The high-density rib structure composite panel could be formed at one time by using the vacuum assisted resin infusion process （VARI）. However， there were issues in the molding process， such as the difficulty of preforming the fabrics at rib area and complex resin flow control. So it was difficult to guarantee the dimensional accuracy and internal defects of the part. Based on the structural characteristics of the multi-featured area of the high-density rib structure composite panel， the resin flow simulation and compaction test were implemented to optimize the preforming process parameters and the partitioned resin injection scheme. The results show that the compaction parameters of the agent concentration of 4%， temperature of 120 ℃， pressure of 0.1 MPa， and holding time of 60 min can effectively ensure the satisfied fiber volume fraction. Adopting a graded glue injection scheme that combines line injection， line riser， and rib point riser can effectively infiltrate the panel structure. The optimized process parameters and the partitioned resin injection scheme are successfully applied to the VARI forming of a high-density rib structure integral panel belonging to an aircraft. The effectiveness of the used analysis method is verified in this paper. The critical reference value for the use and development of low-cost integrated forming technology for rib structure composite panels in military and commercial aircraft is provided.