Abstract: The solar array has to be locked in a specified position after deployment. The locking process produces a large shock on the SADA of the satellite. Accurate related results are difficult to be obtained from the commercial software simulations. This paper proposes a measurement method by connecting a measuring tool between the satellite body and the root hinge of the solar array. The strain data can be measured from the tool and the shock load can be calculated indirectly. The method is validated in the satellite development.