Abstract: The dynamic response of aviation dummy under vertical impact is studied by combing experimental study and numerical simulation. Firstly, 14 g and 19 g dynamic impact tests were carried out to compare the lumbar response of aviation dummy under different impact loads. Secondly, the numerical analysis model for aviation dummy/seat restraint system was developed and validated. Then, parametric studies were conducted to investigate the effects of seatback angle and seat pitch angle on occupant injury and seat responses. Results show that the ratios of peak lumbar force, peak longitudinal friction and seat pan pressure are greater than the ratio of peak load pulse under both 14 g and 19 g impacts, so the lumbar force, longitudinal friction force and seat pan pressure all have amplification effect on the peak load pulse. The 14 g pulse has a longer duration, and it causes greater Y-axis peak moment of lumbar and Y-axis peak moment of seat pan than 19 g pulse. The peak compression load of the lumbar and the peak pressure of the seat pan both have a quadratic function relationship with the seat back angle. When the seat back angle is about 110°, the risk of lumbar injury of occupant is the largest. The peak compression load of lumbar and the peak pressure of seat pan increase with the increase of the pitch angle of seat, showing a quadratic function relationship, and the growth gradually becomes gentle.