LIPS-300离子推力器为兰州空间技术物理研究所自主研制的双模式离子推力器。推力器在轨运行寿命是决定其是否能够满足未来航天使命需求的关键因素之一。根据未来航天任务对LIPS-300离子推力器系统寿命的要求,即采用LIPS-300离子推力器...LIPS-300离子推力器为兰州空间技术物理研究所自主研制的双模式离子推力器。推力器在轨运行寿命是决定其是否能够满足未来航天使命需求的关键因素之一。根据未来航天任务对LIPS-300离子推力器系统寿命的要求,即采用LIPS-300离子推力器完成所有在轨任务所需要的时间为10 098 h。因此,为了准确预测LIPS-300离子推力器运行过程中其关键部组件单点失效的栅极组件寿命,文中建立了LIPS-300离子推力器栅极组件寿命模型,利用数值仿真计算的方法(PIC/MCC)预测了推力器分别单独工作在210 m N和80 m N时栅极发生失效所对应的寿命,并分析了关键失效模式,同时计算了推力器在大推力210 m N模式下工作6 000 h后,继续在小推力模式80 m N工况下栅极对应的寿命和关键失效模式。另外,分析了不同工况下LIPS-300离子推力器栅极寿命是否满足未来航天使命的寿命需求,即安全裕度。数值结果显示,LIPS-300离子推力器分别单独工作在210 m N和80 m N时,其栅极工作寿命分别为16 064.3、26 633.2 h,安全裕度分别为1.3、2.2,两种情况对应的关键失效失效模式均为电子反流失效;LIPS-300离子推力器在210 m N大推力模式下工作6 000 h后,继续在小推力80 m N下工作,此时对应的寿命约为22 064.3 h,安全裕度为1.8,关键失效模式为电子反流失效;推力器单独工作在210 m N和80 m N及双模式下工作时的安全裕度分别为1.6、2.6和2.2。展开更多
Accelerator grid structural and electron backstreaming failures are the most important factors affecting the ion thruster＇s lifetime.During the thruster＇s operation,Charge Exchange Xenon（CEX） ions are generated fr...Accelerator grid structural and electron backstreaming failures are the most important factors affecting the ion thruster＇s lifetime.During the thruster＇s operation,Charge Exchange Xenon（CEX） ions are generated from collisions between plasma and neutral atoms.Those CEX ions grid＇s barrel and wall frequently,which cause the failures of the grid system.In order to validate whether the 20 cm Lanzhou Ion Propulsion System（LIPS-200） satisfies China＇s communication satellite platform＇s application requirement for North-South Station Keeping（NSSK）,this study analyzed the measured depth of the pit/groove on the accelerator grid＇s wall and aperture diameter＇s variation and estimated the operating lifetime of the ion thruster.Different from the previous method,in this paper,the experimental results after the 5500 h of accumulated operation of the LIPS-200 ion thruster are presented firstly.Then,based on these results,theoretical analysis and numerical calculations were firstly performed to predict the on-orbit lifetime of LIPS-200.The results obtained were more accurate to calculate the reliability and analyze the failure modes of the ion thruster.The results indicated that the predicted lifetime of LIPS-200＇s was about 13218.1 h which could satisfy the required lifetime requirement of 11000 h very well.展开更多
The distribution of the thermal effects of the ion thruster plume are essential for estimating the influence of the thruster plume, improving the layout of the spacecraft, and for the thermal shielding of critical sen...The distribution of the thermal effects of the ion thruster plume are essential for estimating the influence of the thruster plume, improving the layout of the spacecraft, and for the thermal shielding of critical sensitive components. In order to obtain the heat flow distribution in the plume of the LIPS-200 xenon ion thruster, an experimental study of the thermal effects of the plume has been conducted in this work,with a total heat flow sensor and a radiant heat flow sensor over an axial distance of 0.5–0.9 m and a thruster angle of 0°–60°. Combined with a Faraday probe and a retarding potential analyzer, the thermal accommodation coefficient of the sensor surface in the plume is available. The results of the experiment show that the xenon ion thruster plume heat flow is mainly concentrated within a range of15°. The total and radial heat flow of the plume downstream of the thruster gradually decreases along the axial and radial directions, with the corresponding values of 11.78 k W m^(-2) and 0.3 k W m^(-2) for the axial 0.5 m position, respectively. At the same position, the radiation heat flow accounts for a very small part of the total heat flow, approximately 3%–5%. The thermal accommodation factor is0.72–0.99 over the measured region. Furthermore, the PIC and DSMC methods based on the Maxwell thermal accommodation coefficient model(EX-PWS) show a maximum error of 28.6% between simulation and experiment for LIPS-200 ion thruster plume heat flow, which, on the one hand, provides an experimental basis for studying the interaction between the ion thruster and the spacecraft, and on the other hand provides optimization of the ion thruster plume simulation model.展开更多
文摘LIPS-300离子推力器为兰州空间技术物理研究所自主研制的双模式离子推力器。推力器在轨运行寿命是决定其是否能够满足未来航天使命需求的关键因素之一。根据未来航天任务对LIPS-300离子推力器系统寿命的要求,即采用LIPS-300离子推力器完成所有在轨任务所需要的时间为10 098 h。因此,为了准确预测LIPS-300离子推力器运行过程中其关键部组件单点失效的栅极组件寿命,文中建立了LIPS-300离子推力器栅极组件寿命模型,利用数值仿真计算的方法(PIC/MCC)预测了推力器分别单独工作在210 m N和80 m N时栅极发生失效所对应的寿命,并分析了关键失效模式,同时计算了推力器在大推力210 m N模式下工作6 000 h后,继续在小推力模式80 m N工况下栅极对应的寿命和关键失效模式。另外,分析了不同工况下LIPS-300离子推力器栅极寿命是否满足未来航天使命的寿命需求,即安全裕度。数值结果显示,LIPS-300离子推力器分别单独工作在210 m N和80 m N时,其栅极工作寿命分别为16 064.3、26 633.2 h,安全裕度分别为1.3、2.2,两种情况对应的关键失效失效模式均为电子反流失效;LIPS-300离子推力器在210 m N大推力模式下工作6 000 h后,继续在小推力80 m N下工作,此时对应的寿命约为22 064.3 h,安全裕度为1.8,关键失效模式为电子反流失效;推力器单独工作在210 m N和80 m N及双模式下工作时的安全裕度分别为1.6、2.6和2.2。
文摘Accelerator grid structural and electron backstreaming failures are the most important factors affecting the ion thruster＇s lifetime.During the thruster＇s operation,Charge Exchange Xenon（CEX） ions are generated from collisions between plasma and neutral atoms.Those CEX ions grid＇s barrel and wall frequently,which cause the failures of the grid system.In order to validate whether the 20 cm Lanzhou Ion Propulsion System（LIPS-200） satisfies China＇s communication satellite platform＇s application requirement for North-South Station Keeping（NSSK）,this study analyzed the measured depth of the pit/groove on the accelerator grid＇s wall and aperture diameter＇s variation and estimated the operating lifetime of the ion thruster.Different from the previous method,in this paper,the experimental results after the 5500 h of accumulated operation of the LIPS-200 ion thruster are presented firstly.Then,based on these results,theoretical analysis and numerical calculations were firstly performed to predict the on-orbit lifetime of LIPS-200.The results obtained were more accurate to calculate the reliability and analyze the failure modes of the ion thruster.The results indicated that the predicted lifetime of LIPS-200＇s was about 13218.1 h which could satisfy the required lifetime requirement of 11000 h very well.
基金National Natural Science Foundation of China (No. 12005087)the Science and Technology Program of Gansu Province (Nos. 2006ZCTF0054, HTKJ2019KL510003, and 20JR10RA478)。
文摘The distribution of the thermal effects of the ion thruster plume are essential for estimating the influence of the thruster plume, improving the layout of the spacecraft, and for the thermal shielding of critical sensitive components. In order to obtain the heat flow distribution in the plume of the LIPS-200 xenon ion thruster, an experimental study of the thermal effects of the plume has been conducted in this work,with a total heat flow sensor and a radiant heat flow sensor over an axial distance of 0.5–0.9 m and a thruster angle of 0°–60°. Combined with a Faraday probe and a retarding potential analyzer, the thermal accommodation coefficient of the sensor surface in the plume is available. The results of the experiment show that the xenon ion thruster plume heat flow is mainly concentrated within a range of15°. The total and radial heat flow of the plume downstream of the thruster gradually decreases along the axial and radial directions, with the corresponding values of 11.78 k W m^(-2) and 0.3 k W m^(-2) for the axial 0.5 m position, respectively. At the same position, the radiation heat flow accounts for a very small part of the total heat flow, approximately 3%–5%. The thermal accommodation factor is0.72–0.99 over the measured region. Furthermore, the PIC and DSMC methods based on the Maxwell thermal accommodation coefficient model(EX-PWS) show a maximum error of 28.6% between simulation and experiment for LIPS-200 ion thruster plume heat flow, which, on the one hand, provides an experimental basis for studying the interaction between the ion thruster and the spacecraft, and on the other hand provides optimization of the ion thruster plume simulation model.
