Verification experience of spacecraft load-bearing structure and equipment units loading parameters results

One of the most important issues which should be resolved during the space vehicles development phase is dynamic coupled loads analysis. The results of such analysis for spacecrafts is the determination of loading parameters (including internal forces, moments and accelerations, as well) for load-bearing body structure and separate secondary structure items, such as solar arrays antennae reflectors, fuel tanks and others. The RSC Energia’s experience under loading parameter determination results is generalized in this article. The object is to be investigated was conditionally divided by 7 parts (named as partial units) under finite-element models (FEM) development. The partial FEM was developed for each mentioned item. Partial FEM’s verification was implemented by modal survey or/and vibrostrength tests (on the frequency response functions determination phase). The verified partial FEMs were assembled into «generalized» FEM of the Spacecraft by using «synthesis of partial dynamic parameters» methodology. Based on the coupled loads analysis implemented by Launch vehicle developer, the loads for spacecraft’s body principle interfaces and conditional spectra of limit load factors for attachment zones of the main secondary structure items were determined.