A　multi-physical　field　numerical　model　considering　the　thermo-chemical　and　mechanical　effects　was　used　to　simulate　the　curing　process　of　a　nitrate　ester　plasticized　polyether　(NEPE)　solid　propellant.　The　curing　process　of　solid　rocket　propellants　was　detected　through　physical　experiments　such　as　differential　scanning　calorimetry　(DSC)　and　heat　transfer.　The　variation　laws　and　distribution　patterns　of　the　temperature　field　and　curing　degree　field　during　the　propellant　curing　process　were　numerically　and　experimentally　analyzed,　and　the　residual　and　contact　stresses　caused　by　the　effects　of　temperature,　chemical　reaction,　and　pressure　were　studied.　The　results　showed　that　the　internal　temperature　field　of　the　NEPE　propellant　during　the　curing　process　was　closely　related　to　the　curing　time.　At　about　3　d　of　curing　time,　the　propellant　curing　rate　was　the　fastest,　and　the　temperature　reached　a　maximum　value　of　58　degrees　C.　During　curing,　the　NEPE　solid　propellant　produces　an　unevenly　distributed　temperature　field　and　curing　degree　field　distribution,　which　aggravates　the　residual　stress.　The　molding　pressure　can　reduce　the　residual　stress;　however,　when　the　pressure　exceeds　approximately　3　MPa,　it　causes　extrusion　stress　on　the　interface　layer　between　propellant-to-case　and　propellant-to-core　mold.　Based　on　the　numerical　calculation　results,　an　optimal　pressure　calculation　formula　for　multiple　parameters　that　can　quickly　estimate　the　optimal　pressure　is　derived.