固体火箭技术
固體火箭技術
고체화전기술
JOURNAL OF SOLID ROCKET TECHNOLOGY
2009年
6期
654-658
,共5页
李苗苗%汪越%郭效德%宋洪昌%李凤生
李苗苗%汪越%郭效德%宋洪昌%李鳳生
리묘묘%왕월%곽효덕%송홍창%리봉생
固体推进剂%燃烧模型%RDX%AMMO%BAMO
固體推進劑%燃燒模型%RDX%AMMO%BAMO
고체추진제%연소모형%RDX%AMMO%BAMO
solid propellant%combustion mode%RDX%AMMO%BAMO
以详细的气相基元反应机理为基础,建立了RDX和RDX/AMMO-BAMO(80∶20)推进剂的一维、稳态燃烧模型.计算了0.1～10 MPa压强下RDX和RDX/AMMO-BAMO推进剂的燃速、燃烧波结构、气相热反馈等燃烧特性参数.预估的燃速值与实验值吻合得很好,相对误差都在10%以内.计算结果显示,20%AMMO-BAMO共聚物的加入,降低了RDX推进剂的燃速,降低幅度约为42%.
以詳細的氣相基元反應機理為基礎,建立瞭RDX和RDX/AMMO-BAMO(80∶20)推進劑的一維、穩態燃燒模型.計算瞭0.1～10 MPa壓彊下RDX和RDX/AMMO-BAMO推進劑的燃速、燃燒波結構、氣相熱反饋等燃燒特性參數.預估的燃速值與實驗值吻閤得很好,相對誤差都在10%以內.計算結果顯示,20%AMMO-BAMO共聚物的加入,降低瞭RDX推進劑的燃速,降低幅度約為42%.
이상세적기상기원반응궤리위기출,건립료RDX화RDX/AMMO-BAMO(80∶20)추진제적일유、은태연소모형.계산료0.1～10 MPa압강하RDX화RDX/AMMO-BAMO추진제적연속、연소파결구、기상열반궤등연소특성삼수.예고적연속치여실험치문합득흔호,상대오차도재10%이내.계산결과현시,20%AMMO-BAMO공취물적가입,강저료RDX추진제적연속,강저폭도약위42%.
The steady-state combustion of RDX and mixtures of RDX/AMMO-BAMO characteristics include the burning rate, pressure exponent, combustion wave structure and heat feedback were calculated. Computed combustion characteristics are in reasonable agreement with the experiment result. The calculated results show that the addition of AMMO-BAMO copolymer result in a decrease of the burning rate by 42%.
