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热控涂层参数对卫星辐射特性的影响 总被引:1,自引:0,他引:1
为分析卫星红外和可见光双光谱辐射特性,分别建立了采用节点网络法求解卫星表面热控涂层温度和卫星辐射特性的计算模型,依据粗糙表面光散射理论计算了涂层表面对太阳、地球和地球反照辐射的吸收和反射。通过数值模拟,计算分析了卫星对地面的温度变化规律。最后,选择不同的热控涂层参数,获得了对卫星在红外和可见光波段的辐射特征的影响。 相似文献
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热控涂层红外发射率对GEO卫星蓄电池温度波动的影响 总被引:1,自引:0,他引:1
在东方红一3卫星平台的基础上,将合理简化后的南蓄电池舱作为热分析模型。根据影响蓄电池温度波动的机理,提出服务舱舱板内表面常用热控涂层(白漆、镀铝膜、碳蒙皮)的5种组合方案,并量化分析了热控涂层红外发射率对蓄电池温度波动的影响。分析结果表明:降低蓄电池舱舱板内表面热控涂层红外发射率,尤其是降低蓄电池安装舱板表面的热控涂层红外发射率,可有效减小蓄电池温度波动幅度。与基准方案相比,最优组合方案能使蓄电池温度波动幅度降低50%。 相似文献
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为解决铝合金表面液相等离子体电解氧化(PEO)涂层(Y2O3-ZnO-Al2O3)导电性差而导致的静电效应,对其进行表面改性处理。采用原子层沉积(ALD)技术在铝合金表面PEO涂层原位沉积铝掺杂氧化锌(AZO)导电薄膜以提高PEO涂层的导电性。对AZO改性PEO涂层的相组成和表面微观结构进行分析;对不同沉积温度下所得复合涂层的电阻率、载流子浓度和迁移率,以及沉积前后的热控性能、耐腐蚀性进行测量分析。结果表明:AZO导电薄膜均质连续致密地沉积在PEO涂层表面;当沉积温度为150 ℃时,AZO@Y2O3-ZnO-Al2O3复合涂层的电阻率为1.15×10-4 Ω·cm,载流子浓度为1.8×1020 cm-3,太阳吸收比为0.409,发射率为0.892,且抗电化学腐蚀性能良好,能够满足航天器热控涂层在空间环境应用的技术要求。 相似文献
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多层隔热组件等效热物性参数的分析 总被引:4,自引:0,他引:4
多层隔热组件在卫星热设计中应用最为广泛,主要用于减小漏热以及整星与外环境之间的热耦合。文章采用等效处理的方式,将多层隔热组件等效成为一种低太阳吸收比、低红外发射率的热控涂层。根据等效处理法结果讨论了等效处理法在计算中可能带来的误差。 相似文献
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红外诱饵等空间特定目标是对抗红外探测的主要手段之一。随着双色制导技术的发展,红外探测灵敏度不断提升,目标识别能力不断增强,这对空间特定目标表面的双波段红外辐射的逼真性提出了要求。通过改变空间特定目标表面发射率控制其红外辐射强度的大小,使用数值仿真的方法进行计算,从而提出了对空间特定目标表面红外辐射特性的调控方法。此外根据所确定的表面发射率、可见光吸收及红外发射比例以及内热源功率,选择合适的表面材料以及热功率施加方法,在保证空间特定目标表面机械性能的同时,使空间特定目标满足光照及阴影区的双波段红外辐射特性要求,并进行模型的制作以及热真空实验,证明了理论计算的准确性。 相似文献
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The purpose of this paper is to introduce a new method in the research of radiative and thermal properties of materials with further applications in the design of thermal control systems (TCS) of spacecrafts. In this paper the radiative and thermal properties (emissivity and thermal conductance) of a multilayered thermal-insulating blanket (MLI), which is a screen-vacuum thermal insulation as a part of the TCS for perspective spacecrafts, are estimated. Properties of the materials under study are determined in the result of temperature and heat flux measurement data processing based on the solution of the inverse heat transfer problem (IHTP) technique. Given are physical and mathematical models of heat transfer processes in a specimen of the multilayered thermal-insulating blanket located in the experimental facility. A mathematical formulation of the inverse heat conduction problem is presented as well. The practical approves were made for specimen of the real MLI. 相似文献
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Optical surveys have identified a class of high area-to-mass ratio (HAMR) objects in the vicinity of the Geostationary Earth Orbit (GEO) ring. The exact origin and nature of these objects are not well known, although their proximity to the GEO belt poses a hazard to active GEO satellites. The prevalent conjecture is that many of these objects may be thermal materials shed from derelict spacecraft in ‘graveyard’ orbits above the GEO ring. Due to their high area-to-mass ratios and unknown attitude dynamics and material characteristics, solar radiation pressure (SRP) perturbs their orbits in ways that makes it difficult to predict their orbital trajectories over periods of time exceeding a week or less. To better understand and track these objects and infer their origins, we have made observations that allow us to determine physical characteristics that will improve the non-conservative force modeling used for orbit determination (OD) and prediction. Information on their temperatures, areas, emissivities, and albedos may be obtained from thermal infrared and visible measurements. Simultaneous observations in the thermal infrared and visible wavelengths may allow disentangling of projected area, albedo, and object emissivity.Further analysis and modeling of observational data on certain of the HAMR objects collected at the AMOS observatory 3.6 m AEOS telescope are presented. The thermal-IR spectra of these geosynchronous orbit objects acquired by the Broadband Array Spectrograph System (BASS) span wavelengths 3 to 13 μm and constitute a unique data set, providing a means of measuring object fluxes in the infrared and visible wavelengths. These, in turn, allow temperatures and emissivity-area products to be calculated, and in some cases provide information on rotation rates. We compare our observational results with the outputs of simple models, in terms of visible and infrared flux and orbital characteristics. The resulting temperatures and rotation rates are used in SRP acceleration models to demonstrate improvements in OD and prediction performance relative to models which assume default ambient temperature and static attitude dynamics. Additionally, we have the capability and plans to measure material properties with the same instrument in the lab as used at the telescope to facilitate direct comparisons. 相似文献