火箭推进

液氧/甲烷轨姿控推进系统集成演示试验

程诚^1,2,周海清^1,2,田桂^1,2,熊靖宇^1,2,周国峰^1,2,曾夜明^1,2

(1.上海空间推进研究所,上海 201112; 2.上海空间发动机工程技术研究中心,上海 201112)

System integration and hot-fire test of liquid oxygen/liquid methane rocket engine for orbit maneuver and attitude control

CHENG Cheng^1,2, ZHOU Haiqing^1,2, TIAN Gui^1,2, XIONG Jingyu^1,2, ZHOU Guofeng^1,2, ZENG Yeming^1,2

(1. Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2. Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China)

Keywords： space propulsion system; liquid oxygen/liquid methane; orbit maneuver engine; attitude control engine; hot-fire test

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为验证液氧/甲烷轨姿控一体化推进系统涉及的主要关键技术和安全操作流程,上海空间推进研究所研制了国内首款氦气恒压挤压式液氧甲烷推进系统演示样机。历时3年,演示样机于2021年底顺利完成多轮次地面热试车考核,系统运行平稳,轨/姿控发动机工作协调、产品状态良好。介绍了演示样机的设计方案、研制历程和集成演示试验结果,以及轨/姿控发动机的设计与试验情况。液氧甲烷推进系统累计完成48次/约6 000 s系统冷/热态试验考核,配套的5 kN轨控发动机累计完成点火工作40次/1 860 s,配套的150 N/25 N姿控发动机累计完成稳态工作1 690 s/脉冲点火约1 250次。演示样机热试车的成功,标志着我国液氧甲烷空间推进系统实现了从“0”到“1”的突破,为后续型号工程应用奠定了基础,也为我国液体空间动力的升级换代和可持续发展提供了有力支撑。

In order to validate the key technologies and safe operating procedures, the first integrated demonstration prototype of pressure-fed liquid oxygen /liquid methane(LO2/LCH4)propulsion system using helium for orbit maneuver and attitude control in China has been developed by Shanghai Institute of Space Propulsion(SISP)from 2019 for the future in-space vehicles. After 3 years, the demonstration prototype was successfully completed multiple rounds of ground hot-fire tests at the end of 2021, with stable system operation, coordinated engine work and good product condition. The design scheme, development process and test results of the demonstration prototype, as well as the design and test of the orbit/attitude control engine, are introduced in this paper. The integrated propulsion system has performed a total of 48 times/about 6 000 s cold state and hot-fire operations. The 5 kN orbit maneuver engine has completed the hot-fire working for 40 times /1 860 s, and the 150 N and 25 N attitude control engines have completed steady-state hot-fire for 1 690 s /pulse ignition for about 1 250 times. The successful hot-fire tests of the demonstration prototype indicates that the LO2/LCH4 space propulsion system in China has achieved a breakthrough from “0” to “1”, which provides a foundation for the subsequent flight applications and a support for the sustainable development of national liquid space propulsion technology.

引言
1 液氧/ 甲烷推进系统演示样机
2 研制历程
3 发动机设计与试验
4 集成演示热试车
5 结论

图1 液氧/甲烷推进系统演示样机<br/>Fig.1 Demonstration prototype of LOx/LCH4propulsion system

图1 液氧/甲烷推进系统演示样机
Fig.1 Demonstration prototype of LOx/LCH4propulsion system

图2 液氧/甲烷推进系统演示样机原理图<br/>Fig.2 Schematic diagram of demonstration prototype for LOx/LCH4 propulsion system

图2 液氧/甲烷推进系统演示样机原理图
Fig.2 Schematic diagram of demonstration prototype for LOx/LCH4 propulsion system

图3 COP电火花点火控制系统实物照片<br/>Fig.3 Photograph of the coil-on-plug ignition system

图3 COP电火花点火控制系统实物照片
Fig.3 Photograph of the coil-on-plug ignition system

表1 液氧/甲烷推进系统演示样机主要技术参数<br/>Tab.1 Main technical specifications of LOx/LCH4propulsion system prototype

表1 液氧/甲烷推进系统演示样机主要技术参数
Tab.1 Main technical specifications of LOx/LCH4propulsion system prototype

图4 液氧/甲烷推进系统冷试样机系统液氮试验<br/>Fig.4 Liquid nitrogen test of LOx/LCH4 propulsion system prototype(for cold flow test)

图4 液氧/甲烷推进系统冷试样机系统液氮试验
Fig.4 Liquid nitrogen test of LOx/LCH4 propulsion system prototype(for cold flow test)

图5 液氧/甲烷推进系统热试样机液甲烷加注<br/>Fig.5 Liquid methane loading of LOx/LCH4propulsion system prototype

图5 液氧/甲烷推进系统热试样机液甲烷加注
Fig.5 Liquid methane loading of LOx/LCH4propulsion system prototype

表2 液氧/甲烷推进系统演示样机研制历程<br/>Tab.2 Development Pocess of LOx/LCH4 propulsion system prototype

表2 液氧/甲烷推进系统演示样机研制历程
Tab.2 Development Pocess of LOx/LCH4 propulsion system prototype

图6 5kN液氧/甲烷轨控发动机<br/>Fig.6 5kN LOx/LCH4 engine for orbit maneuver

图6 5kN液氧/甲烷轨控发动机
Fig.6 5kN LOx/LCH4 engine for orbit maneuver

图7 5kN发动机模拟火炬点火器稳态热试车<br/>Fig.7 Steady-state hot-fire test of simulated torch igniter for 5 kN LOx/LCH4 engine

图7 5kN发动机模拟火炬点火器稳态热试车
Fig.7 Steady-state hot-fire test of simulated torch igniter for 5 kN LOx/LCH4 engine

图8 5kN发动机(3D打印水冷燃烧室)稳态热试车<br/>Fig.8 Steady-state hot-fire test of 5 kN LOx/LCH4 engine with 3D printed water cooling combustion chamber

图8 5kN发动机(3D打印水冷燃烧室)稳态热试车
Fig.8 Steady-state hot-fire test of 5 kN LOx/LCH4 engine with 3D printed water cooling combustion chamber

图9 5kN发动机(铌钨合金燃烧室)稳态热试车<br/>Fig.9 Steady-state hot-fire test of 5 kN LOx/LCH4 engine with niobium-tungsten alloy combustion chamber

图9 5kN发动机(铌钨合金燃烧室)稳态热试车
Fig.9 Steady-state hot-fire test of 5 kN LOx/LCH4 engine with niobium-tungsten alloy combustion chamber

图10 150N液氧/甲烷姿控发动机<br/>Fig.10 150 N LOx/LCH4 engine for attitude control

图10 150N液氧/甲烷姿控发动机
Fig.10 150 N LOx/LCH4 engine for attitude control

图11 150N发动机(3D打印水冷燃烧室)稳态热试车<br/>Fig.11 Steady-state hot-fire test of 150N LOx/LCH4 engine with 3D printed water cooling combustion chamber

图11 150N发动机(3D打印水冷燃烧室)稳态热试车
Fig.11 Steady-state hot-fire test of 150N LOx/LCH4 engine with 3D printed water cooling combustion chamber

图12 150N发动机(铌钨合金燃烧室)稳态热试车<br/>Fig.12 Steady-state hot-fire test of 150N LOx/LCH4 engine with niobium-tungsten alloy combustion chamber

图12 150N发动机(铌钨合金燃烧室)稳态热试车
Fig.12 Steady-state hot-fire test of 150N LOx/LCH4 engine with niobium-tungsten alloy combustion chamber

图13 25N姿控发动机(层板方案)及其稳态热试车<br/>Fig.13 25N LOx/LCH4 engine(using platelet diffusion bonding process)and hot-fire test

图13 25N姿控发动机(层板方案)及其稳态热试车
Fig.13 25N LOx/LCH4 engine(using platelet diffusion bonding process)and hot-fire test

图14 25N姿控发动机(机加方案)及其稳态热试车<br/>Fig.14 25NLOx/LCH4 engine(using traditional machining process)and hot-fire test

图14 25N姿控发动机(机加方案)及其稳态热试车
Fig.14 25NLOx/LCH4 engine(using traditional machining process)and hot-fire test

图15 25N姿控发动机(改进方案)及其稳态热试车<br/>Fig.15 Optimized 25 N LOx/LCH4 engine andhot-fire test

图15 25N姿控发动机(改进方案)及其稳态热试车
Fig.15 Optimized 25 N LOx/LCH4 engine andhot-fire test

图16 液氧/甲烷推进系统演示样机贮箱加注及预冷流程<br/>Fig.16 Tank loading and feed line precooling process of LOx/LCH4 propulsion system prototype

图16 液氧/甲烷推进系统演示样机贮箱加注及预冷流程
Fig.16 Tank loading and feed line precooling process of LOx/LCH4 propulsion system prototype

表3 液氧/甲烷推进系统演示样机集成热试车历程<br/>Tab.3 Detailed hot-fire test process of LOx/LCH4 propulsion system prototype

表3 液氧/甲烷推进系统演示样机集成热试车历程
Tab.3 Detailed hot-fire test process of LOx/LCH4 propulsion system prototype

图17 液氧/甲烷推进系统演示样机集成热试车<br/>Fig.17 Hot-fire test of LOx/LCH4 propulsion system prototype

图17 液氧/甲烷推进系统演示样机集成热试车
Fig.17 Hot-fire test of LOx/LCH4 propulsion system prototype

图18 液氧/甲烷推进系统演示样机集成热试车典型压力/温度试验曲线<br/>Fig.18 Typical pressure-temperature curves of hot-fire test for LOx/LCH4 propulsion system prototype

图18 液氧/甲烷推进系统演示样机集成热试车典型压力/温度试验曲线
Fig.18 Typical pressure-temperature curves of hot-fire test for LOx/LCH4 propulsion system prototype

图19 演示样机热试车时5kN液氧/甲烷发动机典型工作曲线<br/>Fig.19 Typical work curves of 5 kN LOx/LCH4engine during hot-fire test of prototype

图19 演示样机热试车时5kN液氧/甲烷发动机典型工作曲线
Fig.19 Typical work curves of 5 kN LOx/LCH4engine during hot-fire test of prototype

图20 演示样机热试车时150N发动机典型工作曲线<br/>Fig.20 Typical work curves of 150 N engine during hot-fire test of prototype

图20 演示样机热试车时150N发动机典型工作曲线
Fig.20 Typical work curves of 150 N engine during hot-fire test of prototype

图21 演示样机热试车时25N发动机典型工作曲线<br/>Fig.21 Typical work curves of 25N engine during hot-fire test of prototype

图21 演示样机热试车时25N发动机典型工作曲线
Fig.21 Typical work curves of 25N engine during hot-fire test of prototype

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火箭推进
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引言

1 液氧/ 甲烷推进系统演示样机

2 研制历程

3 发动机设计与试验

4 集成演示热试车

5 结论

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