太阳风中航天器带电与尾迹效应的模拟

航天器充电和尾迹效应会对周围等离子体造成扰动,影响测量装置结果的准确性.利用SPIS （Spacecraft Plasma Interaction Software）分别模拟了航天器与太阳风的相互作用,考察了光电效应以及航天器尺度对表面充电情况和尾迹效应的影响.结果表明:太阳风环境下,等离子体密度稀薄,电子电流比光电子电流小得多,航天器表面为正电势,航天器后部有清晰的尾迹结构,尾迹带负电;光电效应可改变尾迹结构,与无光电效应相比,光电效应使得航天器尾迹尺度变大;由于太阳风定向运动动能大于航天器表面势能,航天器的尾迹结构与其几何尺寸有关,航天器尺寸越大,尾迹尺度越大.      

Giotto/Cometary dust interaction event near the comet Halley ionopause

Plasma and magnetic field disturbances accompanying dust particle impacts are explained by means of creation of a secondary cloud around the spacecraft. Cold cometary ions impinging upon the cloud are scattered by atoms of the cloud. This scattering changes initial angular distribution of cometary ions. Magnetic field perturbation is created by the friction between the electron component of the cometary plasma flow and the cloud.     

The new ESA meteoroid model

The orbital distributions of meteoroids in interplanetary space are revised in the ESA meteoroid model to account for recently obtained observational data and to comply with the constraints due to the orbital evolution under planetary gravity and Poynting–Robertson effects. Infrared observations of the zodiacal cloud by the COBE DIRBE instrument, in situ flux measurements by the dust detectors on board Galileo and Ulysses spacecraft, and the crater size distributions on lunar rock samples retrieved by the Apollo missions are synthesized into a single model. Within the model, the orbital distributions are expanded into a sum of contributions due to a number of known sources, including the asteroid belt with the emphasis on the prominent families Themis, Koronis, Eos and Veritas, as well as comets on Jupiter-encountering orbits. An attempt to incorporate the meteor orbit database acquired by the AMOR radar is also discussed.     

Electric antenna as a dust detector

Electric antenna responds to three effects caused by a dust impact-induced plasma cloud: -change separation electric fields, -charging of the antenna, -pulse of the spacecraft potential. Each effect, being a function of the induced charge (particle mass), depends on the ambient plasma conditions, including photo- and secondary emissions. The first two effects are also strongly dependent on the impact geometry. In the paper an attempt is made to consider systematically the dependence on the charge and ambient conditions for two main types of antenna (probe, wire/cylinder) and for both configurations (monopole, dipole). A conclusion is drawn that for a plasma wave/radio experiment to be utilized as a dust detector, the most advantageous option is a monopole, whose probe (wire/cylinder) is not exposed to dust-induced plasma.     

弹丸撞击防护屏形成碎片云速度特性研究

微流星及空间碎片的高速撞击威胁着长寿命，大尺寸航天器的安全运行，导致其严重的损伤和灾难性的失效，为精确估计微流星及空间碎片主速撞击防护屏产生的碎片对舱壁的损伤，必须确定碎片云速度特性。文章在冲量和能量守恒的基础上，建立了碎片速度性分析模型，研究了碎片云的速度特性，得到了碎片云材料传播及碎片云喷射角随弹丸撞击速度的变化规律。     

Project overview and highlights of Suisei and Sakigake

ISAS's (Institute of Space and Astronautical Science) project for the exploration of comet Halley consists of two spacecraft, Sakigake and Suisei, launched on 7 January 1985 and 18 August, respectively.

Sakigake passed the sunward side of the comet on 11 March 1986 with a miss distance of 6.99 million km. Three experiments, a plasma wave probe with dipole and search-coil antennae, a magnetometer with three axis ring core sensor on an extended boom and a four-grid Faraday cup attached to the inner side of the wall of the spacecraft, detected various phenomena caused by the comet at a distance as far as 7 million km.

The other spacecraft, Suisei, flew by the comet on its sunward side with a miss distance of 151 thousand km on 8 March 1986. It carried two experiments, an ultraviolet imager and an energy analyzer for ions. The UV imager was able to take the first image of the hydrogen cloud of comet Halley on 26 November 1985. With this experiment, the spin period of the cometary nucleus, location of jets, amount of water evaporation, distribution of hydrogen density inside cloud, etc. were clarified. The energy analyser experiment provided information on the intensive interaction between cometary and solar wind ions.     

Estimation of the bias of the Minimum Variance technique in the determination of magnetic clouds global quantities and orientation

Magnetic clouds (MCs) are highly magnetized plasma structures that have a low proton temperature and a magnetic field vector that rotates when seen by a heliospheric observer. More than 25 years of observations of magnetic and plasma properties of MCs at 1 AU have provided significant knowledge of their magnetic structure. However, because in situ observations only give information along the trajectory of the spacecraft, their real 3D magnetic configuration remains still partially unknown. We generate a set of synthetic clouds, exploring the space of parameters that represents the possible orientations and minimum distances of the satellite trajectory to the cloud axis, p. The synthetic clouds have a local cylindrical symmetry and a linear force-free magnetic configuration. From the analysis of synthetic clouds, we quantify the errors introduced in the determination of the orientation/size (and, consequently, of the global magnetohydrodynamic quantities) by the Minimum Variance method when p is not zero.     

柱状弹丸撞击防护屏形成碎片云材料状态特性研究

微流星体及空间碎片的高速撞击威胁着长寿命、大尺寸航天器的安全运行，导致其严重的损伤和灾难性的失效。为精确估计微流星体及空间碎片高速撞击防护屏所产生碎片云对舱壁的损伤，必须确定碎片云中三种状态材料的特性，建立了碎片云特性分析模型，分别计算了柱状弹丸撞击防护屏所产生碎片云以及碎片云中弹丸和防护屏材料三种状态物质的质量分布。通过计算分析可见，弹丸以不同速度撞击防护屏所产生碎片云三种状态物质的质量分布是不同的，速度增大，液化和气化增强，对靶件的损伤小。而在速度小于7km/s时，碎片云以固体碎片的形式存在，对靶件的损伤大。     

Faster algorithm of debris cloud orbital character from spacecraft collision breakup

Space debris is polluting the space environment. Collision fragment is its important source. NASA standard breakup model, including size distributions, area-to-mass distributions, and delta velocity distributions, is a statistic experimental model used widely. The general algorithm based on the model is introduced. But this algorithm is difficult when debris quantity is more than hundreds or thousands. So a new faster algorithm for calculating debris cloud orbital lifetime and character from spacecraft collision breakup is presented first. For validating the faster algorithm, USA 193 satellite breakup event is simulated and compared with general algorithm. Contrast result indicates that calculation speed and efficiency of faster algorithm is very good. When debris size is in 0.01–0.05 m, the faster algorithm is almost a hundred times faster than general algorithm. And at the same time, its calculation precision is held well. The difference between corresponding orbital debris ratios from two algorithms is less than 1% generally.     

The plasma sheet and boundary layers under northward IMF: A multi-point and multi-instrument perspective

During conditions of northward interplanetary magnetic field (IMF), the near-tail plasma sheet is known to become denser and cooler, and is described as the cold-dense plasma sheet (CDPS). While its source is likely the solar wind, the prominent penetration mechanisms are less clear. The two main candidates are solar wind direct capture via double high-latitude reconnection on the dayside and Kelvin–Helmholtz/diffusive processes at the flank magnetopause. This paper presents a case study on the formation of the CDPS utilizing a wide variety of space- and ground-based observations, but primarily from the Double Star and Polar spacecraft on December 5th, 2004. The pertinent observations can be summarized as follows: TC-1 observes quasi-periodic (∼2 min period) cold-dense boundary layer (compared to a hot-tenuous plasma sheet) signatures interspersed with magnetosheath plasma at the dusk flank magnetopause near the dawn-dusk terminator. Analysis of this region suggests the boundary to be Kelvin–Helmholtz unstable and that plasma transport is ongoing across the boundary. At the same time, IMAGE spacecraft and ground based SuperDARN measurements provide evidence of high-latitude reconnection in both hemispheres. The Polar spacecraft, located in the southern hemisphere afternoon sector, sunward of TC-1, observes a persistent boundary layer with no obvious signature of boundary waves. The plasma is of a similar appearance to that observed by TC-1 inside the boundary layer further down the dusk flank, and by TC-2 in the near-Earth magnetotail. We present comparisons of electron phase space distributions between the spacecraft. Although the dayside boundary layer at Polar is most likely formed via double high-altitude reconnection, and is somewhat comparable to the flank boundary layer at Double Star, some differences argue in favour of additional transport that augment solar wind plasma entry into the tail regions.     

等离子体鞘层效应对磁层探测电场仪设计的影响

在空间环境探测中，卫星与等离子体的相互作用会改变背景环境的粒子和电位的分布，从而影响探测器对空间电场的测量.为了给磁层卫星电场探测仪器的研制和设计提供参考，本文以中国未来的磁层电离层探测为背景，针对不同轨道高度的等离子体环境，利用SPIS（Spacecraft Plasma Interaction Software）模拟了卫星平台和探针与等离子体的相互作用，从而得到了不同环境下卫星周围等离子体鞘层的厚度，以及探针电位与电流的对应关系.模拟结果表明:由于光电子和二次电子的影响，卫星鞘层的厚度小于等离子体的德拜半径，且温度越高其偏差越大；模拟得到的探针表面电流与电位的关系表明，施加偏置电流的探针可明显提高对电流扰动的抗干扰能力.此外，估计了不同轨道高度上探针处于最佳工作点时应施加偏置电流的大小.      

The exit of the photoelectron flows from the ionosphere of the Earth after X-ray burst

The process of the disturbance formation and evolution in the ionosphere of the Earth with a pulsed source of X-ray radiation is studied. The region of altitudes H > 100km, where nonlocal effects are essential, is examined. The formation of current system developed by noncompensated photoelectron flows is studied in detail. Time characteristics of the photoelectron flows leaving the ionosphere are calculated. A possibility of the plasma turbulence excitation by these fluxes is analyzed.     

磁云边界层中的复合重联喷流观测分析

太阳风中的磁场重联通常与行星际日冕物质抛射有关.本文分析了1995年10月18日WIND飞船观测到的一例磁云前边界层中的复合重联喷流事件.该复合排空区由相邻两个不同方向的喷流构成，这两个喷流分别经过Walén关系的证认，符合行星际磁场重联排空区等离子体喷流的特征.结果表明，在磁云前端可能存在众多重联点，从而将磁云本体的磁场剥离，形成比单一重联喷流区更复杂的三维边界层结构.磁云边界层中可能发生多点多次重联，从而不表现出单点重联的排空区特征，这可能是行星际磁场重联排空区较少在ICME前端被观测到的原因之一.      

Impact induced plasma during a cometary fly-by

GIOTTO, the probe which is presently developed by the European Space Agency, will encounter comet Halley in March 1986 with a relative velocity of 69 km/s. The fore section of the surface will be submitted to the bombardment of dust grains and neutral molecules in the final phase of the mission, like that of an Earth orbiter during atmospheric re-entry. These particles have a kinetic energy of 24 eV per a.m.u.; they produce secondary ions and electrons which form a plasma cloud around the body and control the electric potential of its surface. This paper is a review of the work which has been performed on the subject by dedicated study groups; the purpose of their action was to gather information and produce new findings which might have an influence on the design of the spacecraft and help in the interpretation of the data collected by the scientific payload.

The effect of impact induced plasma may already be significant at 10⁵ km from the comet nucleus; at a distance of 1000 km the flux of ions and electrons produced by cometary dust and neutrals will possibly exceed that of the ambient plasma by more than three orders of magnitude. It is expected that the spacecraft surface potential will be positive and will reach at least a few tens of volts; coating the leading surface of the spacecraft with a thin layer of gold or silver will help reducing the emission of ions from neutral gas. Computer simulation models are used to predict the structure of the charged particle density distribution in the vicinity of the surface. Effects associated with the wake and differential charging are also discussed. The significance of these results is conditioned by the validity of the models and the largest source of uncertainty seems to be associated with the plasma generated by dust impact.     

Interaction between a body and its environment during a cometary fly-by

The surface of a spacecraft is submitted to the bombardment of dust grains and neutral molecules during an atmospheric re-entry or a cometary fly-by. These particles create secondary ions and electrons which form a plasma cloud around the body and control the electric potential of its surface. Computer simulation models are used to predict the structure and dynamic behaviour of the charged particle density distribution for the cases of planar and cylindrical bodies. It is found that an ion and an electron layer form in the vicinity of the surface at distances of the order of the ion and electron Debye lengths, respectively. The potential of the surface is positive on the average and is a function of the electron mean kinetic energy. A positive potential barrier develops at the location of the ion layer and its height is governed by the sum of the electron and ion mean kinetic energies. The threat caused by this interaction to the spacecraft and its instrumentation is discussed and an in-situ observation of this phenomenon is proposed as a possible diagnostic technique of the environment.     

An investigation into the roles of ECH and whistler mode waves in the formation of “pancake” electron distributions using data from the CRRES satellite

Electron pitch angle distributions sharply peaked at 90° pitch angle were first recorded in the energy range 50 eV < E < 500 eV by the GEOS-1 and GEOS-2 spacecraft in 1977/8, from the plasmapause out to geostationary orbit. At the time they were explained as the remnants of pitch angle diffusion driven solely by Electron Cyclotron Harmonic (ECH) waves. Here we use observations by instruments on board the CRRES spacecraft to study these distributions in more detail. The pancake distributions are now seen to develop from injected distributions that are nearly isotropic in velocity space, on a time scale that is greater than 2 hours. The freshly injected distributions are associated with strong ECH and whistler mode waves suggesting that the pancake distributions are likely to be caused by a combination of both wave types. Our results suggest that whistler mode waves play a dominant role in the formation of pancake distributions outside L = 6.0, whereas inside L = 6.0 and, in particular, in the vicinity of the plasmapause, the ECH waves also play a significant role. Consequently both types of waves should be considered in any attempt to explain the diffuse aurora and the variation with L taken into account.     

超高速撞击航天器二次碎片云能量特性分析

为了评估空间碎片超高速撞击航天器的碎片云破坏能力,挖掘超高速撞击数值模 拟结果数据的应用价值,基于9.53 mm铝球以6.64 km/s速度对2.2 mm铝靶撞 击的Ls-Dyna/SPH(Smoothed Particle Hydrodynamic)数值模拟研究结果,对靶后碎片云的 粒子动能进行求和统计,建立了碎片云比动能概念和函数形式;碎片云比动能综合考虑了靶 后所有碎片云粒子的动能,反映了一定距离处垂直于撞击方向平面上单位面积上的碎片云粒 子所蕴含的撞击能量;应用碎片云比动能概念,揭示出随着演化距离的增加,碎片云能量的 衰减规律;通过不同速度条件下的SPH计算,得到了碎片云的比动能函数的曲线形式随撞击 速度的变化规律;最后对采用2种材料模型进行数值模拟所对应的结果误差进行碎片云比动 能函数的曲线比较,反映出数值模拟中不同材料模型引起的差异.      

Night side lunar surface potential in the Earth’s magnetosphere

In the Earth’s magnetotail, Japanese Moon orbiter Kaguya repeatedly encountered the plasmoid or plasma sheet. The encounters were characterized by the low energy ion signatures including lobe cold ions, cold ion acceleration in the plasma sheet-lobe boundaries, and hot plasma sheet ions or fast flowing ions associated with plasmoids. Different from the previous observations made in the magnetotail by the GEOTAIL spacecraft, the ions were affected by the existence of the Moon. On the dayside of the Moon, tailward flowing cold ions and their acceleration were observed. However, on the night side, tailward flowing cold ions could not be observed since the Moon blocked them. In stead, ion acceleration by the spacecraft potential and the electron beam accelerated by the potential difference between lunar surface and spacecraft were simultaneously observed. These electron and ion data enabled us to determine the night side lunar surface potential and spacecraft potential only from the observed data for the first time.