This paper aims to strengthen the knowledge of galvanic corrosion between 7B04 aluminium alloy and TC16 titanium and provide guidance on corrosion protection for aircraft in service under specific marine atmospheric environment. The 10-cycle accelerated corrosion test of 7B04 Aluminium-7B04 aluminium lap joints riveted with titanium alloy rivets and polarization test pieces were carried out in simulated marine atmospheric environment. Polarization curves of two alloys after 0 cycle and 10 cycles were measured by PARSTAT 4000 electrochemical workstation. Its results were used as boundary conditions for COMSOL numerical simulation to contrast with test results. Fatigue life of lap joints after 4, 6, 8 and 10 cycles of accelerated corrosion test were obtained by fatigue test. Observation of corrosion morphology and measurement of corrosion pit depth near fatigue fracture were got by using optical microscope. Using XRD to analysis corrosion products of aluminium alloy so as to reveal whether the corrosion mechanism has changed. Through a variety of characterization test results, the galvanic corrosion between 7B04 aluminum alloy and TC16 Titanium alloy is explained from different angles. Coupled with the comparative analysis with the numerical simulation results, the reliability and accuracy of the test results are ensured. After 0 cycles and 10 cycles of the accelerated corrosion test, the self-corrosion potential and self-corrosion current density of aluminium alloy are ?802 mV and ?872 mV, 2.357×10?7 A/cm2 and 1.477×10?6 A/cm2, respectively, while those of titanium alloy are respectively ?313 mV and ?274 mV, 1.638×10?8 A/cm2 and 4.144×10?8 A/cm2. The location of the fatigue fracture is consistent with the most severely corroded area and the largest potential difference in numerical simulation. With the extension of the corrosion cycle, the corrosion becomes more and more serious, and the depth of the corrosion pit gradually increases. Galvanic corrosion occurs between the two alloys. 7B04 aluminium alloy corrodes as the anode, and with the extension of the corrosion cycle, the corrosion potential is negatively shifted, and the corrosion rate increases; TC16 titanium alloy is used as the cathode, and the corrosion potential is positively shifted with the extension of the corrosion cycle. XRD spectrums show that the main components of aluminium alloy corrosion products are Al(OH)3, Al2O3; XRD results show that the corrosion mechanism of 7B04 aluminum alloy in 0-10 cycle has not changed, and with the progress of corrosion, a large number of corrosion products wrap the aluminum alloy surface, resulting in the slow growth rate of corrosion pit depth, indicating that the uniform corrosion layer on the surface has a certain protective function, which will reduce the pitting corrosion sensitivity of the aluminum alloy surface. The numerical simulation results are consistent with the experimental results. Through the comprehensive analysis of corrosion morphology and numerical simulation results, the action range of galvanic corrosion is found out. In addition to the internal corrosion of the screw hole, the maximum range is about a circular area 2 mm larger than the radius of the screw hole. Aircraft new structure design and old structure maintenance should focus on rivets around to avoid fatigue failure.