Quasi-Static Structural Test of Satellites

Satellites are exposed to simultaneous static and dynamic loads during the launch phase due to launcher acceleration and aerodynamics. Therefore, they are designed and tested to withstand all these loads. From design perspective, a common approach is to combine static and dynamic loads into an equivalent static load which is referred to as quasi-static loads [1]. The validation of the structural design of the satellite is performed by tests and/or analysis. This paper discusses the static load test methods with an emphasis on the acceleration tests performed on vibration test systems.