导弹与航天运载技术
導彈與航天運載技術
도탄여항천운재기술
MISSILES AND SPACE VEHICLES
2014年
4期
18-22
,共5页
液体火箭发动机%电磁阀%吸力特性%可靠性
液體火箭髮動機%電磁閥%吸力特性%可靠性
액체화전발동궤%전자벌%흡력특성%가고성
Liquid propellant rocket engine%Solenoid valve%Magnetic suction characteristics%Reliability analysis
以直流螺线管电磁阀为研究对象，利用电磁有限元软件Ansoft Maxwell对某种直动型电磁阀进行二维建模，并得出磁感应强度、磁力线分布图及静磁场下的吸力特性曲线。用正交设计法通过Ansoft Maxwell软件进行各指标的吸力计算，对得出吸力仿真计算值进行可靠性评估和因素分析；通过试验测试得到电磁阀吸力数据，对得出的吸力实测值也进行可靠性评估；后续对电磁阀吸力仿真计算值的可靠性评估和吸力实测值的可靠性评估进行了对比和分析。结果表明，通过改进仿真方法及缩小仿真计算时各因素取值范围，吸力仿真计算结果能真实地反映吸力可靠性。
以直流螺線管電磁閥為研究對象，利用電磁有限元軟件Ansoft Maxwell對某種直動型電磁閥進行二維建模，併得齣磁感應彊度、磁力線分佈圖及靜磁場下的吸力特性麯線。用正交設計法通過Ansoft Maxwell軟件進行各指標的吸力計算，對得齣吸力倣真計算值進行可靠性評估和因素分析；通過試驗測試得到電磁閥吸力數據，對得齣的吸力實測值也進行可靠性評估；後續對電磁閥吸力倣真計算值的可靠性評估和吸力實測值的可靠性評估進行瞭對比和分析。結果錶明，通過改進倣真方法及縮小倣真計算時各因素取值範圍，吸力倣真計算結果能真實地反映吸力可靠性。
이직류라선관전자벌위연구대상，이용전자유한원연건Ansoft Maxwell대모충직동형전자벌진행이유건모，병득출자감응강도、자력선분포도급정자장하적흡력특성곡선。용정교설계법통과Ansoft Maxwell연건진행각지표적흡력계산，대득출흡력방진계산치진행가고성평고화인소분석；통과시험측시득도전자벌흡력수거，대득출적흡력실측치야진행가고성평고；후속대전자벌흡력방진계산치적가고성평고화흡력실측치적가고성평고진행료대비화분석。결과표명，통과개진방진방법급축소방진계산시각인소취치범위，흡력방진계산결과능진실지반영흡력가고성。
A direct current solenoid valve was studied in this paper. Adopting finite element analysis software “Ansoft Maxwell” to build the 2D models of the solenoid valve, the magnetic induction intensity, mangnetic lines and suction curves under static magnet field were gained. The electromagnet suctions of all targets were calculated by orthogonal design method, using Ansoft Maxwell software; and then the reliability evaluation and factor analysis were applied on the simulation results. Also, the reliability evaluation was applied on the electromagnet suction data which were gained by testing. Finally, the simulation results and test data of electromagnet suction were compared and analyzed. The results proved that, after improving the simulation methods and narrowing down the range of each factor, the simulation results can authentically reflect the suction reliability.
