摘要
为了对取消散热板后的12.5 kW霍尔推力器的热设计优化提供工程指引,计算了推力器热耗并校准了热模型,之后采用有限元仿真结合热平衡试验验证对12.5 kW霍尔推力器的不同热设计措施的有效性进行了分析。结果显示,在取消散热板后,推力器各部件平均温升达到50~150℃,在考虑推力器主要的热量传递路径后,提出6种热设计措施并分别进行仿真分析。分析结果表明,措施4和措施6,即阻断空心阴极与内线圈的辐射热交换以及提高导磁底座外磁屏和外线圈套筒的发射系数,对控制内线圈及导磁底座的温升具有显著影响。基于措施1即阻断内线圈和导磁底座之间的热传导,在二者间增加了厚度为5 mm隔热垫并开展了热平衡试验验证。结果显示,各部件的仿真值与实测值的比对误差均小于10%,而导磁底座和外壳处的温度比对误差最大,这是由于试验中仍存在轴向热传导所导致。比对结果验证了针对措施1所开展仿真分析的准确性,同时也间接证明了措施4组合措施6的降温效果有效性。
[Background]As the working power of Hall thrusters increases,the overall temperature of the thrusters will rise accordingly.A significant increase in temperature can lead to a decline in work performance and structural failure of the thruster.Therefore,a reasonable thermal design can significantly enhance the performance stability and reliability of Hall thrusters.[Purpose]The purpose of this paper is to provide engineering guidance for the reasonable thermal design of a 12.5 kW Hall thruster without a cooling plate.In addition,a thermal model of the thruster is established and verified for the continuous optimization of the thruster’s structure.[Methods]The heat loss distribution of the 12.5 kW Hall thruster is calculated by theoretical analysis,then FEM(finite element method)is used to bulid the thermal build of a 12.5 kW Hall thruster,and six different thermal design methods are proposed in this paper.In addition,the effectiveness of different thermal design methods is analyzed by finite element simulation combined with a thermal balance experiment.[Results]The results show that the average temperature rise of each thruster part reaches 50~150℃after the cooling plate is removed.Therefore,considering the main heat transfer paths of the thruster,six thermal design methods are proposed and simulated,respectively.The results indicate that Method 4 and Method 6,namely,intercept the radiation heat exchange between the hollow cathode and the inner coil,and increasing the emission coefficient of outer magnetic screen and the outer coil sleeve.Meanwhile,based on Method 1,that is,blocking the heat conduction between the inner coil and the magnetic base,then a 5-mm-thick heat insulation pad is added between the inner coil and the magnetic base.The test results show that the comparison errors between simulations and the measurements of each component are less than 10%,and the comparison error between the magnetic base and the thruster base is the largest,which is caused by the top-down axial heat conduction in the test.[Conclusions]Axial heat conduction and radial heat radiation are the main heat transfer methods of the Hall thruster.According to the research results,the combination of Method 4 and 6 is the most effective way for thermal design optimization.Subsequently,the process will be verified to achieve the purpose of significantly reducing the temperature of the thruster.
作者
孙明明
孔繁庭
杨俊泰
李沛
王尚民
Sun Mingming;Kong Fanting;Yang Juntai;Li Pei;Wang Shangmin(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute of Physics,Lanzhou 730000,China;School of Media Engineering,Lanzhou University of Arts and Sciences,Lanzhou 730000,China)
出处
《强激光与粒子束》
北大核心
2025年第9期91-101,共11页
High Power Laser and Particle Beams
基金
兰州市青年科技人才创新项目(2023-QN-5)。
关键词
霍尔推力器
热边界
热设计
热量传递
Hall thruster
thermal boundaries
thermal design
heat transfer
