In the design and manufacture of aircraft composite skin structure, composite Ω stringer or T stringer reinforced skin panel is typical airplane integrated structure. The study on the two different structures of composite reinforced panels in the world nowadays is mainly about whether the reinforcement geometrical shape, strength and weight could meet the structure performance requirement. Rare researchers study on the process comparison and analysis of the two different kinds of stringer structures. However, the study on process comparison and analysis of the two different kinds of stringer structures on the early design stage could help with the balance between reinforced panel structure performance and cost, therefore to achieve optimum design with low manufacture cost, as being not only the basis of material choosing, but being helpful for optimal process. The thesis studies on aircraft composite typical Ω stringer and T stringer co-curing process structure through simulation of different manufacture process tests, strength comparison tests etc., then we gain mass of data of manufacture advantages and disadvantages, strength comparison, individual process characteristics etc. We propose methods of different structure process analysis in aircraft design and manufacture concurrent engineering. Through the comparison analysis of the data, we illustrate the process advantages and disadvantages of the two structures. Then we summarize the analysis and research result and make a conclusion.