火箭推进

上面级是介于运载火箭与航天器之间的相对独立的一级,具备轨道转移能力,可将有效载荷精确送入预定轨道。上面级是提高火箭运载能力和提升任务适应性的有效途径,上面级发动机是实现该目标的关键。长期在轨的高性能上面级,要求主动力具备比冲高、空间可长期贮存和高可靠性等能力。针对此技术需求,对比分析了上面级发动机的系统方案; 设计了采用泵压膨胀循环、双涡轮泵串联的30 kN上面级发动机系统方案; 重点介绍了推力室、涡轮泵和发动机总装集成等关键组件的研究进展。研究表明:液氧甲烷推进剂非常适用于长期在轨上面级发动机; 闭式膨胀循环发动机系统是长期在轨上面级动力系统方案的首选; 推力室和涡轮泵等组件的研制结果,初步证明了发动机系统及组件方案的可行性; 发动机总装和演示试验方案设计工作,为深入开展发动机系统技术研究打下了良好基础。

The upstage is an relatively independent stage between the launch vehicle and the spacecraft, it has the ability of orbit transfer and can accurately send the payload into predetermined orbit. The upstage is an effective way to improve the carrying capacity and adaptability of rocket, and the upstage engine is the key to achieve this goal. The upstage with high performance and long-term on orbit needs the main engine with the capabilities on high specific impulse, long-term storage in space and high reliability. Based on those requirements, this paper compared and analyzed the system scheme of the upstage engine. It designed the system scheme of 30 kN engine of the upstage with expander cycle and double turbo-pump, also introduced the research progress of key technologies including the combustion chamber, turbo-pump and engine system integration.The results show that LOX/methane propellant is suitable for long-term on orbit upstage engine. The closed expander cycle engine system is the best choice for long-term on orbit upstage power system; the research results of combustion chamber, turbo-pump and other components have preliminarily proved the feasibility of design scheme of engine system and components. The design of engine prototype assembly and demonstrate scheme lays a good foundation for further research on engine system technology.

引言
1 液氧/甲烷的特点
2 发动机系统方案
3 推力室
4 涡轮泵
5 发动机总装集成
6 结论

表1 系统循环方案对比<br/>Tab.1 Contrast of engine system power cycle

表1 系统循环方案对比
Tab.1 Contrast of engine system power cycle

图1 液氧甲烷发动机系统原理图<br/>Fig.1 System schematic of LOX/methane engine

图1 液氧甲烷发动机系统原理图
Fig.1 System schematic of LOX/methane engine

图2 发动机总体布局示意图<br/>Fig.2 Schematic layout of LOX/methane engine

图2 发动机总体布局示意图
Fig.2 Schematic layout of LOX/methane engine

表2 30 kN液氧甲烷上面级发动机主要参数<br/>Tab.2 Main parameter of 30 kN upstage LOX/methane engine

表2 30 kN液氧甲烷上面级发动机主要参数
Tab.2 Main parameter of 30 kN upstage LOX/methane engine

图3 推力室身部和喷管延伸段示意图(单段式再生冷却方案)<br/>Fig.3 Combustion chamber and nozzle extension(single-stage regenerative cooling design scheme)

图3 推力室身部和喷管延伸段示意图(单段式再生冷却方案)
Fig.3 Combustion chamber and nozzle extension(single-stage regenerative cooling design scheme)

图4 推力室
Fig.4 Combustion chamber

图5 推力室头部示意和产品<br/>Fig.5 Top of combustion chamber

图5 推力室头部示意和产品
Fig.5 Top of combustion chamber

图6 喷嘴和喷注器产品照片<br/>Fig.6 Nozzle and injector

图6 喷嘴和喷注器产品照片
Fig.6 Nozzle and injector

图7 推力室身部<br/>Fig.7 Body of combustion chamber

图7 推力室身部
Fig.7 Body of combustion chamber

图8 推力室挤压试验系统示意图<br/>Fig.8 Combustion chamber extrusion test system

图8 推力室挤压试验系统示意图
Fig.8 Combustion chamber extrusion test system

表3 试验设计参数<br/>Tab.3 Test design parameter

表3 试验设计参数
Tab.3 Test design parameter

图9 推力室工作照片
Fig.9 Combustion chamber

图10 推力室试车后<br/>Fig.10 Combustion chamber after test

图10 推力室试车后
Fig.10 Combustion chamber after test

图11 喷注面压力曲线<br/>Fig.11 Pressure curve of injection surface

图11 喷注面压力曲线
Fig.11 Pressure curve of injection surface

图12 甲烷(左)和液氧(右)涡轮泵示意图<br/>Fig.12 Methane(left)and liquid oxygen(right)turbo pumps

图12 甲烷(左)和液氧(右)涡轮泵示意图
Fig.12 Methane(left)and liquid oxygen(right)turbo pumps

图13 甲烷(左)和液氧(右)涡轮泵照片<br/>Fig.13 Methane(left)and liquid oxygen(right)turbo pumps

图13 甲烷(左)和液氧(右)涡轮泵照片
Fig.13 Methane(left)and liquid oxygen(right)turbo pumps

图14 甲烷涡轮泵效率—转速曲线<br/>Fig.14 Efficiency—speed curve of methane turbo pump

图14 甲烷涡轮泵效率—转速曲线
Fig.14 Efficiency—speed curve of methane turbo pump

图15 液氧涡轮泵效率—转速曲线<br/>Fig.15 Efficiency—speed curve of liquid oxygen turbo pump

图15 液氧涡轮泵效率—转速曲线
Fig.15 Efficiency—speed curve of liquid oxygen turbo pump

图16 30 kN液氧甲烷上面级发动机全系统原理样机<br/>Fig.16 Schematic prototype of the 30 kN upstage LOX/methane engine

图16 30 kN液氧甲烷上面级发动机全系统原理样机
Fig.16 Schematic prototype of the 30 kN upstage LOX/methane engine

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备注

引言

1 液氧/甲烷的特点

2 发动机系统方案

3 推力室

4 涡轮泵

5 发动机总装集成

6 结论

期刊信息