It's an important operational performance of stealth aircrafts to realize embedded ejection and launch of air-to-air missiles under the condition of carriers’ large maneuvering flight. Carriers’ large maneuvering flight makes missile ejection separation parameters deviate design values to threat seriously the launch safety of stealth aircrafts. Based on the flexible multi-body Lagrange multiplier method, components modal tests and the condition of stealth aircrafts’ large maneuvering flight, a rigid-flexible-liquid coupled dynamic modeling method for stealth aircrafts’ embedded ejection under their large maneuvering flight was put forward. The corresponding launch dynamic characteristics were simulated. The influences of high overload centrifugal force produced due to carriers’ large maneuvering flight on the ejection separation parameters of air-to-air missiles were analyzed. The simulation results showed that carriers’ large maneuvering flight makes missiles’ ejection separation attitude angle decrease obviously to threat missiles’ launch safety. The results provided a theoretical basis for further studying stealth aircrafts’ launch safety under large maneuvering flight and initial trajectories of air-to-air missiles.