The generation of torque of traditional aircraft corresponds to the fixed rudder surface, but the multi-control plane faces the problem of rudder surface allocation during maneuvering, so the multi-control plane often needs to separate the control law from the distribution law. This paper takes an aircraft with multiple control surfaces as an example. Firstly, the distribution strategy of control law and distributive law is analyzed. Secondly, according to the characteristics of multi-control surface aircraft, distributive law design based on weighted pseudo-inverse and cascade chain method is carried out respectively. Finally, the distributive law of the designed weighted pseudo-inverse method and cascade chain method combined with the dynamic inverse control law is verified by simulation. The results show that the responses of the two methods to the specified command are basically the same, but there are big differences in the direct lift rudder surface, which has reference value for the subsequent application of the multi-control surface aircraft in direct lift.