Experimental and numerical simulation study of the effect for the anode positions on the discharge characteristics of 300 W class low power Hall thrusters

Low-power Hall thruster(LHT) generally has poor discharge efficiency characteristics due to the large surface-to-volume ratio.Aiming to further refine and improve the performance of 300 W class LHT in terms of thrust and efficiency,and to obtain the most optimal operating point,the experimental study of the discharge characteristics for three different anode positions was conducted under the operation of various discharge voltages(100-400 V) and anode mass flow rates(0.65 mg·s^-1 and 0...     

具有高选择性和谐波抑制的滤波天线设计

设计了一款同时具有高选择性和谐波抑制的滤波天线.通过在正方形微带贴片上蚀刻1对缝隙和在地面上引入两口环DGS,引入2个辐射零点,提高了选择性;通过在接地板上蚀刻2个哑铃型DGS和在馈线上加载1个圆头形开路短截线,谐波抑制达到了12 GHz(4.8f₀).测试结果表明,设计滤波天线工作通带为2.34 GHz～2.42 GHz,在2.28 GHz和2.70 GHz处有两个辐射零点,在3 GHz～12 GHz间的反射系数均大于-4 dB.     

一种基于多模谐振的宽带贴片天线设计

设计了一种基于多模谐振的宽带贴片天线.首先,通过在一个矩形贴片上蚀刻两条缝隙的方式,使天线同时工作在TM₁₀和反相TM₃₀两个正交的模式来展宽天线的带宽;其次,通过在辐射贴片左右两侧的顶角处蚀刻4个方形缝隙,改善天线低频处的阻抗匹配,有效激励起缝隙模式,进一步展宽天线的工作带宽;为了激励这3个工作模式,天线采用缝隙耦合馈电方式,同时在微带馈线的终端加载方形贴片,来改善天线的阻抗匹配.测量和仿真结果吻合良好,天线的工作频带为2.09 GHz～2.77 GHz,相对带宽为27.9%.天线实现了良好的宽边辐射,峰值增益达到了6.3 dBi.     

基于共面波导馈电的三频单极子天线

本文提出了一种新型的三频单极子天线,该天线用共面波导(CPW)馈电,由两个不同长度和结构的单极子构成,长单极子结构实现谐振频率1.57GHz和3.5GHz,短单极子结构实现谐振频率2.4GHz.同时,通过在左侧接地面上增加一个正方形贴片,改善了三个频段内的峰值增益.所实现的天线尺寸为59mm×40.55mm×1.6 mm,在三个工作频率上的带宽分别为254 MHz(1.518 GHz~1.772 GHz)、461 MHz(2.289GHz~2.75 GHz)和226 MHz(3.514 GHz~3.714 GHz),覆盖了GPS、无线局域网(WLAN)和无线接入系统等频段,增益分别为2.15dBi,3.12dBi和3.86dBi.     

建筑节能中的外墙保温技术

随着对节约能源与保护环境要求的不断提高,建筑维护结构的保温技术也在日益加强,尤其是外墙保温技术得到了长足的发展,并成为我国一项重要的建筑节能技术。建筑中常使用的外墙保温在具有优势的同时,也出现了各种各样的质量问题。通过对质量问题产生的原因进行分析,提出解决途径。     

面向5G无线通信的紧凑型高隔离度双频MIMO天线

设计了一种适用于5G无线通信的紧凑型高隔离度双频多输入多输出(Multiple-Input Multiple-Output, MIMO)缝隙天线.天线单元采用矩形环作为地,在其中嵌入2个大小不同,开口方向相反的六边形谐振环实现双频.将两天线单元正交放置形成二单元MIMO天线,为提升隔离度,在两天线单元环形地相接处刻蚀矩形缝隙进行解耦.仿真和测试结果表明,该天线可以工作在2.57 GHz～2.62 GHz和3.5 GHz～3.6 GHz频段,且在2个工作频段内隔离度均高于23.2 dB, ECC低于0.01,具有良好的辐射性能.     

应用于TCXO的新型五次方电压发生器的设计

采用VIS 0.40 μm BCD工艺,设计并实现了一种带有修调技术的应用于温度补偿晶体振荡器(TCXO)的新型五次方电压发生器电路,该五次方电压发生器电路主要由五次方电压产生电路与修调电路两部分构成.其中,五次方电压产生电路采用曲线拟合技术,相较于传统的乘法器级联结构具有更高的精度;新型修调电路用来改变五次方电压发生器的系数,采用双路开关技术提高了修调结果的精度.仿真结果显示,该五次方电压发生器的最大拟合误差为1.2％.测试结果显示,采用该新型五次方电压发生器电路设计的TCXO,其频率-温度稳定度达到(±0.45)×10-6,相位噪声为-135 dBc/Hz@1 kHz,芯片面积为2 782 μm×2 432 μm.     

液压同步提升技术在大型起重机吊装中的应用

1引言江苏某造船公司制造了1台800 t×216 m龙门起重机,该机结构主要由主梁、刚性支腿、柔性支腿、上下小车及行走机构组成。主梁为单箱型结构,高13.15 m,宽9.36 m,结构总重约为5 400 t,起重量约为4 390 t,起升高度为90 m。根据该机的结构特点,吊装方案中采用2副提升塔架,塔架额定承载力为3 300 t,塔架有效提升     

Investigation into the thermal effect of the LIPS-200 ion thruster plume

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 of 15°. 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 kW m⁻² and 0.3 kW 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 is 0.72–0.99 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.