[Background]　Electric　propulsion　systems,　compared　to　traditional　chemical　propulsion,　offer　longer　operational　lifespans　and　lower　fuel　consumption　in　space　missions,　garnering　significant　attention　in　recent　years.　However,　for　high-power　Hall　effect　electric　thrusters　developed　based　on　controlled　fusion　concepts,　measuring　thrust　proves　challenging　due　to　the　high-temperature　environments　required　for　ionizing　propellants　in　electric　thruster,　resulting　in　the　generation　of　hot　plasma　plumes　during　operation.　As　a　result,　traditional　thrust　measurement　methods　are　unable　to　accurately　measure　the　thrust.　[Purpose]　This　study　aims　to　accurately　measure　thrust　during　ground　testing　of　electric　thrusters　for　precise　control　of　the　spacecraft＇s　attitude　and　orbit　maintenance.　[Methods]　Firstly,　a　thrust　measurement　platform　based　on　flexible　beam　structure　was　designed　and　implemented　with　capability　of　measuring　the　thrust　generated　by　electric　thrusters　in　high-temperature.　Simultaneously,　a　calibration　system　was　built　to　verify　the　stability　and　repeatability　of　the　thrust　measurement　results.　Then,　simulation　analysis　was　conducted　on　the　structural　mechanics　and　thermal　coupling　field　of　the　thrust　measurement　system　under　different　operating　conditions.　Finally,　the　variable　specific　impulse　magnetoplasma　rocket　(VASIMR)　was　taken　for　experimental　thrust　measurement　of　its　electric　propulsion　system.　[Results]　The　experimental　results　of　VASIMR　indicate　the　thrust　is　266.5　mN　measured　in　real　time　at　the　central　magnetic　field　intensity　of　0.2　T　with　a　mass　flow　rate　of　20　mg∙s−1.　[Conclusions]　The　thrust　measurement　platform　based　on　the　bending　beam　structure　can　meet　the　measurement　requirements　of　VASIMR,　providing　valuable　references　for　subsequent　experiments.　©　2024　Science　Press.　All　rights　reserved.