MOS电容型微小空间碎片探测器探头研究
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摘要
MOS电容传感器具有结构简单、可靠、功耗小等优点,在国外已被成功用于微小空间碎片在轨探测,但国内开展的相关研究还较少。文章在对MOS电容传感器探测微小空间碎片原理及过程进行分析的基础上,基于ADS软件建立了传感器电路模型,确定了影响传感器探测性能的关键参数,完成了传感器的设计及研制,进而研制了阵列式探头。最后对阵列式探头成功开展了地面高速微粒撞击试验,探头在经过了数十次高速微粒撞击后,仍能对高速撞击事件进行测量,初步验证了使用该探头开展在轨微小空间碎片探测是可行的。
Due to its advantages of simple structure, credibility and low-power consumption, the metal-oxide-silicon(MOS) capacitance type sensor is successfully used in foreign countries to detect the orbital micro-debris, but so far not in domestic studies. In this paper, the detection principle of the MOS capacitance sensor is introduced. A charging and discharging model for the orbital micro-debris impact MOS capacitance sensor is built. Then the simulation is carried out by using ADS software. The MOS capacitance sensor's key parameter is confirmed and the structure and process design of MOS capacitance sensor is completed. Based on the sensor, an array probe is designed and fabricated. Finally, with the array probe, the ground high-speed particulate impact test is carried out. The array probe sensor has experienced dozens of high-speed impacts, without affecting its ability to measure the high-speed impact event, which verifies the feasibility of using the probe for the on-orbit space micro-debris detection.
Due to its advantages of simple structure, credibility and low-power consumption, the metal-oxide-silicon(MOS) capacitance type sensor is successfully used in foreign countries to detect the orbital micro-debris, but so far not in domestic studies. In this paper, the detection principle of the MOS capacitance sensor is introduced. A charging and discharging model for the orbital micro-debris impact MOS capacitance sensor is built. Then the simulation is carried out by using ADS software. The MOS capacitance sensor's key parameter is confirmed and the structure and process design of MOS capacitance sensor is completed. Based on the sensor, an array probe is designed and fabricated. Finally, with the array probe, the ground high-speed particulate impact test is carried out. The array probe sensor has experienced dozens of high-speed impacts, without affecting its ability to measure the high-speed impact event, which verifies the feasibility of using the probe for the on-orbit space micro-debris detection.
引文
[1]都亨,张文祥,庞宝君,等.空间碎片[M].北京:中国宇航出版社,2007:5-18
[2]SIMON C G,MULHOLLAND J D,OLIVER J P,et al.Long-term microparticle flux variability indicated by comparison of interplanetary dust experiment(IDE)time impacts for LDEF’s first year in orbit with impact data for the entire 5.77 year orbital lifetime:93N29379[R].Vriginia:NASA,1993:693-703
[3]何正文,张明磊,向宏文,等.探测微小空间碎片的MOS电容传感器设计研究[J].航天器工程,2013,22(1):205-209HE Z W,ZHANG M L,XIANG H W,et al.Study of on-board micro space debris mos capacitor-type detector[J].Spacecraft Engineering,2013,22(1):205-209
[4]HEINER K.空间碎片——模型与风险分析[M].钱卫平,译.北京:清华大学出版社,2012:46-56
[5]董尚利,李延伟,吕钢,等.空间粉尘探测器研究进展[J].航天器环境工程,2013,30(4):339-345DONG S L,LI Y W,LüG,et al.Research progress in the field of space dust detector[J].Spacecraft Environment Engineering,2013,30(4):339-345
[6]GSIMON C G,OLIVER J P,COOKE W J,et al.Long term microparticle impact fluxes on LDEF determined from optical survey of interplanetary dust experiment(IDE)sensor:95N23826[R].Florida:NASA,1995:323-336
[7]袁庆智.空间微小碎片探测器[D].北京:中国科学院空间科学与应用研究中心,2005:24-26
[8]KINARD W H,ARMSTRONG D,CROCKET S K,et al.Orbiting meteoroid and debris counting experiment:95N27668[R].Vriginia:NASA,1995:1331-1340
[9]ALBY F,OTRIO G,DURIN C.Space based observations of orbital debris[C]//51st International Astronautical Congress.Paris,2000:104-112
[10]KASSEL P C,WORTMAN J J.Metal-oxide-silicon capacitor detectors for measuring micro-meteoroid and space debris flux[J].Journal of Spacecraft and Rockets,1995,32(4):710-718
[11]HAYASHIDA K B,ROBINSON J H.Single wall penetration equations:NASA TM-103565[R].Washington D.C.:NASA,1991:1-6
[12]董尚利,刘海,吕钢,等.光学器件的空间粉尘高速撞击效应研究[J].航天器环境工程,2011,28(2):115-120DONG S L,LIU H,LüG,et al.Investigation of effects of hypervelocity impact of space dust on optical components[J].Spacecraft Environment Engineering,2011,28(2):115-120
[2]SIMON C G,MULHOLLAND J D,OLIVER J P,et al.Long-term microparticle flux variability indicated by comparison of interplanetary dust experiment(IDE)time impacts for LDEF’s first year in orbit with impact data for the entire 5.77 year orbital lifetime:93N29379[R].Vriginia:NASA,1993:693-703
[3]何正文,张明磊,向宏文,等.探测微小空间碎片的MOS电容传感器设计研究[J].航天器工程,2013,22(1):205-209HE Z W,ZHANG M L,XIANG H W,et al.Study of on-board micro space debris mos capacitor-type detector[J].Spacecraft Engineering,2013,22(1):205-209
[4]HEINER K.空间碎片——模型与风险分析[M].钱卫平,译.北京:清华大学出版社,2012:46-56
[5]董尚利,李延伟,吕钢,等.空间粉尘探测器研究进展[J].航天器环境工程,2013,30(4):339-345DONG S L,LI Y W,LüG,et al.Research progress in the field of space dust detector[J].Spacecraft Environment Engineering,2013,30(4):339-345
[6]GSIMON C G,OLIVER J P,COOKE W J,et al.Long term microparticle impact fluxes on LDEF determined from optical survey of interplanetary dust experiment(IDE)sensor:95N23826[R].Florida:NASA,1995:323-336
[7]袁庆智.空间微小碎片探测器[D].北京:中国科学院空间科学与应用研究中心,2005:24-26
[8]KINARD W H,ARMSTRONG D,CROCKET S K,et al.Orbiting meteoroid and debris counting experiment:95N27668[R].Vriginia:NASA,1995:1331-1340
[9]ALBY F,OTRIO G,DURIN C.Space based observations of orbital debris[C]//51st International Astronautical Congress.Paris,2000:104-112
[10]KASSEL P C,WORTMAN J J.Metal-oxide-silicon capacitor detectors for measuring micro-meteoroid and space debris flux[J].Journal of Spacecraft and Rockets,1995,32(4):710-718
[11]HAYASHIDA K B,ROBINSON J H.Single wall penetration equations:NASA TM-103565[R].Washington D.C.:NASA,1991:1-6
[12]董尚利,刘海,吕钢,等.光学器件的空间粉尘高速撞击效应研究[J].航天器环境工程,2011,28(2):115-120DONG S L,LIU H,LüG,et al.Investigation of effects of hypervelocity impact of space dust on optical components[J].Spacecraft Environment Engineering,2011,28(2):115-120