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航天器环境工程

航天器环境工程

北大核心

CSTPCD

Spacecraft Environment Engineering
《航天器环境工程》是由中国空间技术研究院北京卫星环境工程研究所主办的中国科技核心期刊，是国内航天器环境工程专业领域的唯一学术、技术性期刊，广泛报道本专业最新研究成果和技术成就，主要涉及空间环境、空间环境效应和模拟以及材料科学等。《航天器环境工程》面向国内外公开发行，读者对象主要是从事航空航天及高科技领域的科研人员、工程技术人员、高校师生以及航天爱好者等。 本刊内容涵盖真空、力学、热学、电磁学、辐射与防护、低温与光学、可靠性等多个学科领域，目前开设栏目包括：探月和月球环境，空间碎片模拟与防护技术，空间特殊环境效应研究，真空热试验技术，动力学环境试验技术，标准、计量与测试，环境设备研制，航天器总装技术，结构、材料与工艺，航天器平台技术，可靠性技术，计算机仿真与应用，管理撷英等。
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  • 发文量：2178
  • 被引量：699
  • H指数：1
  • 开始收录时间：-
  • CNKI综合因子：-
  • 维普期刊影响因子： 0.66
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  • 创刊时间：-
  • 国内刊号/CN：11-5333/V
    国际刊号/ISSN：1673-1379
  • 发行周期：双月刊
    邮发代号：-
  • 主管单位：中国航天科技集团公司
    主办单位：北京卫星环境工程研究所
航天器环境工程-联系信息
  • 主编：易忠
  • 电话：010-68116408/6407
  • 邮箱：htqhjgc@126.com
  • 地址：北京9832信箱编辑部
  • 邮编：100029
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航天器环境工程 >2023年第2期

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  • 摘要：多点激励振动试验的实施较为复杂.文章研究应用虚拟试验技术在试验前进行试验方案设计及优化的方法.以双点激励虚拟随机振动试验系统为例进行虚拟试验,以及试验方案的优化;并将双点激励实物试验结果与虚拟试验结果进行对比分析.结果显示虚拟试验结果准确可靠,试验方案设计合理有效.%The implementation of a multi-exciter vibration test is a relatively complicated task. The design and the optimization of the test scheme can be helped by using the virtual test technology. In this paper, firstly, the two-exciter random vibration test system is analyzed, and then with the system, the virtual test is carried out to optimize the scheme. The complete missile physical test results and the virtual test results are compared and analyzed. It is shown that the virtual vibration test gives accurate and reliable results, and that the optimized test scheme is reasonable and effective.
  • 摘要：冲击响应谱时域波形合成技术是目前实验室环境下模拟实际复杂冲击环境的重要手段.文章在研究局域均值分解(LMD)方法和冲击响应谱时域波形合成原理的基础上,对实测冲击时域波形进行分解得到一组具有不同频率分布的PF信号分量,然后对不同频率分布的PF信号分量进行聚类分析并重新构造得到一组新的PF信号分量,使得PF信号分量的频率-幅值特性与设定的冲击响应谱试验条件一致.将重构后的PF信号分量组合即可得到合成后的冲击时域波形.数值仿真分析结果表明,基于LMD的冲击响应谱时域波形合成新方法生成的冲击时域波形能更好模拟真实冲击环境,冲击响应谱具有较好的控制精度.%The technique of time domain waveform synthesis of shock response spectrum is an important approach to simulate the complex shock environment in laboratory. The measured time domain waveform is decomposed by the local mean decomposition (LMD) method, and a set of PF signal components with different frequency distributions are obtained based on the LMD and the time domain waveform synthesis of the shock response spectrum. Then, a new set of PF signal components is reconstructed by using the data clustering analysis method for reconstructing the prior PF signal components. The frequency-amplitude characteristics of the new PF signal components are made to be consistent with the set of the shock response spectrum test conditions. The impulse signal can therefore be reconstructed by properly combining the reconstructed signal components. Simulation results show that the time domain waveform obtained from the shock response spectrum generated by the new method based on the LMD method can well represent the real shock environment, and the shock response spectrum has a good control accuracy.
  • 摘要：为了实现MW级热流环境的长时间稳态测量,研制了一种新型结构的水卡式大热流传感器.该传感器采用 U 型水冷通道结构,基于沸腾换热理论进行换热设计,设计量程5~15 MW/m2.在高温超声速燃气流试验台上进行了热流测试试验,实际测试量程3~25 MW/m2.沸腾换热理论的应用可以在较小的水流速下实现MW级热防护,大大降低了设计难度.新型结构传感器相对传统的中心冲击结构换热效率更高,可实现的量程范围更大.%For the long time steady measurement of heat flux of MW magnitude, a calorimetric heat-flux sensor of new structure is designed based on the boiling heat transfer method. A U-shaped water cooling channel is designed, with expected measuremente range from 5 to 15 MW/m2. The sensor is tested in the high temperature supersonic gas flow field, to find its real range of 3 to 25 MW/m2. It is shown that the application of the boiling heat transfer method makes the design much easier due to the better heat transfer efficiency at a lower speed and a smaller pressure loss of the subcooled water, leading to its extended range for measurment.
  • 摘要：To meet the demand of high-speed readout of multi-channel signals from micro pattern gas detectors, a digitization system is designed for the 128-channel preamplifier chip APV25 based on the field programmable gate array (FPGA) Spartan-6. In this system, the serial analog signal output by the APV25 is digitized by the analog-to-digital conversion (ADC) chip ADS5242. After the serial-to-parallel conversion by the Spartan-6, the data are acquired, buffered and packaged to the user datagram, and then sent to the computer via the gigabit ethernet for storage and analysis. In the test, the system reaches a maximum sampling rate of 280 kHz for the APV25, and the pedestal noise is as low as 716 electrons. The linearity of the charge response is good when the input amount of charge is less than 75 000 electrons. This system is expected to be used in the multi-channel radiation detection system in space thanks to the radiation tolerance of the APV25.%为满足微结构气体探测器多通道信号高速读出的需求,文章基于现场可编程门阵列(FPGA) Spartan-6设计了128通道前置放大芯片APV25的数字化系统.该系统中,APV25输出的串行模拟信号经模/数转换芯片ADS5242进行模/数转换,由Spartan-6接收、解串、缓冲和打包后,经千兆以太网传送至计算机进行存储和分析.经测试,该系统可实现APV25的最大采样速率280 kHz,基线噪声低至716 e-.输入电荷量低于75000 e-时,电荷响应线性良好.由于APV25的抗辐射特性,该系统有望用于空间多通道辐射探测系统.
  • 摘要：《航天器环境工程》是由中国空间技术研究院北京卫星环境工程研究所主办的中国科技核心期刊，是国内航天器环境工程专业领域唯一的学术、技术性期刊，广泛报道本专业最新研究成果和技术成就，主要涉及空间环境探测、环境效应建模与评价、航天器环境与调控、地面模拟试验技术、材料性能与环境防护、人机环境工程等，内容涵盖真空与低温、力学、热学、电磁学、辐射与防护、光学、材料科学、可靠性、航天科技管理等多个学科。办刊宗旨是推动航天器环境工程的发展和应用，服务于我国卫星研制、载人航天、探月工程和深空探测。
  • 摘要：未来大型组合体航天器振动试验可能难以在现有设备上进行,需要进行分舱考核.文章针对此问题开展了利用分舱段振动试验获取整器响应的方法研究.提出的方法为:根据不同界面下模态的映射关系,利用单舱段的振动试验数据辨识出舱段的两端固支模态;采用模态综合技术计算出整器组合体模态参数,拟合出结构的加速度响应传递函数;结合整器的加速度试验条件可以给出整器的试验响应曲线.仿真验证结果表明该方法合理可行,具有工程应用价值.%To meet the requirement for the vibration test for the coming ultra large spacecraft structures, single-cabin vibration tests have to be carried out for individual substructures. This paper proposes a method to obtain the transfer function of the whole spacecraft based on the substructure vibration test data. With the mapping relations among different boundary modal shapes, the modal shape of a certain cabin with fixed ends is identified. Then, the modal parameters of the combined structure are calculated by the modal integration technique, and the transfer functions of the acceleration response of the structure are calculated, so the test response curve for the whole spacecraft can be deduced under the given acceleration test conditions. The method is verified by a dynamics simulation, and its engineering feasibility is shown.
  • 摘要：微振动试验中所用的加速度传感器简称高精度加速度传感器,其相比于常规加速度传感器测量量级很低,可以达到10-5g量级甚至更低,用常规的加速度动态标定技术无法实现该量级水平的标定,也无从验证其测量精度的准确性.针对高精度加速度传感器测试精度的标定难题,文章提出在气浮台上设置比对梁的方法,通过激光测振仪和高精度加速度传感器对同一测点进行测量,并将两者的测量结果进行比对分析,以标定高精度加速度传感器的低量级测试精度.同时设计试验对手头现有的微振动加速度传感器进行标定以验证该方法的有效性,试验结果表明:利用激光测振仪标定现有高精度加速度传感器得到的比对结果符合预期;高精度加速度传感器测得的时域波形及频域波形与激光测振仪测得的基本一致,比对偏差在10%左右,满足标定方法要求.%The micro-vibration acceleration sensor can measure as low an acceleration as 10-5g or even in a lower level, but its dynamic calibration of the acceleration in that level is a hard issue with the normal technology to garantee the accuracy and the precision of the measurement. To solve this prolem, this paper proposes a combined approach for calibration: first, set up a beam as the control object, and install the acceleration sensor on it; then use the laser vibrometer and the acceleration sensor for the measurement at the same point on the beam; finally, compare the measurement results to determine the accuracy of the acceleration sensors. We have also designed an experiment to calibrate a predefined acceleration sensor to show the effectiveness of this method. It is indicated that the laser vibrometer is a good instrument for calibration, and the comparison result for the predefined sensor is satisfatory; the almost same results are obtained in both ways not only in the time domain but also in the frequency domain, and their relative deviation is as low as about 10%, which satisfies the demand of the calibrating method.
  • 摘要：文章基于电磁监测卫星的空间等离子体表面带电环境和等电位要求,对卫星多层隔热组件表面等电位的控制方法进行分析和优化,给出多层隔热组件制作、安装、接地、检测和保护工艺方法,从而满足整星表面的电位差在±2 V以内的控制要求.%This paper analyzes and optimizes the method of equipotential control on the surface of the multilayer heat insulation of an electromagnetic monitoring satellite in the space plasma charging environment of the satellite and with consideration of its surface equipotential requirements. The desirable working processes for the multilayer components are proposed, including the fabrication, the installation, the grounding, the detection, and the protection, to meet the requirement of controlling the surface potential difference of the whole satellite within ±2V.
  • 摘要：The paper, based on Hilbert-Huang transform (HHT) method, analyzes the dynamic environmental data recorded during the fairing separation process of fairing. The Hilbert spectrum in the time and frequency domain is acquired from a group of self-adapted primary functions. Meanwhile, the main frequency and the corresponding time range of the diachronic vibration signals are accurately identified. The example of using HHT to deal with the flight data can serve as a reference for the establishment of ground spacecraft mechanical test conditions and the examination of the interface conditions for the launch vehicle.%文章基于Hilbert-Huang变换,对某载人航天器发射过程中整流罩分离期间测量的力学环境参数进行处理分析,利用HHT的基函数自适应性特点,得到振动时间历程信号的时频域Hilbert谱,准确识别出信号主频率及对应时间范围.此应用案例可为地面力学试验条件制定以及运载接口条件确定提供参考.
  • 摘要：To study the influence of atomic oxygen on the LaB6 hallow cathode, the LHC-5 hollow cathode is placed in the atomic oxygen test facility with repeated ignitions, and with the tungsten-rhenium 5-26 thermocouple to measure the temperature of the cathode tube. After the test, the hollow cathode is inspected, and the cathode tube appears to be expanded and cracked. The XPS analysis of the cross section shows that the failure of the cathode tube is caused by oxidation. Therefore, protective measures should be taken for LHC-5-type hollow cathode ion thrusters, the Hall thrusters and the plasma contactors in LEO under atomic oxygen attack, and a correct shutdown strategy is essential for ensuring the normal work of the cathode.%为确定原子氧对六硼化镧型空心阴极的影响,将LHC-5型空心阴极放置于原子氧试验设备中反复点火,期间使用钨铼5-26热电偶测量阴极管温度.试验完成后检查空心阴极,发现阴极管出现膨胀开裂现象,其断面的XPS成分分析结果表明阴极管的断裂失效是由氧化导致的.因此,针对LEO使用六硼化镧型空心阴极的离子推力器、霍尔推力器和等离子体接触器等航天器部件,应制定正确的工作关机策略以保证阴极不受原子氧环境影响.
  • 摘要：为充分验证卫星在轨温度控制策略的适用性和效果,针对航天器在轨温度控制的特点及方式,提出一种在地面模拟星上控温策略的方法.该方法包含:设计开发一套适用于航天器真空热试验的星上控温模拟系统及基于比例开关控制算法的星上控温模拟软件;采用并行驱动技术实现单个控温时间片为1 s的时间控制精度,工况稳定后温度控制误差不超过±0.3 ℃.该方法已成功应用于某型号卫星真空热试验过程,系统配置灵活、操作简单、控温周期短、控温精度高,实现了星上控温策略的有效验证.%In order to verify the feasibility and the effect of the satellite on-orbit temperature control strategy on the ground, a method for simulating the strategy based on the characteristics and manners of spacecraft temperature control is proposed, including the design of a satellite temperature control simulation system for the spacecraft thermal vacuum test, and the development of a temperature control simulation software based on the proportional switch control algorithm. The simulation results show that the time control precision of the single slice of the temperature control time is 1 s, and the temperature control error is within the range of ±0.3 ℃. The system is successfully applied in the vacuum thermal test of a certain type of satellite, featuring flexibility, simple operation, short temperature control cycle, high temperature control accuracy, and an effective verification is made for the temperature control strategy onboard the satellite.
  • 摘要：目前对复合材料胶接修理结构中胶层的模拟多采用二维平面单元,不能有效模拟胶层在外载荷作用下的真实应力状态.考虑某飞行器弹翼修理时形成的复合材料双面胶接结构承受载荷后处于三维应力状态的情况,建立了该修理结构的三维有限元模型,计算出单向拉伸条件下胶层的剪应力,并与Hart-Smith解析解进行对比.分析结果表明三维有限元模型正确、合理.利用所建立的模型分析胶层的剪应力和剥离应力的分布特点,得出胶层破坏的失效顺序,为胶接修理结构的承载能力分析以及结构改进提供参考依据.%At present, the simulation of the adhesive layer in the composite adhesive repair structure mostly adopts a two-dimentional planar element, which cannot effectively simulate the true stress state of the adhesive layer under the action of the external load. A three-dimensional finite element model is established for analyzing the three-dimensional stress state of adhesively bonded composite repair structures. The adhesive shear stress is calculated under uniaxial tensile loading condition, and compared with the Hart-Smith analytical solutions to validate the effectiveness of the present model. It is indicated that the finite element computation results correlate very well with those of the analytical solutions. The distributions of the adhesive shear stress and the peel stress, as well as the mechanism of the failure mode of the adhesive, are analyzed based on the finite element model. The present model and the analytical approaches may help the investigation of the load-bearing capacity of the patched structure and improve the design accordingly.
  • 摘要：为满足"高分三号"卫星8年长寿命在轨数据处理需求,须开展针对数据处理单元(DPU)的可靠性设计验证.针对星载DPU,采用基于阿伦尼斯(Arrhenius)模型的加速因子估计方法进行高温加速寿命试验方案设计与分析,并给出故障判定及处理准则.8年加速寿命试验结果验证了DPU产品各项功能和性能满足技术指标.加速寿命试验技术能够在较短的时间内用较低的成本快速估计星载电子产品的可靠性,在航天产品设计中具有广阔的应用前景.%To meet the requirement of the eight-year long life in-orbit data processing for the GF-3 satellite, an accelerated life test should be carried out to validate the reliability design of the onboard data processing unit (DPU). In this paper, a method based on the Arrhenius model is adopted to estimate the accelerating factor of the onboard DPU. The scheme design of the accelerated life test is described. The failure criteria are proposed with suggested measures, as well as the endurance criteria at the end of the lifetime. It is shown that all functions and performances of the DPU of the GF-3 satellite during and after the test meet the technical specifications. In a conclusion, the accelerated life test technology is an effective way to estimate the reliability of the onboard satellite products in a short time with a low cost, thus it can be widely applied in the design of aerospace electronic products in the future.
  • 摘要：为解决通信卫星真空热试验中有效载荷的部分测试电缆工作温度超出正常区间导致电缆相位特性发生极大跃变的问题,文章设计了一种新型电缆控温方法,实现了测试电缆在真空低温复杂环境下的集中控温.在某新一代通信卫星真空热试验中,应用该集中控温方法后测试电缆网的温度被严格控制在40 ℃±5 ℃,单根电缆沿路径的温度差异被控制在±3 ℃之内,满足了星上有效载荷的时序和相位要求,提高了地面测试的准确性.%In the thermal vacuum test, a large number of cables are connected to the communication satellite through a flange outside the space environmental simulator. A part of the cables would work beyond the normal temperature range, which may lead to undesirable phase jumps. To solve this problem, a new type of cables temperature control device is proposed. With it, the centralized temperature control of the cables in complex vacuum cryogenic environment is realized. In the thermal vacuum test of a new-generation communications satellite, the temperature of the related cables is controlled within a range of 40 ℃±5 ℃, and the temperature difference of a single cable along its path is kept within ±3 ℃. Under the controlled temperature, the requirements of timing and phase of the satellite payload is guaranteed, and therefore the accuracy of the ground testing is also improved.
  • 摘要：The three-dimension Navier-Stokes equations are solved to reveal the aerothermal behavior of the cavity-like structure of protuberance on the surface of flight vehicles. Based on the calculated supersonic flow field and the local heat flux, the aerothermodynamic mechanism of the cavity-like structure is discussed. It is indicated that the heat flux peak is at the front edge of the cavity. An optimized shape is designed for reducing the peak value of the heat flux injected to the front edge. It is shown that the heat-flux onto the front wall is reduced to only about 20 percent of the initial value with the original shape.%针对飞行器上由凸起物形成的类凹腔气动加热问题,采用数值方法求解三维N-S方程,研究了类凹腔外形结构的高超声速气动加热规律,获得了三维高超声速流场和局部热流分布,并详细分析了局部的流场结构和气动加热机理.针对凹腔前壁面热流密度过高的问题,提出并验证了一种降低前壁面边缘热流密度的优化外形,将前壁面的热流密度降低至优化前的20%左右.
  • 摘要：文章通过在卫星电子设备整机上开展单粒子试验验证的案例,揭示单粒子事件对卫星软件指令的影响.试验对象选取卫星平台中典型的电子设备——测控单元,它包含处理器、SRAM等单粒子敏感器件.本案例成功实现在整机状态下触发单粒子事件,测控单元发生单粒子事件的频度疏密适当,验证了测控单元抗单粒子设计的有效性,掌握了测控单元在发生单粒子事件时的工作状态,对漏指令、误指令的产生条件进行了试验验证,并依据试验数据计算了由单粒子事件引发卫星漏指令、误指令的概率.试验结果可为卫星在轨故障分析提供依据,也可为抗单粒子设计提供数据支持.%This paper considers a case of single event impinging the RTU, one of the most vulnerable device on the satellite, to show the influence of the single particle event on the satellite commands. The RTU, as a typical electronic device on the satellite, contains the SEE sensible components such as the processor and the SRAM. In this case, the single particle events are successfully enacted in the working state of the RTU in an appropriate rate. The working state of the RTU under single particle event attack is obtained, and the effectiveness of the RTU's anti-SEE design is well verified. The rate of command loss and command error is calculated from the test data. The result is helpful for analyzing the inflight faults and the anti single particle design.
  • 摘要：文章建立了一个结霜可视化实验装置,对在不同气压条件下的低温竖直表面的结霜现象进行实验研究,掌握了低温环境下的结霜过程和霜层微观形貌特征,实验过程中冷表面的温度控制在-180 ℃.实验结果表明:常压低温结霜工况下,霜晶呈羽毛状,初始晶核趋向于在冷板的边缘形成,之后平行于冷板表面向下生长,并且在初始霜晶形成后的一段时间内,霜层平行于冷板表面向下的生长速度明显大于垂直于冷板表面的生长速度,向下生长的速度达到0.3 mm/min;真空低温结霜工况下,霜层以颗粒状固体存在,生长速度缓慢,在冷表面上分布均匀,并在霜层生长过程中发现开裂现象.此实验装置提供的清晰结霜图像可为后续展开真空条件下的结霜机理研究提供参考.%In order to study the frost growth morphology, a visualization platform is set up. By using the platform, a series of experiments are carried out to study the frost deposited on a vertical flat copper plate in the atmospheric pressure and in vacuum, respectively. The plate is cooled by the liquid nitrogen and controlled at a temperature of -180 ℃. It is shown that under the atmospheric pressure and cryogenic temperature conditions, the initial nucleation tends to take place on the edge of the cold plate, then the frost grow downward along the plate surface with a growth rate of about 0.3 mm per minute. The growth rate in parallel to the cold plate direction is significantly greater than that in the perpendicular direction; under vacuum and cryogenic temperature conditions, the frost is in the form of solid particles and grows very slowly, to reach a uniform distribution on the plate. Cracks are found in the frosting process. The clear frosting images provided by the platform are expected to be used for investigating the frosting mechanism in the future.
  • 摘要：The on-orbit manned spacecraft provides an optimal habitable environment with suitable temperature, humidity and air composition for crew members, as well as favorable conditions for the growth of microorganisms. Meanwhile, the special space environment including the microgravity and the radiation may aggravate the microbial corrosion capability. Therefore, the control and the protection of the space microbial effects should be systematically studied. The microbial control and protection system contains the following four aspects: the collection and the identification of space microbial strains, the microbial corrosion mechanism of the space materials in space, the choice of antimicrobial coated materials used for the manned spacecraft, and the system microbial protection both in orbit and on the ground. The results can serve as a reference for the study of the microbial control and protection technology for inflight manned spacecraft.%载人航天器密封舱内环境适宜航天员工作和生活,同时也给空间微生物提供了生长繁殖的有利条件.而空间微重力和电磁辐射等环境会加大空间微生物对材料的腐蚀能力.因此,必须对空间微生物防控技术进行体系化研究.文章从空间微生物菌种的采集和鉴定、空间环境下微生物对航天材料的腐蚀机理、载人航天材料抗菌涂层选择以及微生物控制技术等方面对微生物防控体系进行阐述,可以作为开展载人航天器空间微生物防控技术研究的参考.
  • 摘要：A better understanding of the behavior of the debris cloud model under the hypervelocity impact is important for designing the shield structure of spacecraft. In this paper, a numerical simulation method is proposed to study the inner and outer boundary model of the debris cloud. According to its origin, the debris cloud is classified into the target cloud and the projectile cloud. The inner and outer boundaries of the cloud shape are determined according to the distribution characteristics of each cloud. The curves of Bernoulli's lemniscates are modified into a combination of lemniscates and circles. It is shown that the modified curves are more appropriate to fit the actual debris shape than the lemniscates.%研究超高速撞击防护靶形成的碎片云的形状模型对航天器防护结构设计具有重要意义.文章用数值仿真的方法研究靶后碎片云的内外边界模型:将碎片云根据其材料来源分为靶板碎片云和弹丸碎片云,分别根据各碎片云的分布特点建立碎片云形状的内外边界方程;在双纽线边界方程的基础上,修正为由双纽线方程和圆弧方程组成的边界方程.对比整体碎片云的适用率表明,由双纽线方程和圆弧方程组成的边界方程比单一的双纽线边界方程描述碎片云实际分布更为贴合.
  • 摘要：To improve the in-orbit surface and structural stabilities of the primary mirror for the remote sensing camera, a special design of a 650 mm primary mirror assembly is presented in this paper. The traditional frame support structure is used for the mirror subassembly, and the glue spot is subjected to shear loads in this structure to make a uniform distribution of the thermal expansion of the materials of the mirror with the support structure. The structural analysis of the mirror assembly shows that the optical surface error is 2.30 nm(PV) and 0.42 nm(RMS); the displacement of the mirror vertex is 0.8 μm, and the light axis deviation of the mirror is 0.01″under 1g gravity in the y direction, on which the mirror subassembly is tested. And the optical surface error is 3.02 nm(PV) and 0.56 nm(RMS), respectively under a (20±2) ℃ thermal environment, as complied with the camera thermal requirement on obrit. The simulated natural frequency of the mirror assembly is 164.3 Hz, basically in accordance with the experimental result of 158.0 Hz. After a routine vibration and vaccum outgassing test, the structural displacement is measured to be less than 3 μm and the degree deviation is less than 3″. It is shown that all concerned properties of this large-aperture space mirror meet the design requirements.%为提高遥感相机主反射镜的在轨面形和结构稳定度,文章对φ650 mm主反射镜组件进行了特殊结构设计,采用传统的装框式支撑结构,通过设计使胶斑切向受力,以有效解决镜子和支撑结构材料热失调问题.力学和热特性计算表明:主反射镜面形在y向(地面装调方向)1g重力作用下的峰谷值(PV)变化为2.30 nm,均方根值(RMS)变化为0.42 nm,镜子顶点位置变化为0.8 μm,光轴变化为0.01";在相机温控指标(20±2) ℃环境下,反射镜的PV变化为3.02 nm,RMS变化为0.56 nm;主反射镜的计算仿真基频为164.3 Hz.主反射镜组件振动试验结果显示组件的实际基频为158.0 Hz,与仿真计算结果基本一致.经过振动和真空放气试验,组件的结构接口稳定性均为平移不大于3 μm,角度变化不大于3".以上全部满足设计指标要求.
  • 摘要：在航天器真空热试验中,常选用红外加热笼作为外热流模拟装置.为提高外热流模拟的准确性,红外加热笼需要对航天器进行全表面覆形.文章针对如何确认外热流模拟装置与航天器的结构匹配性这个难题,依托三维扫描技术,建立了一套数字化结构匹配方法,解决了多站测量拼接误差累积、三维扫描仪参数优化选择2个技术难点,使三维扫描和逆向建模过程引入的几何误差不超过10 mm.该数字化结构匹配方法的实际应用结果表明,外热流模拟装置与航天器的配装成功率达到100%,实际安装状态与仿真结果吻合度较好.%The infrared heating cage is often used as the external heat flux simulation device in the thermal vacuum test (TBT& TVT) for spacecraft. To conduct an accurate simulation of the heat flux, the infrared heating tape array is supposed to cover the whole surface of the spacecraft. To solve the difficulties in confirming the structural matching degree between the spacecraft and the infrared heating cage in the test, a set of digital structure matching methods is adopted based on the 3D scanning technology. The set of methods is successful in reducing the accumulated error during the data splicing and in optimizing the parameters of the 3D scanner. The total geometric error of the 3D scanning and the reverse modeling is not more than 10 mm. By using this set of methods, the structural matching is completely achieved between the heat flux simulation device and the spacecraft. In the meantime, the actual installation state is in good agreement with the simulation results.
  • 摘要：月壤原位成型技术作为月球资源原位利用技术体系中的研究热点,是在月表制造建筑材料及实施月表基础设施建设的关键.文章基于国内外月壤原位成型技术发展现状,根据未来可能的月壤成型任务提出了5种月壤成型技术,分析了其各自涉及的成型体性能与任务需求的匹配性,成本及能耗约束,环境适应性以及成型工艺流程的可实现性等;梳理了形成了月壤原位成型领域的发展建议,对于后续月球资源探测和开发具有一定的借鉴和指导意义.%The lunar soil in-situ forming technology, as an important part of the lunar resource in-situ utilization technological system, is essential to produce the building material and infrastructures on the lunar surface. Based on the development at home and abroad, five kinds of lunar soil forming techniques are discussed according to the tasks of lunar soil forming. The matching between the performance of the formed body and the task requirements, the constraints of cost and energy consumption, the environmental adaptability, and the feasibility of the forming process are analyzed in detail. Suggestions are made for the in-situ forming, which may be taken as a reference for the future lunar resource exploration and development.
  • 摘要：在当前天基激光移除碎片方案设计中,通常采用kJ级高能激光器、100 m/s大速度增量和简单降轨模型计算移除系统参数,然而kJ级天基高能激光器尚未实现.文章基于目前实验室现有的J级激光器水平,参考现阶段碎片移除方案,针对特定区域的目标空间碎片,结合碎片轨道特性信息建立降轨模型,仿真研究目标碎片在低能量天基激光驱动下的运动过程和降轨效果,分析了影响目标碎片降轨效果的因素.对部署在500 km轨道高度的天基平台移除附近碎片的仿真结果表明,速度增量和降轨高度的变化具有累积效应,提高频率、增大有效作用距离等可延长激光烧蚀驱动时间,进而增强碎片降轨效果.分析表明,J级小能量激光器通过长时间的烧蚀,也可有效驱动和移除1～10 cm碎片.%In the scheme of a space debris removal system with the space-based laser(SBL), a kJ-class high-power laser, with a high additional velocity, is to be used. However, the implementation of the kJ-class space-based laser systems is not feasible in the engineering pratice. In this paper, the onboard removal procedure based on the laser system of J-level energy is simulated, and the influential parameters are analyzed. The simulation results of the space-based laser system of 500 km in altitude show that the incremental velocity and the perigee decrease are of an accumulating nature during the removal procedure. Higher frequency and longer distant range of the laser can increase the effective acting time, with a lower perigee of the targeted debris. It is indicated that with the long-term engagement, the J-class low-power laser instead of the kJ-class high-power laser can also be used to drive and remove the middle-sized debris.
  • 摘要：为探究超临界压力下碳氢燃料在水平管内的对流换热规律,文章针对超临界条件下航空煤油RP-3在水平细圆管内的对流换热,分析了热流密度、进口雷诺数及浮升力对对流换热的影响.研究表明:沿流动方向,管内表面传热系数随热流密度的增大先减小后增大;在低进口温度及低进口雷诺数情况下,管内换热均出现先恶化后强化的现象,而随着进口温度和雷诺数的增加,此现象消失;浮升力对换热的影响随热流密度的增加而增加;浮升力对下表面换热的加强使得入口效应的影响在下表面先于上表面结束;受浮升力影响,上下壁最大温差可达50 K;质量流速的增加会抑制浮升力对换热的影响;准则数Grq/Grth可以很好地反映浮升力的变化趋势.以上研究结果可为采用碳氢燃料作冷却介质的各类飞行器主动热防护技术方案提供技术支撑.%To better understand the convective heat transfer of the hydrocarbon fuel in horizontal tubes under supercritical pressures, an experimental study is carried out for the convective heat transfer of the aviation kerosene RP-3 in a horizontal miniature round tube. Under the working conditions of the air-kerosene heat exchanger, the aviation kerosene is heated up to the supercritical regime. The influences of the heat flux, the fluid inlet temperature, and the buoyancy on the heat transfer of the RP-3 are analyzed. It is found that the heat transfer coefficients decrease with the increase of the heat flux, and the buoyancy causes a large temperature difference of 50 K between the top and the bottom surfaces of the test tube under high heat flux conditions, which can be predicted by the non-dimensional parameter Grq/Grth. The effects of the buoyancy on the heat transfer can be suppressed by increasing the mass flux. The results may provide a technological basis for the active thermal protection of the flight vehicles to be cooled by hydrocarbon fuels.
  • 摘要：This paper introduces a kind of micro photometer with the advantages of light weight and small volume for the ionosphere detection. It can retrieve the total electron content (TEC) of ionosphere by measuring the atomic oxygen airglow in form of far ultraviolet radiation with a wavelength of 136.5 nm. The principle of detection and the design scheme of the photometer are presented. The integration and the miniaturization of the reflecting mirror, the industrial-grade FUV detector and the electronics are realized through a proper design of the lightweight aluminum reflector and the anti-interference preamplifier. The one-kilogram level micro sensor is developed, which is applicable to the micro-nano satellite for ionosphere detection. By taking the advantages of multi-orbit constellation, large amount of data can be obtained by the micro optical ionospheric detector including the TEC distribution in the global ionosphere with high spatial and temporal resolutions, to provides a technical basis of payload for networked satellite detecting in the future.%文章介绍了质量小、体积小的微型电离层光学探测器技术,给出了探测器的探测原理和设计方案,通过探测原子氧远紫外夜气辉(136.5 nm)辐射强度,反演电离层总电子含量(TEC).采用轻量化铝反射镜、抗干扰电荷前放设计,实现反射镜、工业级远紫外探测器、电子学的一体化和小型化,研制出适用于微纳卫星的1 kg量级微型空间电离层光学探测器.该型探测器能够利用微纳星群多种轨道搭载,可获得丰富数据的优势,获取全球电离层高时空分辨率总电子含量分布,为未来实现卫星编队探测提供载荷研制基础.
  • 摘要：《航天器环境工程》是由中国空间技术研究院北京卫星环境工程研究所主办的中国科技核心期刊，是国内航天器环境工程专业领域唯一的学术、技术性期刊，广泛报道本专业最新研究成果和技术成就，主要涉及空间环境探测、环境效应建模与评价、航天器环境与调控、地面模拟试验技术、材料性能与环境防护、人机环境工程等，内容涵盖真空与低温、力学、热学、电磁学、辐射与防护、光学、材料科学、可靠性、航天科技管理等多个学科。办刊宗旨是推动航天器环境工程的发展和应用，服务于我国卫星研制、载人航天、探月工程和深空探测。
  • 摘要：通过试验检测热防护材料或结构的隔热能力是航天器与高超声速飞行器安全可靠性设计中不可缺少的重要环节.为获知隔热性能试验中3种不同边界条件下(试验件竖直放置,水平放置散热面向下,水平放置散热面向上)平板试验件散热面温度的差异,建立3种热试验装置,对轻质隔热材料进行不同温度条件下的隔热性能试验测试(散热面敞开).试验结果表明:试验件水平放置散热面向下时的散热面温度最高;水平放置散热面向上时的散热面温度最低.当热面温度为1000℃时,1800 s后,水平放置散热面向下比水平放置散热面向上时的散热面温度高19.7％;试验件竖直放置比水平放置散热面向下时的散热面温度低2.3％.数值模拟结果与试验结果一致性良好,验证了试验结果的可信性和正确性.研究结果可为航天器与高速飞行器热防护系统设计及试验方案的确定提供重要参考依据.
  • 摘要：文章针对真空热试验红外加热装置计算机辅助设计中的非稳态过程模拟问题,以一种较为复杂的伞状天线结构为例,以红外笼作为加热装置,对真空热试验环境下的加热过程进行数值仿真研究.采用红外笼的等效加热面模型简化仿真模型,使计算负荷可以达到工程应用的水平,同时满足模拟精度的要求.数值仿真与试验数据对比证明,所采用的计算方法可以为红外笼等红外加热装置的设计提供准确的非稳态加热过程模拟.
  • 摘要：针对航天器传动链机械零部件发生故障时训练数据稀缺以及信号的强非平稳非线性特点,提出了动态数据驱动的子空间稀疏多分类智能故障诊断算法.首先对采集的单一传感器动态信号进行分形小波变换,生成常规和非常规二进小波尺度.然后对生成的各子空间提出基于故障能量指标的稀疏多分类器,以监测部件的故障特征频率为搜索目标,在子空间的包络解调谱上计算特征频率及其倍频附近的能量峰值,导出特定故障模式的稀疏评价指标,以各种故障模式的最大值识别和判定故障类型.所提出的算法完全实现了无人工监督的智能故障诊断.最后以航天器轴承故障诊断为例验证了该算法的有效性.所研究算法的泛化能力较强,技术路线同样适用于其他航天器传动部件的在线监测与故障智能预警.
  • 摘要：文章探讨了可用于载人航天器的常压热试验环境模拟技术,包括空间站的在轨漏热分析、多层常压隔热性能试验以及大型常压热试验验证系统试验能力分析,在此基础上完成了空间站某密封舱段的大型常压热试验,并基于试验结果进行漏热对比分析,验证所用常压热试验环境模拟技术的效果能达到预期.

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