A simple method to design non-collision relative orbits for close spacecraft formation flying

A set of linearized relative motion equations of spacecraft flying on unperturbed elliptical orbits are specialized for particular cases, where the leader orbit is circular or equatorial. Based on these extended equations, we are able to analyze the relative motion regulation between a pair of spacecraft flying on arbitrary unperturbed orbits with the same semi-major axis in close formation. Given the initial orbital elements of the leader, this paper presents a simple way to design initial relative orbital elements of close spacecraft with the same semi-major axis, thus preventing collision under non-perturbed conditions. Considering the mean influence of J₂ perturbation, namely secular J₂ perturbation, we derive the mean derivatives of orbital element differences, and then expand them to first order. Thus the first order expansion of orbital element differences can be added to the relative motion equations for further analysis. For a pair of spacecraft that will never collide under non-perturbed situations, we present a simple method to determine whether a collision will occur when J₂ perturbation is considered. Examples are given to prove the validity of the extended relative motion equations and to illustrate how the methods presented can be used. The simple method for designing initial relative orbital elements proposed here could be helpful to the preliminary design of the relative orbital elements between spacecraft in a close formation, when collision avoidance is necessary.     

太阳与地磁活动对超低轨重力卫星电推进系统工作的影响

面向当前第25太阳活动周,评估太阳与地磁活动对超低轨重力卫星电推进系统工作的影响。通过对超低轨道重力卫星进行轨道仿真和分析GOCE任务数据,得出大气阻力的变化规律,并获得了太阳活动极大年附近任务和极小年附近任务对携带工质量的影响、地磁暴对电推进系统保持“无拖曳”工作的影响。结果表明：其余情况相同下,卫星在太阳活动低年附近任务的工作轨道高度可较高年降低约20 km,有利于提高重力信号强度。强地磁暴通常引起超低轨道卫星阻力增加30%～90%,飞行控制需为克服地磁暴影响留足够的推力裕度。推力器设计应保证最大推力的10%～70%推力区间具有高比冲,且着重考虑此区间的寿命问题。     

Detailed comparison of observed dose-time profile of October 19-20, 1989 SPE on Mir with model calculations.

The dose rate dynamics of the October 19-20, 1989 solar energetic particle (SPE) event as observed by the Liulin instrument onboard the Mir orbital station was analyzed in light of new calculations of the geomagnetic cutoff and improved estimates of the >100 MeV energy spectra from the GOES satellite instrument. The new calculations were performed using the as-flown Mir orbital trajectory and includes time variations of the cutoff rigidity due to changes in the Kp index. Although the agreement of total event integrated calculated dose to the measured dose is good, it results from some measured dose-time profile being higher and some lower than model calculations. They point to the need to include the diurnal variation of the geomagnetic cutoff and modifications of the cutoffs to variations in Kp in model calculations. Understanding of such events in light of the upcoming construction of the International Space Station during the period of maximum solar activity needs to be vigorously pursued.     

Atmospheric radioactive isotopes at orbital altitudes

The radioactive isotope ⁷Be was discovered on the forward-facing side of the LDEF satellite in amounts far exceeding that expected from direct cosmic ray activation of the spacecraft material. This prompted an examination of the production of cosmogenic isotopes in the atmosphere and of the processes by which they may be transported to orbital altitudes and absorbed by a spacecraft. ⁷Be is only one of several atmospheric cosmogenic isotopes that might be detectable at orbital altitudes and that might prove to be as useful as tracers of atmosphere ciculation processes in the mesosphre and thermosphere as they have been in the lower layers of the atmosphere.     

掩星状态下的太阳形状及强度的理论及数值分析

提出了一种掩星状态下获得太阳形状及强度的方法,并进行了理论推导,建立了数值仿真模型。建立了无大气折射效应下的太阳形状及强度矩阵,并以此作为参考,通过阿贝尔积分公式及折射率垂直剖面反演得到经大气折射后的太阳像面任意位置处的大气弯曲角,根据弯曲角计算得到掩星后太阳像面各个点位置相对于不发生掩星时的位移,根据参考像面即可得到掩星后的太阳像面形状及强度矩阵。 仿真结果表明,采用此模型能实现掩星状态下,不同轨道位置,任意切点下的太阳形状及强度分布。 同时,以卫星轨道高度600 km作为仿真算例,模拟获得了从5~60 km不同正切点高度位置处相应的太阳形状及强度分布,并且仿真得到了云层遮挡下的太阳强度分布图。此模型对应用于卫星姿态部件的测试标定、遥感技术及材料测量等领域,实现能够较为真实地反映太阳形状及强度的太阳模拟器,具有较高的参考价值。     

Orbit determination and prediction accuracy analysis for a regional tracking network

China's COMPASS satellite navigation system relies on a regional tracking network to provide navigation services. Limited by its geographic border,the regional network is able to cover only 30% of the medium-earth-orbits(MEO). Accuracy of determined and predicted orbits is not able to satisfy system requirements if the tracking data processing strategy for global tracking network processing is used for the regional network. Two major error sources for orbital prediction are accuracy of initial orbital elements and dynamical modeling. To achieve better prediction accuracy,we propose a two-step orbit determination and prediction strategy. For step 1,only solar radiation pressure(SRP) parameters are estimated along with the orbital elements and other parameters; for step 2,all parameters are estimated but the SRP parameters are tightly constrained to their step 1 estimates. Experimenting with data from a regional GPS network,we conclude for orbital prediction using the proposed two-step strategy,the average user range error(URE) for 24-h prediction arcs is better than 0.6 m.     

Observation results of relativistic electrons detected by Fengyun-1 satellite and analysis of relativistic electron enhancement (REE) events

The space particle component detector on Fengyun-1 satellite which works at the sun-synchronous orbit of about 870 km altitude has detected relativistic electrons for a long time. In comparison with the SAMPEX satellite observations during 1999–2004, the relativistic electron data from Fengyun-1 satellite from June 1999 to 2005 are used to analyze the relativistic electron enhancement (REE) events at the low earth orbit, and the possible correlation among REE events at the low earth orbit, high-speed solar wind and geomagnetic storms is discussed. The statistical result presents that 45 REE events are found in total during this time period, and the strong REE events with the maximum daily average flux > 400 cm⁻²·sr^t-1·s⁻¹ occur mostly during the transition period from solar maximum to solar minimum. Among these 45 REE events, four strong REE events last a longer time period from 26-to 51-day and correlate closely with high speed solar wind and strong geomagnetic storms. Meanwhile, several strong geomagnetic storms occur continuously before these REE events, and these continuous geomagnetic storms would be an important factor causing these long-lasting strong REE events. The correlation analysis for overall 45 events indicates that the strength of the REE events correlates with the solar wind speed and the strength of the geomagnetic storm, and the correlation for strong REE events is much stronger than that for weak REE events.     

嫦娥一号卫星太阳风离子探测器数据分析

探月航天器与月球周围等离子体环境相互作用,表面将出现充放电效应,给航天器带来很多不利影响.表面充电电位对充放电的影响至关重要.评估探月航天器的充放电效应,首先需获得月球周围等离子体环境数据.嫦娥一号上搭载的两台太阳风离子探测器SWIDA/B是用来观测月球200 km轨道附近等离子体环境的探测仪器,获得了月球附近的太阳风速度、密度和温度.本文对2008年6月一个月内太阳风离子探测器SWIDA机获得的离子微分通量进行统计平均,得到太阳风离子微分通量能谱,并计算得到了月球200 km附近的太阳风速度(300.00—600.00 km·s-1)、密度(1—10 cm-3)和温度(1—20 eV).最后采用等效电路模型的方法计算得到了探月航天器表面充电电位范围为-7—-70 V.     

Reconciling cold dark matter with COBE/IRAS plus solar and atmospheric neutrino data

We present a model where an unstable MeV Majorana tau neutrino can naturally reconcile the cold dark matter model (CDM) with cosmological observations of large and small scale density fluctuations and, simultaneously, with data on solar and atmospheric neutrinos. The solar neutrino deficit is explained through long wavelength, so-called just-so oscillations involving conversions of ν_e into both ν_μ and a sterile species ν_s , while atmospheric neutrino data are explained through ν_μ to ν_e conversions. Future long baseline neutrino oscillation experiments, as well as some reactor experiments will test this hypothesis. The model is based on the spontaneous violation of a global lepton number symmetry at the weak scale. This symmetry plays a key role in generating the cosmologically required decay of the ν_τ with lifetime τ_ντ ≈ 10²-10⁴ seconds, as well as the masses and oscillations of the three light neutrinos ν_e, ν_μ and ν_s required in order to account for solar and atmospheric neutrino data. It also leads to the invisibly decaying Higgs signature that can be searched at LEP and future particle colliders.     

Orbit determination and prediction for Beidou GEO satellites at the time of the spring/autumn equinox

Geostationary(GEO) satellites form an indispensable component of the constellation of Beidou navigation system(BDS). The ephemerides, or predicted orbits of these GEO satellites(GEOs), are broadcast to positioning, navigation, and timing users. User equivalent ranging error(UERE) based on broadcast message is better than 1.5 m(root formal errors: RMS) for GEO satellites. However, monitoring of UERE indicates that the orbital prediction precision is significantly degraded when the Sun is close to the Earth's equatorial plane(or near spring or autumn Equinox). Error source analysis shows that the complicated solar radiation pressure on satellite buses and the simple box-wing model maybe the major contributor to the deterioration of orbital precision. With the aid of BDS' two-way frequency and time transfer between the GEOs and Beidou time(BDT, that is maintained at the master control station), we propose a new orbit determination strategy, namely three-step approach of the multi-satellite precise orbit determination(MPOD). Pseudo-range(carrier phase) data are transformed to geometric range(biased geometric range) data without clock offsets; and reasonable empirical acceleration parameters are estimated along with orbital elements to account for the error in solar radiation pressure modeling. Experiments with Beidou data show that using the proposed approach, the GEOs' UERE when near the autumn Equinox of 2012 can be improved to 1.3 m from 2.5 m(RMS), and the probability of user equivalent range error(UERE)2.0 m can be improved from 50% to above 85%.     

A note on vector flux models for radiation dose calculations

This paper reviews and extends modelling of anisotropic fluxes for radiation belt protons to provide closed-form equations for vector proton fluxes and proton flux anisotropy in terms of standard omnidirectional flux models. These equations provide a flexible alternative to the data-based vector flux models currently available. At higher energies, anisotropy of trapped proton flux in the upper atmosphere depends strongly on the variation of atmospheric density with altitude. Calculations of proton flux anisotropies using present models require specification of the average atmospheric density along trapped particle trajectories and its variation with mirror point altitude. For an isothermal atmosphere, calculations show that in a dipole magnetic field, the scale height of this trajectory-averaged density closely approximates the scale height of the atmosphere at the mirror point of the trapped particle. However, for the earth's magnetic field, the altitudes of mirror points vary for protons drifting in longitude. This results in a small increase in longitude-averaged scale heights compared to the atmospheric scale heights at minimum mirror point altitudes. The trajectory-averaged scale heights are increased by about 10-20% over scale heights from standard atmosphere models for protons mirroring at altitudes less than 500 km in the South Atlantic Anomaly. Atmospheric losses of protons in the geomagnetic field minimum in the South Atlantic Anomaly control proton flux anisotropies of interest for radiation studies in low earth orbit. Standard atmosphere models provide corrections for diurnal, seasonal and solar activity-driven variations. Thus, determination of an "equilibrium" model of trapped proton fluxes of a given energy requires using a scale height that is time-averaged over the lifetime of the protons. The trajectory-averaged atmospheric densities calculated here lead to estimates for trapped proton lifetimes. These lifetimes provide appropriate time-averaging intervals for equilibrium models of trapped proton fluxes.     

The Perturbation Effect of Rotating Solar Polytropic Model on the Variation of Planetary Orbital Elements

In this paper the author examines the perturbation effect of rotating solar polytropic model on the variation of planetary orbital elements by the method of general perturbation in celestial mechanics and the polytropic model ofgaseous star in astrophysics. The perturbation variables of planetary orbital elements caused by the rotation, oblateness and central density of the sun for the polytropic index n = 3 are derived. The result shows clearly that the periodic perturbation effects are the orbital elements of all and the secular perturbation effects are the variation of the longitudes of perihelion, the ascending node and the mean anomaly of epoch. Finally, the author applies the obtained theoretical results to a calculation of the variation of orbital elements of four planets. The numerical results are given in Table 1.     

Effect of change in large and fast solar wind dynamic pressure on geosynchronous magnetic field

We present a comparison of changes in large and sharp solar wind dynamic pressure, observed by several spacecraft, with fast disturbances in the magnetospheric magnetic field, measured by the geosynchronous satellites. More than 260 changes in solar wind pressure during the period 1996--2003 are selected for this study. Large statistics show that an increase (a decrease) in dynamic pressure always results in an increase (a decrease) in the magnitude of geosynchronous magnetic field. The amplitude of response to the geomagnetic field strongly depends on the location of observer relative to the noon meridian, the value of pressure before disturbance, and the change in amplitude of pressure.     

Atmospheric neutrino flux at INO,South Pole and Pyhäsalmi

We present the calculation of the atmospheric neutrino fluxes for the neutrino experiments proposed at INO, South Pole and Pyhäsalmi. Neutrino fluxes have been obtained using ATMNC, a simulation code for cosmic ray in the atmosphere. Even using the same primary flux model and the interaction model, the calculated atmospheric neutrino fluxes are different for the different sites due to the geomagnetic field. The prediction of these fluxes in the present Letter would be quite useful in the experimental analysis.     

Radiation dose rates in Space Shuttle as a function of atmospheric density.

Current models of the inner trapped belt describe the radiation environment at times of solar minimum and solar maximum, respectively. These two models were constructed using data acquired prior to 1970 during a small solar cycle, and no valid model for the past two high solar cycles exists. There is a clear need to accurately predict the radiation exposure of astronauts at all times between the solar minimum and solar maximum, not only on the short duration Space Shuttle flights, but on the longer term stay onboard the Mir orbital station and the planned International Space Station (ISS). An analysis of the trapped absorbed dose rate, D, at six fixed locations in the habitable volume of the Shuttle shows a power law relationship, D=A rho-n, where rho is the atmospheric density, rho. The index, n, is weakly dependent on the shielding, decreasing as the average shielding increases. A better representation is provided by D=A tan-1 [(Xi-Xi c)/(Xi c-Xi m)], where Xi=ln(rho), and A, Xi c, and Xi m are constants. Xi c is related to the atmospheric density near the altitude of atmospheric cutoff. These relationships hold over nearly four decades of density variation and throughout the solar cycle. This then provides a method of calculating absorbed dose rate at anytime in the solar cycle. These empirically derived relations were used to predict the dose rates for eleven Space Shuttle flights carried out since January 1997. The predictions are in excellent agreement with measured values. This method reduces the uncertainties of a factor of about 2 for the AP-8 MIN/MAX models to less than 30%.     

Numerical analysis of CdS-CIGS interface configuration on the performances of Cu(In,Ga)Se2 solar cells

One dimension solar Cell Simulation package (SCAPS) is used to analyze the impact of the CdS-CIGS interface configuration on the performances of CIGS solar cells. We simulated the current-voltage characteristic of two models of the cell: one with a donor type defect (OVC model) and the other with acceptor type defect (P+ model) at the CdS-CIGS interface. The advantages and disadvantages of these CIGS surface configuration on the electrical parameters were discussed according to their thicknesses, defect density and carrier lifetime. The simulation results show that the model with the P+ layer has poor performance when its thickness and defect density increase, due to a huge distortion on the J-V characteristic. On the other hand, the OVC layer plays a fundamental role in the performance of CIGS solar cells. Better performances are obtained with the OVC model when the density of donor defect is in the range 10¹³ - 10¹⁵ cm⁻³, the charge carriers lifetime in the range 0.02 - 1 ns, and the thickness of the OVC layer in the range 200 - 400 nm.     

基于地基观测的时序卫星红外光谱建模与分析

针对地基观测的卫星红外光谱受复杂因素的影响和外场试验对测量卫星物性信息的缺乏,无法解释卫星红外光谱反演出特征的有效性和具体物理意义的问题,提出了一种基于地基观测的卫星热红外光谱的建模和分析的方法.首先,考虑了太阳辐射、地球辐射、卫星各面对探测器的可见情况、地基探测器可探测卫星的范围、大气衰减等因素的影响,更加准确地建立卫星热红外光谱模型.然后,以风云三号卫星为例,利用该模型计算了在观测时序上卫星在地基探测器入瞳上的3—14μm红外光谱辐照度;分析了影响卫星红外光谱变化的主要因素.最后,利用普朗克函数拟合卫星红外光谱,提取出特征与卫星的物性比较,并对其进行分析.结果表明:在各种影响因素中,由卫星运动引起的对探测器可见情况的改变是影响卫星红外光谱数据的主要因素.等效温度和等效面积物理含义能被有效地解释,等效温度接近于太阳帆板的温度,温差仅在15 K左右,等效面积能表征卫星投影面积的变化;发现利用帆板和本体有较大的温差,能实现帆板和本体的分离,并实现新特征的提取.     

Forecasting Earth's magnetopause, magnetosheath, and bow shock

The magnetopause and bow shock are two of the most important discontinuities in near Earth space, separating three distinct plasma regimes: the solar wind, magnetosheath, and the magnetosphere. Both discontinuities are sensitive to the solar wind conditions. They change their shape and location in space in response to upstream solar wind variations. Prediction of the location of a satellite relative to these two boundaries helps satellite operators to be prepared for major changes in plasma condition. The physical conditions near the magnetopause are useful information for magnetospheric models. Over the past decades, our observational knowledge and physical understanding of these regions have been advanced significantly. We have developed the capability of prediction. The location of the magnetopause and its dependence on the upstream conditions can be relatively accurately predicted. Prediction models have been tested extensively. The success rate is extremely high and the false-alarm rate is relatively low. A magnetosheath prediction model has been developed and tested. Some of the magnetosheath quantities can often be predicted fairly accurately. Others may have slightly larger errors. Further tests and scientific investigations of the causes of these errors are under way. Our ability to predict the location of the bow shock is very limited. More research is needed     

Dependence of InGaN solar cell performance on polarization-induced electric field and carrier lifetime

The effects of Mg-induced net acceptor doping concentration and carrier lifetime on the performance of a p-i-n InGaN solar cell are investigated. It is found that the electric field induced by spontaneous and piezoelectric polariza- tion in the i-region could be totally shielded when the Mg-induced net acceptor doping concentration is sufficiently high. The polarization-induced potential barriers are reduced and the short circuit current density is remarkably increased from 0.21 mA/cm2 to 0.95 mA/cm2 by elevating the Mg doping concentration. The carrier lifetime determined by defect density of i-InGaN also plays an important role in determining the photovoltaic properties of solar cell. The short circuit current density severely degrades, and the performance of InGaN solar cell becomes more sensitive to the polarization when carrier lifetime is lower than the transit time. This study demonstrates that the crystal quality of InGaN absorption layer is one of the most important challenges in realizing high efficiency InGaN solar cells.     

地表反照率对短波红外探测大气CO2的影响

在卫星短波红外遥感二氧化碳的过程中, 表征地表特征的地表反照率是影响探测精度的重要参数之一. 针对温室气体二氧化碳高精度探测的需求, 本文研究了地表反照率对正演模拟光谱和反演近地面二氧化碳平均柱浓度XCO₂的影响. 模拟计算结果显示, 地表反照率数值增大时, 观察的光谱强度也相应增大, 并且在O₂-A波段造成的光谱差异比1.6 μm波段高出一个数量级, 即地表反照率在O₂-A波段的影响比较大. 选取了两个不同地表类型的实际观测光谱, 仅改变O₂-A波段和1.6 μm波段地表反照率数值, 得出草地点在O₂-A波段地表反照率达到0.25的误差时, 会给XCO₂的反演结果造成大于1%的相对误差, 而1.6 μm波段的地表反照率变化对XCO₂的反演结果造成的误差可以忽略不计, 说明了地表反照率在反演XCO₂过程中的重要性主要来自对O₂-A波段的影响. 此研究表明了地表反照率在卫星遥感温室气体过程中的重要性, 为提高遥感探测二氧化碳的精度提供了重要的理论依据和指导.