The invention relates to the field of flexible satellite attitude orbit coupling control, in particular to a flexible satellite attitude orbit coupling control method based on an isolation allowance method and a pulse width fusion strategy. The method solves the problems that in the satellite in-orbit attitude and orbit control process, a flywheel cannot control that the corresponding thruster layout is not given, the plume influence and rotational inertia level bias are not considered, isolation allowance is not considered and the attitude does not meet the requirement. The method comprises the steps of 1, obtaining sailboard locking and satellite uncontrollable dynamical model parameters; 2, determining installation position coordinates of a thrust; 3, determining an IM value; 4, obtaining an orbit-control LQG sequence; 5, determining the orbit-control pulse width and the air injection direction; 6, selecting air injection of the attitude-controlled thrust; 7, determining the range of the attitude-controlled thrust; 8, determining the attitude-controlled air injection time; 9, obtaining an equivalent force moment value. The flexible satellite attitude orbit coupling control method is applied to the field of flexible satellite attitude orbit coupling control.