers of gravity on the deployment process. Additionally, deployment flight tests of the fixed-wing UAV were conducted. The results show that the sub-UAV’s lift curve slope significantly decreases and a nose-up moment is generated due to the carrier aircraft’s wake flow. A smaller initial angle of attack during release results in a higher nose-up angular rate for the UAV, but the vertical displacement in the descent direction remains the largest. Due to the UAV’s small roll moment of inertia, large roll angles will occur under crosswind disturbances. Timely roll attitude control via the flight controller is therefore necessary. During flight tests, a pre-set 1° elevator deflection and a zero-delay flight control strategy were implemented. Upon separation, the UAV exhibited a pronounced right-roll tendency under crosswind disturbances, reaching a maximum roll angular rate of nearly 40 (°)/s and a pitch attitude angle of approximately 6°, before stabilizing under controlled conditions. Flight test results demonstrated successful separation of the UAV from the carrier aircraft, validating the correctness of the simulation analysis and the flight control strategy design.