高室压大流量姿轨控发动机中高空模拟试验扩压器性能与结构方案设计  

Performance and structural scheme design of the diffuser for attitude and orbit control engines with high chamber pressure and large flow rate in mid-high-altitude simulation test

作　　者：超力德 郭红杰[1] 张元 徐勇 梁国柱[1] CHAO Lide;GUO Hongjie;ZHANG Yuan;XU Yong;LIANG Guozhu(School of Astronautics,Beihang University,Beijing 102206,China)

机构地区：[1]北京航空航天大学宇航学院,北京102206

出　　处：《航空动力学报》2024年第8期163-177,共15页Journal of Aerospace Power

摘　　要：采用热力计算方法、正激波理论、传热理论以及强度理论等方法,开展了液体姿轨控发动机与圆柱形扩压器性能与结构方案匹配设计和理论分析。从扩压器的性能、主要尺寸、换热方式、强度和稳定性校核等方面,给出了确定其性能与结构方案的设计计算方法和流程。计算给出了圆柱形扩压器面积比、燃烧室压力比、真空舱压力比以及燃气等熵指数对扩压器的主要尺寸和工作特性的影响曲线。针对推力为5 000 N的某NTO/MMH液体姿轨控发动机的试验需求,设计了内径为1.1 m、长度为8 m、内壁厚度和冷却夹层厚度均为10 mm的圆柱形扩压器,工作包线显示其具备在发动机燃烧室压强为1~5 MPa、最大流量为1~3 kg/s且模拟工作高度为中高空30~60 km高度范围内开展相关试验的能力。研究表明,在扩压器入流和正激波前后引入燃气热力计算的设计方法可获得更加准确的冷却计算所需的燃气热物性参数,因考虑了高温燃气的化学反应从而获得更合理的性能与结构匹配方案,也便于确定已有扩压器的试验能力范围。The thermodynamic calculation method,normal shock wave theory,heat transfer theory,and strength theory were adopted to carry out the matching design and theoretical analysis of the performance and structural scheme of liquid attitude and orbit control engines and cylindrical diffusers.A design calculation method and procedure for determining the performance and structural scheme of diffusers was presented from the aspects of its performance,main dimensions,heat transfer mode,strength and stability verification.Influence curves of the area ratio of cylindrical diffusers,combustion chamber pressure ratio,vacuum chamber pressure ratio,and gas isentropic index on the main dimensions and operating characteristics of diffusers were obtained.A cylindrical diffuser with an inner diameter of 1.1 m,a length of 8 m,and an inner wall thickness and cooling jacket width of 10 mm was designed for the testing requirements of a certain NTO/MMH liquid attitude and orbit control engine with a thrust of 5 000 N.The working envelope demonstrated the ability to conduct relevant tests within the engine combustion chamber pressure range of 1—5 MPa,maximum flowrate range of 1—3 kg/s,and simulated working altitude range of 30—60 km.The research showed that using the design method for gas thermodynamic calculation introduced into the diffuser inflow before and after the normal shock wave,more accurate gas thermodynamic parameters required for cooling calculations can be obtained.In consideration of the chemical reaction of high-temperature gas,a more reasonable performance and structural matching scheme can be obtained using the method,making it convenient to determine the test capacity range of existing diffusers.

关 键 词：姿轨控发动机 高空模拟试验 圆柱形扩压器 性能计算 方案设计 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]