CAJ | 학술논문

主要针对喷管进行高低燃温组合推进剂与纯高燃温推进剂下的喉衬烧蚀实验分析，低燃温推进剂为丁羟低温推进剂和SCH?12低温推进剂。实验研究表明，丁羟低温推进剂和高温推进剂组合推进剂的烧蚀率为0．112 mm／s，SCH?12低温推进剂和高温推进剂为0．115 mm／s，纯高燃温推进剂的烧蚀率为0．133 mm／s，证明了高低燃温组合推进剂降低喉衬烧蚀的有效性与可行性。分析了然后对不同含量低燃温推进剂对比冲性能的影响，结果显示，使用比冲下降小、燃温低的推进剂能有效降低喉衬烧蚀，并对发动机比冲影响较小。
주요침대분관진행고저연온조합추진제여순고연온추진제하적후츤소식실험분석，저연온추진제위정간저온추진제화SCH?12저온추진제。실험연구표명，정간저온추진제화고온추진제조합추진제적소식솔위0．112 mm／s，SCH?12저온추진제화고온추진제위0．115 mm／s，순고연온추진제적소식솔위0．133 mm／s，증명료고저연온조합추진제강저후츤소식적유효성여가행성。분석료연후대불동함량저연온추진제대비충성능적영향，결과현시，사용비충하강소、연온저적추진제능유효강저후츤소식，병대발동궤비충영향교소。
The ablation experiment of nozzle throat?insert by using pure?high temperature propellant and high?low temperature combined propellant were conducted,and low temperature propellants include HTPB and SCH?12 propellant. The results of experi?ments indicate that the ablation rate of HTPB and pure?high temperature combined propellant is 0.112 mm/s,and that of SCH?12 and high temperature combined propellant is 0.115 mm/s,and that of pure?high temperature propellant is 0.133mm/s.These results prove the validity and feasibility of reducing the ablation rate of by using high and low temperature combined propellant.Then the in?fluence of special impulse in different mass low temperature combined propellant was analyzed,the results show that when using low temperature and little specific impulse propellant,ablation of throat?insert can be reduced effectively,and the specific impulse of mo?tor is less affected..