金属热防护系统边缘热短路研究

研究了金属热防护系统(TPS)的缝隙辐射及支架两大热短路问题。通过数值计算分析了缝隙宽度和缝隙辐射率对热短路的影响,完成了整体样件以及阵列组合件的稳态传热实验测试,定量地研究了热短路的影响情况。实验结果显示:支架处热短路现象明显,实验中支架引发的热短路温差高达50K;在773K以下,缝隙传热引发的温升随着缝隙宽度的增加而线性增加;在773K以上,辐射热传导在缝隙宽度超过3mm时即成为内部传热的主导机制,这时缝隙传热引发的温升不再随宽度增加而线性递增。所提供的数值分析和实验方法可为金属热防护系统的分析与设计提供重要的参考价值。     

某探测器上火箭发动机热防护仿真与设计

根据某探测器的具体结构及工作条件,分析和计算探测器上火箭发动机的热环境参数.利用有限元法计算火箭发动机固壁辐射热流密度,依据热流边界条件设计热防护方案;利用有效发射率表征多层隔热材料隔热性能并进行温度场数值仿真.由于多层隔热材料性能参数的不易确定性,计算了参数在较大范围内的热防护效果.通过仿真计算验证热防护方案的有效性和可靠性,并分析影响热防护效果的主要因素;计算结果表明多层隔热材料的有效发射率是影响隔热性能最重要的因素,比热容、表面发射率、密度对热防护性能影响很小.      

星敏感器空间辐射效应研究

星敏感器作为一类高灵敏度光电集成部件,易受空间辐射的影响造成性能退化和工作 异常。分析星敏感器的辐射效应机理并制定相应的防护对策,既是当前可靠性增长的基础, 也是今后高性能星敏感器发展的必然要求,而国内尚缺少对这一问题的详细论述。阐述了空 间辐射环境和星敏感器的组成以及工作原理,综述分析了空间辐射效应机理和对星敏感器产 生的影响,并介绍了国外在相应防护对策上的经验,更进一步对影响星敏感器较为严重的瞬 态效应做了较为深入的探讨。
     

一种基于自适应滤波器的潜艇辐射噪声仿真方法

文章提出了一种基于自适应滤波器的潜艇辐射噪声仿真方法。在对潜艇辐射噪声连续谱、线谱和调制谱的数学模型进行研究的基础上,利用Ecs型功率谱模型,基于自适应滤波器,通过傅里叶反变换对潜艇辐射噪声连续谱进行了仿真,分别叠加了线谱信号和调制谱信号之后,得到潜艇辐射噪声的仿真结果。通过对仿真结果的分析和利用仿真结果与实装进行对接测试,表明仿真的辐射噪声逼真度较高。     

Heliotropic dust rings for Earth climate engineering

This paper examines the concept of a Sun-pointing elliptical Earth ring comprised of dust grains to offset global warming. A new family of non-Keplerian periodic orbits, under the effects of solar radiation pressure and the Earth’s J₂ oblateness perturbation, is used to increase the lifetime of the passive cloud of particles and, thus, increase the efficiency of this geoengineering strategy. An analytical model is used to predict the orbit evolution of the dust ring due to solar-radiation pressure and the J₂ effect. The attenuation of the solar radiation can then be calculated from the ring model. In comparison to circular orbits, eccentric orbits yield a more stable environment for small grain sizes and therefore achieve higher efficiencies when the orbit decay of the material is considered. Moreover, the novel orbital dynamics experienced by high area-to-mass ratio objects, influenced by solar radiation pressure and the J₂ effect, ensure the ring will maintain a permanent heliotropic shape, with dust spending the largest portion of time on the Sun facing side of the orbit. It is envisaged that small dust grains can be released from a circular generator orbit with an initial impulse to enter an eccentric orbit with Sun-facing apogee. Finally, a lowest estimate of 1 × 10¹² kg of material is computed as the total mass required to offset the effects of global warming.     

Preparation of the Biochip experiment on the EXPOSE-R2 mission outside the International Space Station

Biochips might be suited for planetary exploration. Indeed, they present great potential for the search for biomarkers – molecules that are the sign of past or present life in space – thanks to their size (miniaturized devices) and sensitivity. Their detection principle is based on the recognition of a target molecule by affinity receptors fixed on a solid surface. Consequently, one of the main concerns when developing such a system is the behavior of the biological receptors in a space environment. In this paper, we describe the preparation of an experiment planned to be part of the EXPOSE-R2 mission, which will be conducted on the EXPOSE-R facility, outside the International Space Station (ISS), in order to study the resistance of biochip models to space constraints (especially cosmic radiation and thermal cycling). This experiment overcomes the limits of ground tests which do not reproduce exactly the space parameters. Indeed, contrary to ground experiments where constraints are applied individually and in a limited time, the biochip models on the ISS will be exposed to cumulated constraints during several months. Finally, this ISS experiment is a necessary step towards planetary exploration as it will help assessing whether a biochip can be used for future exploration missions.     

CubeSail: A low cost CubeSat based solar sail demonstration mission

CubeSail is a nano-solar sail mission based on the 3U CubeSat standard, which is currently being designed and built at the Surrey Space Centre, University of Surrey. CubeSail will have a total mass of around 3 kg and will deploy a 5 × 5 m sail in low Earth orbit. The primary aim of the mission is to demonstrate the concept of solar sailing and end-of-life de-orbiting using the sail membrane as a drag-sail. The spacecraft will have a compact 3-axis stabilised attitude control system, which uses three magnetic torquers aligned with the spacecraft principle axis as well as a novel two-dimensional translation stage separating the spacecraft bus from the sail. CubeSail’s deployment mechanism consists of four novel booms and four-quadrant sail membranes. The proposed booms are made from tape-spring blades and will deploy the sail membrane from a 2U CubeSat standard structure. This paper presents a systems level overview of the CubeSat mission, focusing on the mission orbit and de-orbiting, in addition to the deployment, attitude control and the satellite bus.     

锥柱形药柱环形槽内传热现象的数值研究

采用标准k-ε湍流模型和离散传递热辐射模型对不同来流雷诺数下锥柱形药柱前向环形槽内的流场与传热进行了数值研究。对槽内各表面与热气流之间的换热量进行了比较,并对努塞尔数沿环形槽各表面的变化进行了分析。结果表明来流雷诺数的大小影响环形槽内的旋涡数和旋涡区域的分布,进而影响槽内温度的分布,最终影响槽内装药表面与点火热气流之间的换热量。整个计算结果可为装药设计和分析推进剂的热解燃烧提供参考。     

Asymmetric precipitation in a coronal loop as explanation of a singular observed spectrum

Almost 10 years of solar submillimeter observations have shown new aspects of solar activity, such as the presence of rapid solar spikes associated with the launch of coronal mass ejections and an increasing submillimeter spectral component in flares. We analyse the singular microwave–submillimeter spectrum of an M class solar flare on 20 December, 2002. Flux density observations measured by Sun patrol telescopes and the Solar Submillimeter Telescope are used to build the radio spectrum, which is fitted using Ramaty’s code. At submillimeter frequencies the spectrum shows a component different from the microwave classical burst. The fitting is achieved proposing two homogeneous sources of emission. This theoretical fitting is in agreement with differential precipitation through a magnetically asymmetric loop or set of loops. From a coronal magnetic field model we infer an asymmetric magnetic structure at the flare location. The model proposed to quantify the differential precipitation rates due to the asymmetry results in a total precipitation ratio Q₂/Q₁≈10⁴–10⁵, where Q₁(Q₂) represents the total precipitation in the loop foot with the high (low) magnetic field intensity. This ratio agrees with the electron total number ratio of the two sources proposed to fit the radio spectrum.     

空间环境模拟器热沉热辐射当量吸收特性研究

文章采用蒙特卡罗法模拟射线的传输过程,分别对两种热沉形式的热辐射当量吸收系数进行了数值计算,研究了表面形式、几何高度及入射光线方向等参数对表面热辐射当量吸收系数的影响。计算表明,正六边形凹腔形式的吸收效果远好于正四棱锥形式,但这种结构形式的吸收有明显的方向性,正四棱锥形式对光线的吸收呈现各向同性。