Composite laminates with joggles as typical design details are widely used in aircraft structures. The length to depth ratio, the same direction joggle spacing and two different direction joggle spacing are used as design verifications to establish the parametric finite element model. Through stress and strain distribution, previous failure and final loading capacity analysis, the effect of design variables on joggle structures mechanical property is determined and the parametric design is carried out. The results indicate that the structure damage initiates at the transition of joggle; the reasonable design parameters for the joggle are B/A ≥ 20 for length to depth ratio, A /H≥12 for spacing between two joggles in the same direction and C /A _min ≥ 1.5 for spacing between two joggles in different directions.