固体火箭技术
固體火箭技術
고체화전기술
JOURNAL OF SOLID ROCKET TECHNOLOGY
2015年
4期
562-565,572
,共5页
唐敏%张岗%史宏斌%高波
唐敏%張崗%史宏斌%高波
당민%장강%사굉빈%고파
背壁绝热层%活化能%指前因子%热导率%比热容%热解
揹壁絕熱層%活化能%指前因子%熱導率%比熱容%熱解
배벽절열층%활화능%지전인자%열도솔%비열용%열해
throat insulator%activation energy%kinetic factor%thermal conductivities%specific heat%pyrolysi
测试了5?II 材料的热物理性能,获得了温度相关的比热容和热导率参数;研究了该材料的分解数学模型,通过热失重实验,获得了热解反应温度和热解动力学参数;通过对 ABAQUS 软件二次开发进行了某长时间工作喉衬背壁的热解数值模拟。结果表明,5?II 材料热解过程主要发生在280~925℃之间,尤其在510~650℃范围内热解速度最快,其活化能约为99.9 kJ/ mol,指前因子为122.7×106/ s;常温至1000℃,5?II 材料的热导率和比热随温度呈“W”型变化;背壁热解数值模拟结果和试验结果较吻合。
測試瞭5?II 材料的熱物理性能,穫得瞭溫度相關的比熱容和熱導率參數;研究瞭該材料的分解數學模型,通過熱失重實驗,穫得瞭熱解反應溫度和熱解動力學參數;通過對 ABAQUS 軟件二次開髮進行瞭某長時間工作喉襯揹壁的熱解數值模擬。結果錶明,5?II 材料熱解過程主要髮生在280~925℃之間,尤其在510~650℃範圍內熱解速度最快,其活化能約為99.9 kJ/ mol,指前因子為122.7×106/ s;常溫至1000℃,5?II 材料的熱導率和比熱隨溫度呈“W”型變化;揹壁熱解數值模擬結果和試驗結果較吻閤。
측시료5?II 재료적열물이성능,획득료온도상관적비열용화열도솔삼수;연구료해재료적분해수학모형,통과열실중실험,획득료열해반응온도화열해동역학삼수;통과대 ABAQUS 연건이차개발진행료모장시간공작후츤배벽적열해수치모의。결과표명,5?II 재료열해과정주요발생재280~925℃지간,우기재510~650℃범위내열해속도최쾌,기활화능약위99.9 kJ/ mol,지전인자위122.7×106/ s;상온지1000℃,5?II 재료적열도솔화비열수온도정“W”형변화;배벽열해수치모의결과화시험결과교문합。
Thermal and physics properties of 5?II material were experimented, and the specific heat and thermal conductivities were obtained. The pyrolysis model was researched. Pyrolysis temperature and kinetic parameters were obtained by thermal loss ex?periment. Pyrolisis simulation on a long working throat was achieved by a user expander film on ABAQUS code. The results show that the pyrolysis temperature domain of 5?II material is between 280 ℃ and 925 ℃ , and the major domain is from 510 ℃ to 650℃ . The activation energy and kinetic factor are 99.9 kJ/ mol and 122.7×106 / s, respectively. Specific heat and thermal conductivi?ties are changed with temperature like ‘W’ from room temperature to 1 000 ℃ . The prediction carbonization depth values are coin?cided with experiment results.