太阳光压模型中面质比误差对IGSO卫星轨道预报的影响分析

太阳光压是影响高轨卫星轨道精密确定的主要因子之一,这种摄动的有效模制将进一步改进卫星轨道的预报精度.主要对太阳光压模型中面质比误差对地球倾斜同步轨道卫星轨道预报的影响进行了分析.20％面质比参数标定误差对地球倾斜同步轨道卫星位置预报影响仿真结果显示:一天内前16h,x、z分量的预报误差幅度相对较小,y分量误差相对较大;一天内最后8h,x、y、z各分量误差发散明显,但z分量的误差发散程度较大.20％面质比参数标定误差对地球倾斜同步轨道卫星速度预报影响仿真结果显示,一天内,x、y、z各分量的预报误差幅度不超过1 mm/s.     

自由段弹道识别及快速预警

针对地面预警雷达捕获跟踪空间目标和实时测轨获取的目标轨道根数,提出了一种基于目标轨道运动特征识别自由飞行导弹及推算发点、落点的处理方法.该方法分为二体模型求解初交点和摄动修正两部分,分别进行迭代计算.数值实验结果表明:该处理方法计算收敛速度快,每次仅需6~8次迭代,能够满足导弹预警的高时效性要求.     

掩星软件OCCULT使用指南（二）

（接上期） 小行星掩星 此程序可以计算小行星、行星和其卫星掩星的预报,预报的结果可以在屏幕上直接显示出来,也可以直接打印或存到文件中。在计算之前,我们首先需要更新小行星轨道根数,有两种方法：一是使用软件自动下载更新（你的电脑里需要安装FTP软件）,使用软件自动下载更新方法如下：     

人造卫星一阶摄动理论的平均根数迭代法

本文对人造卫星一阶摄动理论中的两类平均根数迭代法进行了讨论。分析表明:采用平均根数-2(吻切根数减去一阶短周期项)比采用平均根数-1(吻切根数减去全部一阶周期项)至少有以下四个优点:(1)定义简单明确,在一阶理论中,平均根数-2仅与地球形状的 J_2部分有关;(2)可以克服平均根数-1这一方法本身所引起的临界倾角(i=63°26′或116°34′)的实际计算困难;(3)适用于任何无奇点变量的根数系统,可以消除小偏心率(e=0附近)和sin i=0附近的实际计算困难。(4)适用于同时考虑全部摄动因素。     

利用气球卫星的轨道变异研究太阳活动的一些问题 Ⅰ.力学问题

本文利用抛物旋转体坐标系讨论具有大面积质量比的球状气球卫星的运动特征。计算了地球椭率、太阳光、大气阻力诸因素对本文所规定的褚轨道根数的摄动。推导公式中着眼于高空(距地1000公里左右)!近圆轨道的近似,目的在于应用所观测的回声一号气球卫星数据,计算上述经常起作用的摄动因素的目的,是要发现有无另外的因素扰乱了它正常的轨道,以和太阳活动此较。在这篇文章里,我们只推导一些必须的公式,并作计算实例来验证我们的公式。详细结果的讨论,留待第二部分中去论述。     

人造卫星三阶摄动理论初探

本文研究了Vinti型中间轨道摄动方程的原则解法,提出了一种有实用意义的半分析、半数值方法。用的基本手段是平均根数法,平均根数σ~*及短周期项△σ_s的定义为:这里,σ为密切根数,T为卫星运动周期,t~*为虚拟时间变量。短周期项△σ_s(准到三阶)可用Fourier分析方法求得,而百(dσ~*)/(dt)(准到四阶)则用数值平均方法计算。本方法可用来处理高精度的卫星激光观测。     

人造卫星二阶摄动理论的半分析、半数值方法

本文提出了一种新的计算人造卫星二阶摄动的半分析、半数值方法,其基本思想是: i),采用σ~＊作为基本根数系统;这里σ~＊是从密切根数σ中扣去短周期项△σ_s的平根数。 ii),σ~＊的长期、长周期变率(准到三阶)由密切限的变率dσ/dt的数值平均求得。 ii),计算dσ/dt中所用的密切根数σ,由σ~＊加上短周期项△σ_s,而得,其中一阶短周期项△σ_s~((1))用分析公式计算,二阶短周期项△σ_s~((2))用Fourier分析方法求取。由于采用了σ~＊作为根数系统,克服了密切根数σ数值方法的积分步长短、计算时间长、积累误差大等缺点;由于dσ/dt、△σ_s~((2))用数值方法计算,又避免了繁复的公式推导,兼得了计算公式简单,程序编制方便等优点。用本方法计算二阶摄动,计算时间比经典的数值方法要节省十分之九,所占内存的大小可比分析方法节省4/5—5/6。本文还讨论了微分方程的数值积分方法,改进了迭代过程,使得它更适合于卫星动力测地中测轨的要求。本文还给出了用本方法计算的数值结果。数值结果表明:用本方法测轨,向径、垂迹方向误差小于0.1米,沿迹方向误差小于1米。     

采用重置参数的轨道改进算法

当使用精度差的初始根数作定轨计算时,被估值的模型参数会吸收初值中所含误差而偏离其合理数值(如CD约为2.2),使定轨计算过程的RMS已不再变化,但轨道收敛到与实际状态有偏离的轨道上。文中给出的算例采用重置被歪曲的估值模型参数方法,首先以TLE根数为初值用精密定轨程序解条件方程,然后以第一轮迭代计算结果作为初始根数并重置模型参数,再进行第二轮迭代计算,使定轨计算结果收敛到正确轨道上,文中还使用另一颗激光卫星的双行根数作初值验证了该方法的有效性。较好地解决了因初值不准所引起的定轨计算不收敛,或收敛到与实际状态有偏离的轨道上的问题。最终得出的RMS达到厘米级精度。文中图示了两次定轨计算的RMS变化曲线图、残差分布图,迭代过程的资料采用率及定轨计算结果。     

空间VLBI观测的（u,v）覆盖平面

一个专用VLBI研究的卫星－－VSOP将于1996年9月发射，根据该卫星的轨道根数，我们讨论空间VLBI观测中的（u,v）覆盖及它所受到的影响，以射电源Mkn421作为实例，给出了相应的计算结果。同时也给出了该源在15GHz和43GHz的最新的10台站VLBI观测结果。     

卫星轨道预报的一种分析方法

人造地球卫星的轨道预报是空间环境监测和实时跟踪测量中一个重要环节，由于监测对象众多，要求精度也不太高，通常采用分析法预报．在已有分析法得到t时刻平均根数的基础上给出一种轨道预报方法，由t时刻的平均根数给出该时刻卫星的位置和速度，在此基础上将地球非球形引力摄动的周期项直接用卫星直角坐标的位置和速度分量表示，这样可以避免在计算轨道根数变化的周期项时出现的奇点问题，从而对根数的选择无特殊要求，可适用于各种轨道，简化预报程序和相应的软件，提高预报效率。     

Mass density of the upper atmosphere derived from Starlette’s Precise Orbit Determination with Satellite Laser Ranging

The atmospheric mass density of the upper atmosphere from the spherical Starlette satellite’s Precise Orbit Determination is first derived with Satellite Laser Ranging measurements at 815 to 1115 km during strong solar and geomagnetic activities. Starlette’s orbit is determined using the improved orbit determination techniques combining optimum parameters with a precise empirical drag application to a gravity field. MSIS-86 and NRLMSISE-00 atmospheric density models are compared with the Starlette drag-derived atmospheric density of the upper atmosphere. It is found that the variation in the Starlette’s drag coefficient above 800 km corresponds well with the level of geomagnetic activity. This represents that the satellite orbit is mainly perturbed by the Joule heating from geomagnetic activity at the upper atmosphere. This result concludes that MSIS empirical models strongly underestimate the mass density of the upper atmosphere as compared to the Starlette drag-derived atmospheric density during the geomagnetic storms. We suggest that the atmospheric density models should be analyzed with higher altitude acceleration data for a better understanding of long-term solar and geomagnetic effects.     

月球重力场对绕月低轨卫星的长期影响

从解析形式出发,利用月球重力场模型JGL165P1,分析了月球重力场(带谐项)对绕月低轨卫星的长期影响。为了减少计算误差,保证计算精度,在分析解中使用循环公式来计算倾角函数。结果指出对于一个高度为100km的极月轨道卫星,冻结轨道存在的可能性不大,但是当轨道倾角在i=90°附近或者高度再高一些,则有可能存在冻结轨道;对于100km高的初始圆轨道,卫星在无控的情况下半年内将会坠落到月球表面,如果高度增加到200km,则不进行轨道控制也不会坠落到月面上。利用仿真软件GEODYN解算出来的结果证实了上述结论。     

Physical parameters of the atmosphere of Venus from Venera 15 and 16 missions

The following physical parameters have been computed for the atmosphere of Venus between 65 and 90 km, by intervals of 1 km. (1) Pressure, (2) Density, (3) Speed of sound, (4) Number density, (5) Density scale, (6) Pressure scale, (7) Collisional frequency, (8) Mean particle velocity (9) Mean free path, (10) Columnar mass, (11) Viscosity. For these calculations we have used the temperature altitude measurements of Venera 15 and 16 at 52 °N and 72 °N latitudes, the night and 70 °N and 72 °N latitudes the day.     

Diurnal CO variations in the Venus mesophere from CO microwave spectra

Microwave spectra of carbon monoxide (¹²CO) in the mesosphere of Venus were measured in December 1978, May and December 1980, and January, September, and November 1982. These spectra are analyzed to provide mixing profiles of CO in the Venus mesosphere and best constrain the mixing profile of CO between ～ 100 and 80 km altitude. From the January 1982 measurement (which, of all our spectra, best constrains the abundance of CO below 80 km altitude) we find an upper limit for the CO mixing ratio below 80 km altitude that is two to three times smaller than the stratospheric (～65 km) value of 4.5 ± 1.0 × 10^?5 determined by P. Connes, J. Connes, L.D. Kaplan, and W. S. Benedict (1968, Astrophys. J.152, 731–743) in 1967, indicating a possible long-term change in the lower atmospheric concentration of CO. Intercomparison among the individual CO profiles derived from our spectra indicates considerable short-term temporal and/or spatial variation in the profile of CO mixing in the Venus mesosphere above 80 km. A more complete comparison with previously published CO microwave spectra from a number of authors specifies the basic diurnal nature of mesospheric CO variability. CO abundance above ～ 95 km in the Venus atmosphere shows approximately a factor of 2–4 enhancement on the nightside relative to the dayside of Venus. Peak nightside CO abundance above ～95 km occurs very near to the antisolar point on Venus (local time of peak CO abundance above ～95 km occurs at 0.6_?0.6^+0.7 hr after midnight on Venus), strongly suggesting that retrograde zonal flow is substantially reduced at an altitude of 100 km in the Venus mesosphere. In contrast, CO abundances between 80 and 90 km altitude show a maximum that is shifted from the antisolar point toward the morningside of Venus (local time of peak CO abundance between 80 and 90 km occurs at 8.5 ± 1.0 hr past midnight on Venus). The magnitude of the diurnal variation of CO abundance between 80 and 90 km is again, approximately a factor of 2–4. Disk-averaged spectra of Venus do not determine the exact form for the diurnal distribution of CO in the Venus mesosphere as indicated by comparison of synthetic spectra, based upon model distributions, and the measured spectra. However, the offset in phase for the diurnal variation for the >95 km and 80–90-km-altitude regions requires an asymmetric (in solar zenith angle) distribution.     

The fall of the St-Robert meteorite

Abstract The St-Robert (Québec, Canada) meteorite shower occurred on 1994 June 15 at 0h02m UT accompanied by detonations audible for >200 km from the fireball endpoint. The fireball was recorded by visual observers in Vermont, New York State, New Hampshire, Québec and Ontario as well as by optical and infrared sensors in Earth-orbit. Penetration to an altitude of 36 km occurred ～60 km to the northeast of Montreal, where the bolide experienced several episodes of fragmentation. A total of 20 fragments of this H5 chondrite, comprising a total mass of 25.4 kg, were recovered in an ellipse measuring 8 × 3.5 km. One fragment of the shower partially penetrated the aluminum roof of a shed. Interpretation of the visual and satellite data suggests that the fireball traveled from south-southwest to north-northeast, with a slope from the horizontal of 55°–61°. A statistical evaluation of the likely heliocentric orbits for the body prior to collision with the Earth, coupled with theoretical modeling of the entry, suggests an entry velocity in the range of 12.7–13.3 km/s; the meteoroid had moved in a low-inclination orbit, with orbital perihelion located extremely close to the Earth's orbit. From satellite optical data, it is found that the photometric mass consumed during the largest detonation is ～1200 kg. Estimation of the amplitude of the acoustic signal detected by the most distant observer yields a source energy near 0.5 kt TNT equivalent energy, which corresponds to a mass of order 10 metric tonnes. This measure is uncertain to approximately one order of magnitude. Theoretical modeling of the entry of the object suggests a mass near 1600 kg. Cosmogenic radionuclide activities constrain the lower initial mass to be ～700 kg with an upper limit near 4000 kg. Seismic data possibly associated with the fireball suggest extremely poor coupling between the airwave and the ground. The total mass estimated to have reached the ground is ～100 kg (in material comprising >55 g fragments), while the preatmospheric mass is found to be most probably in the range of 1200–2000 kg.     

Values of the Atmospheric Density at 280 km Obtained from Spin Drag Data of COSMOS 54 Rocket

A set of atmospheric density values at a height of 280 km between MJD 39675—39702 is determined by using the spin drag data of COSMOS 54 rocket. For this purpose photometric observations from five tracking stations and data about the satellite and its orbital evolution were used. The density values determined firstly at the perigee height were reduced at a standard height of 280 km and then compared with density values determined by using orbital drag data of this rocket at the same height and in the same time interval. The agreement between the two sets of densities (determined by using two different methods) is satisfactory.     

MSISE90大气密度模型及其在GPS无线电掩星中的应用

本文简略介绍了MSISE90大气密度模型，它是以提高低高度大气密度计算精度为目标，基于MSIS86模式，采用不相干散射雷达和卫星质谱仪测量资料，在半经验公式的基础上进行拟合处理而成；并指出了Hedin对该模型的修正之处。并将该模型应用于GPS无线电掩星反演中性地球大气参数的先验温度序列的生成。     

Atmospheric densities from satellites and rocket observation

Atmospheric densities deduced from high altitude rocket nights have a large variability of which a large percentage is undoubtedly due to measurement errors. Prior to the IGY, the available density data gave reasonable support to the ARDC Model Atmosphere. Satellite data which at first appeared to be inconsistent with rocket data are now seen to be continuous with the average of presently available rocket derived densities. The current data suggest the revision of the 1956 ARDC Model to lower densities near 100 km altitude and demand higher densities above 160 km (a twenty fold increase at 500 km). The revised altitude distribution of density implies (1) lower temperatures at 90 km and (2) temperature-altitude gradients between 105 and 160 km (two times the molecular-scale-temperature gradient of the 1956 ARDC Model). Density-altitude and temperature-altitude profiles for a revised model atmosphere are discussed.     

Effects of the Absorption of Solar XUV Radiation by the Earth's Upper Atmosphere at Altitudes of 100–500 km in the X-ray Solar Images Obtained Onboard the Coronas-I (TEREK Telescope) and Coronas-F (SPIRIT X-ray Complex) Satellites

We consider the effects of the absorption of solar XUV radiation by the Earth's atmosphere that were observed in the solar images obtained with the TEREK-K telescope onboard the Coronas-I satellite in May–June 1994 at low solar activity and with the SPIRIT instrumentation onboard the Coronas-F satellite in October–November 2001 at maximum solar activity. The solar images were recorded during the satellite occultation: in the 175- and 304-A spectral ranges onboard Coronas-I with the TEREK-K telescope and in the 175-, 304-, and 8.42-A ranges onboard Coronas-F with the SPIRIT instrumentation. Based on the XUV solar images obtained during atmospheric sounding, apart from the total absorption, we can determine the direction of the atmospheric density gradient and study the local absorption variations with altitude on spatial scales of less than 1 km. The described method can significantly supplement the data obtained in studies of the upper atmosphere by the methods of mass spectrometry, incoherent radar scattering, and the drag of orbital spacecraft.     

Some aspects of a global thermospheric density model deduced from the analysis of the orbit of Intercosmos 13 rocket (1975-22B)

An empirical density formula is explored as a practical model for atmospheric variations and satellite drag analyses. Expanding neutral air density as a series of spherical harmonics and normalizing to a fixed height, an analytical expression for the rate of change of the mean motion is developed for an oblate atmosphere with density scale height varying linearly with altitude. A subset of the coefficients in the density expansion is determined by least-squares adjustment to the observed orbital decay rate of Intercosmos 13 rocket (1975-22B) for the period May 1975–December 1979. Comparisons against four thermospheric models are undertaken for the solar activity effect and the diurnal and semi-annual variations. Given the even spread of data and the increase in solar activity from low to moderate, the air density variation with solar activity is particularly well determined. The results support the “J77” model revealing a greater increase in density with the daily solar index than either the “MSIS” or “DTM” thermospheric models near the solar minimum. Analyses of the diurnal and semi-annual variations are less exact.