To meet the requirements of the "three-horizontal" test and launch mode for the horizontal integration of large satellites and fairings in launch vehicles

a tilting device was designed to achieve low-G and smooth vertical-to-horizontal transition of satellites

followed by horizontal assembly with fairings to form the satellite-fairing combination. Considering satellites as precision spacecraft with small design margins

the controlling its flipping overload and stability constitutes critical parameters requiring strict assurance. Strength simulation analysis was conducted on key structures of the flipping mechanism using ANSYS

while many vibration sensors and strain gauges were employed to monitor dynamic responses of the satellite-fairing combination during the tilting test. Both simulation and experimental results demonstrate that the design of tilting device is reasonable and feasible

with all parameters meeting the specified requirements. This study provides an effective technical solution for implementing the "three-horizontal" integration process in satellite launch operations.