Tianzhou 1 Cargo Spacecraft Leaves Orbit

<正>After the space lab missions and extended experiments were completed,the Tianzhou 1 cargo spacecraft effectively put on its"breaks"twice,thus continuously lowering its altitude before burning-up in the atmosphere around 6p.m.on September 22.Tianzhou 1 was China’s first cargo spacecraft developed by CASC,launched on April 20 from the Hainan Wenchang Spacecraft Launch Site.Tianzhou 1,signified the end of the     

Refueling Test System Completed In-orbit Verification

正The in-orbit verification of a refueling test system has been completed successfully.The test system based on a surface tension tank was developed by the Beijing Institute of Control Engineering(BICE),CAST and launched into spacewith the Tianyuan 1 satellite aboard a LM-7 carrier rocket on June 25.The lifetime of any spacecraft is constrained by fuel it carried.It is a cuttingedge technology therefore to be able to refuel spacecraft in orbit safely and effec-     

Tiangong 1 Target Spacecraft Returned to Earth

正China Manned Space Agency announced on April 2 that the Tiangong 1target spacecraft reentered the Earth’s atmosphere around 08:15 Beijing time on April 2 and came down in the middle of the South Pacific.Most parts were burned up during the reentry process.Tiangong 1 was developed by the     

Digital Assembly Technology Helps the Development of Laosat-1

正The Laosat-1 communications satellite was the first spacecraft developed based on the DFH-4S platform,as well as being the first Chinese Flight Model of communications satellite using3D digital assembly technology.The assembly of Laosat-1 had to be completed in a short period while facing great technical difficulties and complexity.To meet the requirements,the Beijing Institute of Spacecraft Envi-     

基于声波理论的氧输送系统低频脉动特性数值研究（英文）

Aiming at the low-frequency pressure fluctuation phenomena in certain liquid oxygen delivery systems during dual engine operation, a numerical study on the intrinsic frequency of the liquid oxygen delivery system was conducted by adopting an acoustic unit in Abaqus. Factors such as condensation characteristics of the oxygen-enriched gas gas in the liquid oxygen's pipeline between pumps, flexibility of the accumulator, and cavitation flexibility of the engine were considered in the simulation models. The simulation results show that the second order frequency of the liquid oxygen delivery system is 8.77 Hz, and the phase difference of the corresponding acoustic modal is 180°, which is the liquid circuit frequency of the small loop between the two branches of the tee. This is consistent with the low-frequency fluctuation phenomenon during flight. Moreover, the simulation results were consistent with the liquid circuit frequency solved via the transfer matrix, which also verified the effectiveness of the frequency analysis method based on acoustic theory.     

Multilevel Tests and Measurement Evaluation Methods for the Application of Composite Materials in Spacecraft Structures

With the implementation of new-generation launch vehicles, space stations, lunar and deep space exploration, etc., the development of spacecraft structures will face new challenges. In order to reduce the spacecraft weight and increase the payload, composite material structures will be widely used. It is difficult to evaluate the strength and life of composite materials due to their complex mechanism and various phenomena in damage and failure. Meanwhile, the structures of composite materials used in spacecrafts will bear complex loads, including the coupling loads of tension, pressure, bending, shear, and torsion. Static loads, thermal loads, and vibration loads may occur at the same time, which asks for verification requirements to ensure the structure safety. Therefore, it is necessary to carry out a systematic multi-level experimental study. In this paper, the building block approach (BBA) is used to investigate the multilevel composite material structures for spacecrafts. The advanced measurement technology is adopted based on digital image correlation (DIC) and piezoelectric and optical fiber sensors to measure the composite material structure deformation. The virtual experiment technology is applied to provide sufficient and reliable data for the evaluation of the composite material structures of spacecrafts.     

First Liquid Oxygen and Coal-Derived Kerosene Rocket Engine Firing Test Succeeded

A ground hot firing test of an overall rocket engine using liquid oxygen and coal-derived kerosene as propellant was conducted on April 12,2015.The success of the test proved that coal-derived kerosene could be used for aerospace application as petroleum-derived aerospace kerosene.It was the first attempt not only for China but also for the whole world to use coal-derived kerosene in     

Tiangong 2 Space Lab Entered Electric Test Phase

<正>It was announced at the beginning of 2015 that CAST had completed installation of payload equipment of the application system onboard Tiangong 2 space lab,which had been delivered for electric test.It was a key point in the integation process of the Tiangong 2 space lab.Compared with the former Tiangong 1 target spacecraft,the application system of Tiangong 2 consists of brand     

Breakthrough on Ultra-High-Temperature Simulation Technology for Spacecraft Thermal Vacuum Test

<正>The Center of Assembly,Integration and Test of CAST made an important technical breakthrough on high-temperature and high heat flux simulation technology recently.The test specimen was heated up to 1850℃by a simulation system developed by the center inside a container simulating the vacuum,cold and dark space environment.Ultra-high-temperature test on the ground is required by spacecraft and relevant parts to simulate the space en-     

SJ-9 Satellite Delivered

On August 21,the SJ-9 satellite delivery ceremony was held in Beijing which marks its formal operation.Yuan Jie,Vice President of CASC attended the ceremony.SJ-9 has conducted in-orbit new product verification of 24 categories which are badly needed for China’s satellite development,and evaluation and assessment on over 20 types of domestic core elements and materials of10 categories.It firstly accomplished the satellite formation flight and high-accurate GPS interplanetary measurement     

原子氧环境下磁力矩器用聚合物材料的质损和红外光谱分析

文章利用新型的原子氧环境模拟设备进行真空和原子氧试验,通过质量损失测量和FT-IR分析,对试样的质量损失率(SAML)和表面成分的变化进行了研究。试验结果表明:真空环境会导致材料产生质量损失,4种材料中真空质损最大相差24倍;原子氧作用导致聚合物材料产生质量损失,4种材料中质量损失率最大相差25倍;原子氧与有机硅物质反应能够形成保护层,可以抑制原子氧对材料内部的进一步侵蚀。FT-IR分析结果表明,原子氧作用导致环氧材料的-N消失,O元素百分比含量升高,硅橡胶的化学键被破坏,并导致新的O-H和C-H的生成。     

三硅醇苯基POSS复合聚酰亚胺薄膜的制备与抗原子氧侵蚀性能研究

低地球轨道上运行的航天器表面材料尤其是聚合物材料极易受到原子氧侵蚀。以三硅醇苯基笼型聚倍半硅氧烷（TSP-POSS）为填料,以PMDA-ODA型聚酰亚胺（PI）为基体,通过机械共混法制备一系列复合薄膜,系统研究TSP-POSS的引入对复合薄膜耐热性能、光学性能以及抗原子氧侵蚀性能的影响。结果表明:TSP-POSS与PMDA-ODA型聚酰胺酸（PAA）具有良好的相容性,复合溶液均匀,储存稳定性优良;PAA/TSP-POSS复合溶液热酰亚胺化后形成的PI/TSP-POSS复合薄膜在TSP-POSS含量（质量分数）低于25%时可保持良好的均匀性;TSP-POSS的加入可在一定程度上提高复合薄膜的光学透明性,且对复合薄膜耐热性能的影响较小;引入TSP-POSS可以显著提高PMDA-ODA薄膜的抗原子氧性能,经受累积注量达4.02×1020 atoms/cm2的原子氧侵蚀后,TSP-POSS含量为25%的复合薄膜的原子氧剥蚀率为2.2×10-25 cm3/atom,仅为不含TSP-POSS薄膜的7.33%。     

磁力矩器用聚合物材料的原子氧效应试验研究

文章对磁力矩器用4种聚合物材料进行原子氧和真空效应评价试验,利用新型的原子氧环境模拟设备及其他分析手段对试样的质量损失率(SAML)和表面形貌的变化进行了研究。试验结果表明,真空环境会导致材料产生质量损失,4种材料的真空质损最大相差24倍;原子氧作用导致聚合物材料的颜色发生变化,且造成材料的质量损失,4种材料的质量损失率最大相差25倍;原子氧与有机硅物质反应能够形成保护层,可以抑制原子氧对材料内部的进一步侵蚀。     

原子氧对航天材料的影响与防护

文章综述了低地球轨道（LEO）中原子氧（AO）环境对航天材料影响的研究现状。首先介绍AO对材料的危害及作用机制等。然后重点阐述了国内外学者关于AO与Al、Ag、Cu、Ni等金属材料以及半导体材料作用的研究成果。最后总结了AO的防护方法,及其对不同材料抗AO侵蚀能力的改善结果。     

Kapton抗原子氧侵蚀的Al2O3涂层研究

在原子氧侵蚀地面模拟设备中对Kapton和利用反应溅射制备的Al2O3涂层进行了原子氧暴露实验，并采用XPS和SEM等分析手段对暴露前后试样表面的物理和化学变化进行了研究。结果表明，Kapton试样遭受了严重的侵蚀，质量损失较大；Al2O3涂层质量变化很小，对基体提供了良好的保护作用。XPS分析结果表明，Kapton的羰基与原子氧作用时形成CO2，随后CO2气体脱附。反应溅射的Al2O3涂层是富Al的，初始暴露时由于氧化反应而质量有少许增加，随时间延长，涂层变得完全符合化学计量。     

真空紫外对原子氧环境下S781白漆 性能影响的研究

文章利用AOBISEE设备对S781白漆分别进行了单一原子氧环境试验、真空紫外与原子氧递次试验以及原子氧与真空紫外综合辐照试验研究。试验研究中原子氧的积分通量为3.5×1019 atom/cm2,真空紫外辐照剂量为200 ESH;试验前后用高精度微量电子天平和TEMP 2000A便携式热发射率测试仪分别对样品的质量和热发射率进行了测试。通过测试及分析,发现原子氧与真空紫外综合环境对S781白漆产生了协和效应。S781白漆在经原子氧与真空紫外综合环境作用之后质量损失显著增大,3种不同环境试验对S781白漆的热发射率影响不明显。在辐照剂量范围内,S781白漆的真空紫外与原子氧递次试验不能替代原子氧／真空紫外综合辐照试验。     

低地球轨道原子氧?太阳远紫外协合效应地面试验条件探讨

低地球轨道航天器表面聚合物材料受中性大气原子氧和太阳远紫外辐照的同时作用,表现出不同于单一因素分别作用的协合效应。文章在总结现有地面试验设备参数和不足的基础上,分析原子氧注量、远紫外曝辐照度随在轨时间变化的计算方法和输入数据特性,并以正立方体卫星为例计算得到典型轨道不同太阳活动环境下迎风面和非迎风面的原子氧注量和远紫外曝辐照度,以及远紫外曝辐照度/原子氧注量之比（注量比）随在轨时间的变化后,提出将该注量比参数作为有关地面试验条件制定的依据之一,以提高航天器外露材料原子氧?远紫外协合效应地面试验模拟的有效性。     

低地球轨道航天器涂层防护技术研究进展

低地球轨道(LEO)环境极为复杂,紫外辐照、原子氧辐照、高能粒子辐照等因素并存,对航天器用有机材料提出苛刻要求。为满足长寿命安全飞行,必须对航天器特别是其上采用的有机材料进行防护。文章简述了LEO环境中各因素对航天器的影响,总结了航天器防护技术特别是涂层防护方案的研究进展,并指出了未来发展方向。     

BHM3碳纤维及其氰酸酯基复合材料耐原子氧侵蚀性能

利用原子氧暴露地面模拟实验装置,分别对BHM3型高模量碳纤维及其增强的氰酸酯基复合材料进行了原子氧暴露模拟实验,采用SEM、XRD、XPS技术分析了原子氧对碳纤维及其氰酸酯复合材料的侵蚀行为。结果表明,经过1×10 21 atoms/cm 2剂量的原子氧暴露后,碳纤维及其氰酸酯复合材料质量损失率均低于1%,纤维表面形貌及组成不变,碳纤维/氰酸酯复合材料的层间剪切强度降低16%。     

空间原子氧环境对太阳电池阵的影响分析

空间原子氧是危害低地球轨道（LEO）航天器在轨性能的最主要空间环境因素之一,其强氧化性能够对包括太阳电池阵在内的航天器外表面暴露材料和组件造成危害。文章分析了某载人航天器在轨原子氧环境、原子氧对不同结构太阳电池阵所用材料的影响以及对太阳电池阵组件电性能的影响,结果表明原子氧对材料的作用能够引起太阳电池阵基板强度降低、电连接可靠性下降及电缆线护套失效等风险,材料的损伤会导致太阳电池组件电性能的下降。鉴于以上结果,作者建议在今后LEO长寿命航天器太阳电池阵研制中,应对原子氧环境条件进行详细设计;同时开展组件级试验,以对电池阵原子氧防护设计的有效性进行验证。