卫星热控涂层地面模拟试验与在轨验证比对分析
|
摘要
卫星在轨运行期间,热控涂层要经受空间复杂环境效应的影响,其光学和热控性能逐渐下降,影响卫星可靠性和寿命。本文利用卫星搭载技术,完成热控涂层5年的在轨试验,验证空间多因素环境对热控涂层的影响。同时,利用地面模拟试验装置,模拟空间质子、电子、紫外等5年的辐照剂量对热控涂层的作用。对在轨试验结果进行解读和分析,并与地面模拟试验结果进行比对。结果显示,在搭载试验和地面试验前,热控涂层太阳吸收比(αs)为0.12,经5年在轨搭载试验后,αs退化为0.23。经地面模拟试验后,αs退化为0.22。搭载试验和地面试验的热控涂层性能均呈现线性退化规律,表明在确定的轨道环境和固定的剂量率条件下,热控涂层的退化与环境作用时间正相关,同时验证了地面试验的有效性。
During in-orbit operation,the optical and thermal control performances of satellite thermal control coating will degrade due to integrated space environment effects and hence has a great impact on reliability and lifetime of satellites. In this paper,an in-orbit experiment of thermal control coatings is carried out for 5 years to investigate the influence of multi-factors environment. And the sensitive factor of coating performance is achieved and then the in-orbit property evolution law and life prediction model are built. Meanwhile,a ground simulation experiment with proton,electron and ultraviolet irradiation factors is carried out to study the influence of those factors on thermal control coatings. The results demonstrate that the absorptance of thermal coatings increase from 0. 12 to 0. 23 after 5-years' in-orbit operation while this value increases to 0. 22 after the ground simulation test with the equivalent radiation dose. The thermal control performance degradation and test time or irradiation dose are linear related and positive correlated both in orbit and on ground,which has also verified the effectiveness of ground test.
During in-orbit operation,the optical and thermal control performances of satellite thermal control coating will degrade due to integrated space environment effects and hence has a great impact on reliability and lifetime of satellites. In this paper,an in-orbit experiment of thermal control coatings is carried out for 5 years to investigate the influence of multi-factors environment. And the sensitive factor of coating performance is achieved and then the in-orbit property evolution law and life prediction model are built. Meanwhile,a ground simulation experiment with proton,electron and ultraviolet irradiation factors is carried out to study the influence of those factors on thermal control coatings. The results demonstrate that the absorptance of thermal coatings increase from 0. 12 to 0. 23 after 5-years' in-orbit operation while this value increases to 0. 22 after the ground simulation test with the equivalent radiation dose. The thermal control performance degradation and test time or irradiation dose are linear related and positive correlated both in orbit and on ground,which has also verified the effectiveness of ground test.
引文
[1]闵桂荣.航天器热控制技术[M].北京:科学出版社,1998:20-156.
[2]曾一兵,张廉正,于翘.空间环境下的有机热控涂层[J].宇航材料工艺,1997,27(3):18-20.
[3]CHEN Jun,DING Nengwen,LI Zhifeng,et al.Organic polymer materials in the space environment[J].Progress in Aerospace Sciences,2016,83:37-56.
[4]BITETTI G,MARCHETTI M,MILETI S,et al.Degradation of the surfaces exposed to the space environment[J].Acta Astronautica,2007,60(3):166-174.
[5]NAKAYAMA Y,IMAGAWA K,TAGASHIRA M,et al.Evaluation and analysis of thermal control materials under ground simulation test for space environment effects[J].High Performance Polymers,2001,13(3):S433-S451.(下转第70页)
[6]JAWORSKE,DONALD A,TUAN GEORGE C,et al.Optical properties of thermal control coatings after weathering,simulated ascent heating,and simulated space radiation exposure[D].NASA 20080025998,2008.
[7]FINCKENOR M,VISENTINE J,ADAM S,et al.Contamination,UV radiation,and atomic oxygen effects on ISS thermal control materials[R].AIAA 2003-1084,2003:1-10.
[8]DEVER JOYCE,MILLER SHARON,MESSER RUS-SELL,et al.Exposure of polymer film thermal control materials on the Materials International Space Station Experiment(MISSE)[R].AIAA 2001-4924,2001.
[9]FOGDALL LAWRENCE B,LEET SUE J,WILKINSONMAURICE C,et al.Effects of electrons,protons,and ultraviolet radiation on spacecraft thermal control materials[R].AIAA Thermophysics Conference,Norfolk,1999:1-10.
[10]KENNY MIKE,MCNULTY ROBERT,FINCKENORMIRIA.Further analysis of thermal control coatings on misse for aerospace applications[R].NASA 20090028808,2009.
[11]FINCKENOR MIRIA M,ZWIENER JAMES M,ALVISAMY,et al.Thermal control materials on MISSE-6 with comparison to earlier flight data[R].NASA,20100033232,2010:7-24.
[12]JEAN-CLAUDE GUILLAUMON,ALAIN PAILLOUS.Spacecraft Materials:Comparison Between Flight Results Obtained on LDEF and MIR[R].NASA,19940026540,1994:485-498.
[13]TRIBBLE A C,LUKINS R,WATTS E,et al.Low earth orbit thermal control coatings exposure flight tests:a comparison of u.s.and russian results[R].NASA Contractor Report 467,19950016520,1995:28-52.
[14]FENG Weiquan,DING Yigang,YAN Dekui,et al.Space combined environment simulation test onαSdegradation of GEO satellite thermal control coatings[J].Spacecraft Environment Engineering,2007,24(1):27-31.
[2]曾一兵,张廉正,于翘.空间环境下的有机热控涂层[J].宇航材料工艺,1997,27(3):18-20.
[3]CHEN Jun,DING Nengwen,LI Zhifeng,et al.Organic polymer materials in the space environment[J].Progress in Aerospace Sciences,2016,83:37-56.
[4]BITETTI G,MARCHETTI M,MILETI S,et al.Degradation of the surfaces exposed to the space environment[J].Acta Astronautica,2007,60(3):166-174.
[5]NAKAYAMA Y,IMAGAWA K,TAGASHIRA M,et al.Evaluation and analysis of thermal control materials under ground simulation test for space environment effects[J].High Performance Polymers,2001,13(3):S433-S451.(下转第70页)
[6]JAWORSKE,DONALD A,TUAN GEORGE C,et al.Optical properties of thermal control coatings after weathering,simulated ascent heating,and simulated space radiation exposure[D].NASA 20080025998,2008.
[7]FINCKENOR M,VISENTINE J,ADAM S,et al.Contamination,UV radiation,and atomic oxygen effects on ISS thermal control materials[R].AIAA 2003-1084,2003:1-10.
[8]DEVER JOYCE,MILLER SHARON,MESSER RUS-SELL,et al.Exposure of polymer film thermal control materials on the Materials International Space Station Experiment(MISSE)[R].AIAA 2001-4924,2001.
[9]FOGDALL LAWRENCE B,LEET SUE J,WILKINSONMAURICE C,et al.Effects of electrons,protons,and ultraviolet radiation on spacecraft thermal control materials[R].AIAA Thermophysics Conference,Norfolk,1999:1-10.
[10]KENNY MIKE,MCNULTY ROBERT,FINCKENORMIRIA.Further analysis of thermal control coatings on misse for aerospace applications[R].NASA 20090028808,2009.
[11]FINCKENOR MIRIA M,ZWIENER JAMES M,ALVISAMY,et al.Thermal control materials on MISSE-6 with comparison to earlier flight data[R].NASA,20100033232,2010:7-24.
[12]JEAN-CLAUDE GUILLAUMON,ALAIN PAILLOUS.Spacecraft Materials:Comparison Between Flight Results Obtained on LDEF and MIR[R].NASA,19940026540,1994:485-498.
[13]TRIBBLE A C,LUKINS R,WATTS E,et al.Low earth orbit thermal control coatings exposure flight tests:a comparison of u.s.and russian results[R].NASA Contractor Report 467,19950016520,1995:28-52.
[14]FENG Weiquan,DING Yigang,YAN Dekui,et al.Space combined environment simulation test onαSdegradation of GEO satellite thermal control coatings[J].Spacecraft Environment Engineering,2007,24(1):27-31.