The　thermal　chemical　coupling　model　was　used　to　characterize　the　thermal　conductivity　and　curing　kinetic　reaction,　and　the　thermal　parameters　and　density　of　nitrate　plasticized　polyether　(NEPE)　propellant　were　measured　by　physical　tests.　The　distribution　and　evolution　of　temperature　field　and　curing　degree　of　NEPE　propellant　during　curing　were　studied.　The　results　show　that　due　to　the　difference　between　the　heat　generation　rate　of　propellant　curing　reaction　and　the　external　heat　transfer　rate,　the　distribution　of　internal　temperature　field　and　curing　degree　field　is　uneven　in　the　curing　process.　When　the　curing　time　is　1　~　4　days,　the　temperature　at　the　center　is　higher　(max.　57.6　℃)　and　the　temperature　at　the　outer　side　is　lower.　When　the　curing　time　is　greater　than　or　equal　to　5　days,　the　temperature　slowly　tends　to　be　in　equilibrium　with　the　ambient　temperature　(50　℃).　The　curing　rate　of　propellant　is　slow　when　the　curing　time　is　less　than　1　day　and　more　than　4　days;　When　the　curing　time　is　2~4　days,　the　curing　rate　is　fast.　The　m　number　of　solid　rocket　motor　has　a　certain　impact　on　the　temperature　and　curing　rate　of　propellant　in　the　curing　process.　The　greater　the　m　number,　the　higher　the　maximum　temperature　of　propellant,　and　the　greater　the　temperature　difference.　The　temperature　difference　will　lead　to　the　difference　in　the　internal　curing　rate　of　propellant　grain,　which　will　cause　a　delay　in　the　curing　of　propellant　and　increase　the　time　it　takes　to　reach　the　specified　curing　degree.　©　2024　Journal　of　Solid　Rocket　Technology.　All　rights　reserved.