Satellites　experience　complex　vibrational　environments　during　their　launch　and　operation,　potentially　leading　to　structural　failures　and　equipment　damage.　This　work　aimed　to　mitigate　this　issue　by　designing　a　variable　cross-sectional　metal　rubber　isolator　(VCMRI),　which　was　fully　constructed　from　metal　and　featured　a　symmetric　structure.　Initially,　a　finite　element　model　of　the　VCMRI　was　developed,　incorporating　symmetric　boundary　conditions　and　employing　the　Bergström–Boyce　model　to　define　variable　cross-sectional　metal　rubber　(VCMR)　parameters.　Subsequently,　sinusoidal　sweep　tests　were　performed　to　investigate　how　variations　in　VCMR　density,　spring　stiffness,　and　exc　itation　deflection　angle　affect　the　peak　acceleration　response　and　natural　frequency　of　the　VCMRI.　Finally,　simulation　analyses　were　conducted　and　insertion　loss　was　derived　from　the　results　to　assess　the　vibration　isolation　performance　of　the　VCMRI.　The　results　indicate　that　the　finite　element　model　accurately　captures　the　dynamic　behavior　of　the　VCMRI　with　minimal　error.　In　addition,　the　VCMRI　demonstrates　robust　vibration　isolation　performance　by　effectively　integrating　the　influences　of　VCMR　density,　spring　stiffness,　and　excitation　angle,　achieving　insertion　losses　of　up　to　19.2　dB　across　a　wide　frequency　range.　It　provides　robust　theoretical　support　for　the　design　and　performance　optimization　of　isolation　systems,　with　potential　positive　impacts　on　relevant　engineering　applications.　©　2025　by　the　authors.