COUPLED LOAD ANALYSIS APPLICATION ON FORMOSAT-2 DEVELOPMENT

摘要

Among those general launch environment loads, the quasi-static load and transient dynamic load are the most important to the design of satellite primary structure. The justification of the transient dynamic load is conducted by coupled load analysis methodology using analytical models of launch vehicle and satellite. This kind of analysis is called coupled load analysis or CLA. This paper is to describe in detail of the FORMOSAT-2/Taurus-7 CLA process, especially on satellite model creation as well as the CLA analysis results interpretation. Two main purposes are met on the FORMOSAT-2 CLA: (1 Verification of maximum loads experience in satellite during transient vibration, (2)identification of system dynamic characteristics. Besides, the CLA also yields the mechanical interface loads and gap displacements which are crucial to the satellite final verification. Usually, at least two coupled load analysis cycles are executed at different development stages. The final CLA results show enough margins existed in the FORMOSAT-2 satellite design. The satellite was successful launch on May 20, 2004. Telemetry acceleration data also validated the efforts.