火箭推进

NASA液氧甲烷集成推进系统热真空试验

(上海空间推进研究所上海空间发动机工程技术研究中心,上海 201112)

Thermal vacuum test of NASA's integrated LO₂/LCH₄ propulsion system

CHENG Cheng,XIONG Jingyu,ZHOU Guofeng,LIN Qingguo

(Shanghai Engineering Research Center of Space Engine, Shanghai Institute of Space Propulsion, Shanghai 201112, China)

Keywords： space propulsion system; liquid oxygen/liquid methane; attitude control propulsion system; thermal vacuum simulation; electric spark ignition

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为降低液氧/甲烷空间推进系统未来应用的技术风险,NASA先后实施了多个研究计划,持续不断地提升液氧/甲烷空间推进技术的成熟度水平。低温推进系统集成试验平台(ICPTA)顺利在梅溪试验站空间推进热真空舱内完成一系列热真空模拟环境下的集成热试车,标志着NASA液氧/甲烷轨姿控一体化推进技术已经具备了在轨飞行验证试验的条件。介绍了ICPTA的研制背景,采用的液氧/甲烷轨姿控一体化推进系统的构成、冷氦加温增压方案和供应管路热控方案。重点讨论了ICPTA热真空模拟试验的具体情况,以及变推力主发动机、姿控动力系统和COP点火系统等核心组件的设计方案、涉及的主要技术问题与试验结果,其成果对于未来星球着陆器的先进低温推进系统的研制具有重要参考价值。

In order to reduce the technical risk of liquid oxygen/liquid methane(LO2/LCH4)propulsion system for the future application, NASA has implemented several research projects to continuously improve the technology readiness level(TRL)of this cryogenic propulsion system.The Integrated Cryogenic Propulsion Test Article(ICPTA)has successfully completed a series of hot-fire tests in the space propulsion thermal vacuum chamber of Plum Brook station, NASA Glenn Research Center.It indicates that NASA's integrated LO2/LCH4 propulsion technologies for the orbit and attitude control have the capability of in-orbit flight test.The development background of ICPTA, the composition of integrated LO2/LCH4 propulsion system, the cold helium system heating and pressurization scheme and thermal control method of feed lines are discussed in detail.Besides, the specific situation of the ICPTA thermal vacuum simulation test is mainly investigated, as well as the design principles, major technical issues and test results of the main engine, attitude control system and Coil-on-Plug ignition system.Its results are valuable for the advanced cryogenic propulsion system development of future planet lander.

引言
1 低温推进系统集成试验平台
2 热真空模拟试验
3 核心组件设计与试验结果
4 结论

图1 低温推进系统集成试验平台<br/>Fig.1 Integrated test platform of cryogenic propulsion system

图1 低温推进系统集成试验平台
Fig.1 Integrated test platform of cryogenic propulsion system

图2 低温推进系统集成试验平台原理图<br/>Fig.2 Schematic diagram of ICPTA

图2 低温推进系统集成试验平台原理图
Fig.2 Schematic diagram of ICPTA

图3 低温姿控机组及其管路TVS热控系统<br/>Fig.3 Cryogenic attitude control system and TVS thermal control system

图3 低温姿控机组及其管路TVS热控系统
Fig.3 Cryogenic attitude control system and TVS thermal control system

图4 氦气热交换器(左)和氦气压力/流量调节面板(右)<br/>Fig.4 Helium heat exchanger(left)and helium regulation & control panel(right)

图4 氦气热交换器(左)和氦气压力/流量调节面板(右)
Fig.4 Helium heat exchanger(left)and helium regulation & control panel(right)

图5 ICPTA在空间推进热真空舱内的安装示意图<br/>Fig.5 Installation diagram of ICPTA in space propulsion thermal vacuum chamber

图5 ICPTA在空间推进热真空舱内的安装示意图
Fig.5 Installation diagram of ICPTA in space propulsion thermal vacuum chamber

图6 ICPTA在模拟热真空环境下热试车照片<br/>Fig.6 ICPTA hot-fire testing under thermal vacuum condition

图6 ICPTA在模拟热真空环境下热试车照片
Fig.6 ICPTA hot-fire testing under thermal vacuum condition

表1 ICPTA的试验<br/>Tab.1 Test activities of ICPTA

表1 ICPTA的试验
Tab.1 Test activities of ICPTA

图7 ICPTA主发动机结构和地面发动机热试车照片<br/>Fig.7 ICPTA main engine(vacuum)and hot-fire test of the sea-level engine

图7 ICPTA主发动机结构和地面发动机热试车照片
Fig.7 ICPTA main engine(vacuum)and hot-fire test of the sea-level engine

图8 ICPTA主发动机高模热试车照片<br/>Fig.8 Hot-fire test of ICPTA main engine under simulated altitude condition

图8 ICPTA主发动机高模热试车照片
Fig.8 Hot-fire test of ICPTA main engine under simulated altitude condition

图9 真空推力125 N液氧甲烷姿控发动机<br/>Fig.9 125 N(vacuum thrust)LO2/LCH4 attitude control engine

图9 真空推力125 N液氧甲烷姿控发动机
Fig.9 125 N(vacuum thrust)LO2/LCH4 attitude control engine

图10 低温姿控发动机入口处的管路充填压力峰<br/>Fig.10 Filling pressure peak at inlet pipe of cryogenic attitude control engine

图10 低温姿控发动机入口处的管路充填压力峰
Fig.10 Filling pressure peak at inlet pipe of cryogenic attitude control engine

图11 125 N姿控发动机脉宽1 s单脉冲试验典型曲线<br/>Fig.11 Typical curve of 1 s monopulse test for 125 N attitude control engine

图11 125 N姿控发动机脉宽1 s单脉冲试验典型曲线
Fig.11 Typical curve of 1 s monopulse test for 125 N attitude control engine

图12 典型的维持液氧/液甲烷入口条件的管路TVS工作<br/>Fig.12 Typical TVS operation for a liquid oxygen/liquid methane pulsing sequence

图12 典型的维持液氧/液甲烷入口条件的管路TVS工作
Fig.12 Typical TVS operation for a liquid oxygen/liquid methane pulsing sequence

图13 高占空比脉冲序列下低温姿控发动机的入口温度<br/>Fig.13 Submerged thermocouple data for high duty cycle test of cryogenic RCS

图13 高占空比脉冲序列下低温姿控发动机的入口温度
Fig.13 Submerged thermocouple data for high duty cycle test of cryogenic RCS

图14 深冷真空条件下姿控发动机脉冲工作时入口温度<br/>Fig.14 Inlet temperature during pulse operation of attitude control engine under cryogenic vacuum conditions

图14 深冷真空条件下姿控发动机脉冲工作时入口温度
Fig.14 Inlet temperature during pulse operation of attitude control engine under cryogenic vacuum conditions

图15 Morpheus项目用火花塞(左)和COP火花塞(右)<br/>Fig.15 Conventional spark plug in Morpheus project(left)and COP plug(right)

图15 Morpheus项目用火花塞(左)和COP火花塞(右)
Fig.15 Conventional spark plug in Morpheus project(left)and COP plug(right)

图16 COP火花塞电性能测试(上)和姿控发动机/火炬点火器高空点火测试(下)<br/>Fig.16 Electrical performance test of COP plug(upper)and attitude simulating hot-fire test of attitude control engine & torch igniter(lower)

图16 COP火花塞电性能测试(上)和姿控发动机/火炬点火器高空点火测试(下)
Fig.16 Electrical performance test of COP plug(upper)and attitude simulating hot-fire test of attitude control engine & torch igniter(lower)