A Brief Introduction and Recent Progress of the Geospace Double Star Program

The Geospace Double Star Project (DSP) consists of two small satellites operating in the near-earth equatorial and polar regions, respectively. The goals of DSP are: (1) to provide high-resolution field, particle, and wave measurements in some important near-earth active regions which have not been covered by current ISTP missions, such as the near-earth plasma sheet and its boundary layer, the ring current, the radiation belts, the dayside magnetopause boundary layer, and the polar region; (2) to investigate the trigger mechanisms of magnetic storms, magnetospheric substorms, and magnetospheric particle events,as well as the responses of geospace storms to solar activities and interplanetary disturbances; (3) to set up the models describing the spatial and temporal variations of the near-earth space environment.To realize the above goals, the equatorial satellite TC-1 and the polar satellite TC-2 will accommodate, respectively, eight instruments on board. TC-1was launched successfully in December 2003 while the polar satellite (TC-2)will be launched in July 2004. The orbit of the equatorial satellite TC-1 consists of a perigee at 550 km, an apogee at 60 000 km, and an inclination of about 28.5; while the orbit of the polar satellite will have a perigee of 700 km, an apogee of 40 000 km, and an inclination of about 90. The two satellites will take coordinated measurements with Cluster Ⅱ and will first form a "six-point exploration" in geospace.The operational status of TC-1 are introduced in this paper.     

地球同步轨道卫星混合推进转移轨道特性分析

以地球同步轨道卫星转移轨道设计为背景，针对全化学推进燃料消耗大和全电推进转移时间长的问题，开展了化学 电混合推进转移轨道优化设计与特性分析。首先，讨论了轨道倾角和近地点幅角变化对混合推进转移轨道的影响。研究表明，在混合推进优化设计中需要将轨道倾角作为优化变量之一。然后，以近地点半径、远地点半径、轨道倾角为优化变量生成搜索网格，得到过渡轨道集。针对每条过渡轨道，构建化学推进转移段和电推进转移段。其中化学推进段采用单圈兰伯特转移解算，电推进段采用混合法优化。最后，以燃料消耗和转移时间为指标，在搜索域内开展解算分析，研究了混合推进轨道在整个搜索域内的变化趋势。该方法可以提供具有不同燃料消耗和转移时间的混合推进转移解集，拓宽了解空间，可供轨道设计人员根据任务约束灵活选用。     

"Mir" radiation dosimetry results during the solar proton events in September-October 1989.

Using data from dosimetry-radiometry system "Liulin" on board of "Mir"-space station the particle flux and doserate during September-October, 1989 has been studied. The orbit of the station was 379 km perigee, 410 km apogee and 51.6 degrees inclination. Special attention has been paid to the flux and doserate changes inside the station after intensive solar proton events (SPE) on 29 of September, 1989. The comparison between the doses before and after the solar flares shows increase of the calculated mean dose per day by factor of 10 to 200. During the SPE on the 29 of September the additional dose was 310 mrad. The results of the experiment are compared with the data for the solar proton fluxes obtained on the GOES-7 satellite.     

月球探测器转移轨道的特性分析

主要分析了月球探测器由近地点出发，在假定末端条件不变的情况下，其转移轨道的特性参数对初始条件和变轨所需的速度脉冲等的影响；考虑的特性参数的变化包括转移轨道倾角的变化，近地点高度的变化和转移时间的不同．     

Energetic particle environment in near-Earth orbit.

The hazard of exposure to high doses of ionizing radiation is one of the primary concerns of extended manned space missions and a continuous threat for the numerous spacecraft in operation today. In the near-Earth environment the main sources of radiation are solar energetic particles (SEP), galactic cosmic rays (GCR), and geomagnetically trapped particles, predominantly protons and electrons. The intensity of the SEP and GCR source depends primarily on the phase of the solar cycle. Due to the shielding effect of the Earth's magnetic field, the observed intensity of SEP and GCR particles in a near-Earth orbit will also depend on the orbital parameters altitude and inclination. The magnetospheric source strength depends also on these orbital parameters because they determine the frequency and location of radiation belt passes. In this paper an overview of the various sources of radiation in the near-Earth orbit will be given and first results obtained with the Solar, Anomalous, and Magnetospheric Particle Explorer (SAMPEX) will be discussed. SAMPEX was launched on 3 July 1992 into a near polar (inclination 82 degrees) low altitude (510 x 675 km) orbit. The SAMPEX payload contains four separate instruments of high sensitivity covering the energy range 0.5 to several hundred MeV/nucleon for ions and 0.4 to 30 MeV for electrons. This low altitude polar orbit with zenith-oriented instrumentation provides a new opportunity for a systematic study of the near-Earth energetic particle environment.     

Satellite monitoring of anomalous effects in the ionosphere probably related to strong earthquakes

The paper presents simultaneously a satellite monitoring of plasma density disturbances and quasi-static electric fields on the one hand, and a ground earthquake monitoring, on the other. The INTERCOSMOS-BULGARIA-1300 satellite was launched on 7th August 1981. It had a perigee of 825 km, an apogee of 906 km and orbit inclination of 81.2°. For satellite’s orbits over sources of earthquakes M ⩾ 5.5 (seismic data of the World Data Center – Denver, Colorado), in the time period 12.08.1981–30.12.1981, some ionospheric effects are investigated. These effects can be considered eventually as possible earthquake precursors. The paper discusses specific anomalous effects observed in the ionosphere, which cannot be explained by factors of solar-magnetospheric origin. They could be associated with the earthquake growing processes in the lithosphere and troposphere zones above the source. In conclusion the results of ionosphere anomalous effects monitoring are proposed.     

Space debris mitigation strategies and practices in geosynchronous transfer orbits

Missions to geosynchronous orbits remain one of the most important elements of space launch traffic, accounting for 40% of all missions to Earth orbit and beyond during the four-year period 2000–2003. The vast majority of these missions leave one or more objects in geosynchronous transfer orbits (GTOs), contributing on a short-term or long-term basis to the space debris population. National and international space debris mitigation guidelines seek to curtail the accumulation of debris in orbits which penetrate the regions of low Earth orbit and of geosynchronous orbit. The orbital lifetime of objects in GTO can be greatly influenced by the initial values of perigee, inclination, and right ascension of the orbital plane, leading to orbital lifetimes of from less than one month to more than 100 years. An examination of the characteristic GTOs employed by launch vehicles from around the world has been conducted. The consequences of using perigees above 300 km and super-synchronous apogees, typically above 40,000 km, have been identified. In addition, the differences in orbital behavior of launch vehicle stages and mission-related debris in GTOs have been investigated. Greater coordination and cooperation between space launch service providers and spacecraft designers and owners could significantly improve overall compliance with guidelines to mitigate the accumulation of debris in Earth orbit.     

A study of positrons from Soviet nuclear powered satellites as tracers for magnetospheric research

Two Soviet satellites carrying nuclear reactors operated in circular 790 km orbits (65° inclination) in 1987 and 1988. Positrons generated in the satellites' surfaces by the intense reactor gamma radiation escaped and were trapped for periods of minutes to hours in the geomagnetic field. These positrons have been observed on many occasions by gamma ray sensors on the SMM satellite (in 500 km orbit) which identify the positrons by the 511 keV gamma rays created when they annihilate in the satellite surface. The SMM detector provides a time resolution of 64 milliseconds. It has recorded positron rise-times of less than 0.5 second (corresponding to a satellite travel distance of about 1 positron gyroradius) on many occasions as it encounters the low-L edge of positrons injected by the Soviet satellites as far as half-way around the earth. We are studying the potential of these sharply defined positron shells as magnetospheric tracers and as a means for examining particle diffusion and loss processes.     

Asymmetrical structure in the thermosphere during magnetic stroms as deduced from the CACTUS accelerometer data

During the last solar activity minimum, a great deal of very precise total density data was obtained in the equatorial regions from the CACTUS accelerometer experiment. Due to the eccentricity of the orbit, it is also possible to determine a density scale height by considering that the density profiles between the perigee (270 km) and 400 km are quasi-vertical. Densities and density scale heights are analysed during magnetic storms and their variations are compared with their behaviour during quiet periods. For densities as well as for scale heights, an asymmetrical structure in latitude and longitude is exhibited with respect to the magnetic equator. Their values are relatively higher in the northern hemisphere than in the southern one. The hypothesis (previously suggested) of a greater energy input in the southern hemisphere inducing asymmetrical winds, explains the results well.     

Spot 1 end of life disposition manoeuvres

The Earth observation satellites of the SPOT family are on a Sun-synchronous orbit at 822 km altitude. The on-orbit lifetime of objects at this altitude is about two centuries, which represents an important risk to the other satellites.The space debris issue has caused the main Agencies to adopt mitigation guidelines with the objective to reduce the population of objects orbiting the Earth. In 1999, CNES published its own standard presenting the management, design and operation rules. This document is fully compliant with the Inter Agency Space Debris Coordination Committee (IADC) mitigation guidelines approved in 2002 by 11 Space Agencies and submitted to United Nations – Committee on Peaceful Uses of Outer Space in February 2003.The space debris mitigation requirements expressed in the CNES standard and in the IADC mitigation guidelines limit the orbital lifetime in LEO to less than 25 years. Although not applicable to Spot 1, launched earlier in 1986, this rule was voluntarily applied and the decision to deorbit Spot 1 was taken.The corresponding operations, performed in November 2003, were complex due to a large number of constraints such as the unusual flight domain, the on-board sensors, the short ground station visibilities or the uncertainties in the estimation of the remaining fuel in the tanks. In the preliminary phase, the orbit was lowered 15 km below the operational orbit to avoid any collision risk with the other Spot satellites. Then, in a second phase, a series of eight apogee boosts lowered progressively the perigee altitude to 619 km. Finally, a large last manoeuvre was performed to empty the tanks and to reduce the perigee altitude the maximum amount. A succession of four ground stations visibilities allowed a real time monitoring of this manoeuvre. In particular the effect of gas bubbles in the propulsion system was observed through telemetry confirming the fuel depletion. The batteries were then disconnected and the telemetry emitter was switched off. According to the obtained perigee altitude, the on-orbit lifetime of Spot 1 should be about 18 years, which meets the space debris mitigation requirements.     

Global pictures of the ozone field,from high altitudes,from DE-I

Using the imaging instrumentation aboard the Dynamics Explorer spacecraft (DE-I), total column ozone densities are obtained in the sunlit hemisphere by measuring the intensities of backscattered solar ultraviolet radiation with multiple filters and multiple photometers. The high apogee altitude (23,000 km) of the eccentric polar orbit allows high resolution global-scale images of the terrestrial ozone field to be obtained within 12 minutes. Previous ozone-monitoring spacecraft have required much longer time periods for comparable spatial coverage because of their lower altitudes (<1200 km). The much higher altitude of DE-I also provides hours of continuous imaging of features compared to minutes or seconds with previous spacecraft. Near perigee, high resolution images can be gained with pixel size as small as 3 km to view mesoscale atmospheric variations. Utilizing these data, the effects of planetary-scale, synoptic-scale, and mesoscale dynamical processes, which control the distribution of ozone near the tropopause, can be studied. Preliminary results show short-term (less than one day) variations in the synoptic ozone field and these variations appear to be in accord with meteorological data. Spatial variations in the ozone field are found to be highly negatively correlated with tropopause altitude.     

一种空间协同探测系统的星座设计方法

研究了由多颗合成孔径雷达卫星和一颗可见光卫星构成的空间协同探测系统的工作模式.根据太阳同步轨道和冻结轨道的特点,结合近地轨道遥感卫星的应用需求,选择了轨道半长轴、偏心率、倾角、近心点幅角.考虑到卫星偏航控制对覆盖性能的影响,在不动的地心坐标系中推导了卫星观测方向与地表交点的表达式,提出了确定系统中各颗卫星的升交点赤经和过近心点时刻的算法.给出了包含两颗合成孔径雷达卫星与一颗可见光卫星的协同探测系统的星座设计结果,并利用国际公认的卫星软件工具包Satellite ToolKit进行了验证,表明该设计方法是正确的.     

Thermospheric heating at high latitudes as observed from intercosmos-Bulgaria-1300 and dynamics explorer-B

This paper reports the results of the first direct comparison of near simultaneous measurements obtained by the INTERCOSMOS-BULGARIA-1300 and the DYNAMICS EXPLORER-B satellites. The ICB-1300 is in a near circular orbit at a mean height of about 850 km. The DE-B satellite in an elliptical orbit is sometimes directly below the ICB-1300 satellite providing an opportunity to investigate the response of the thermosphere to particle fluxes from the magnetosphere. Energy fluxes in the range 0.2–15 keV are obtained from an energetic particle analyzer on board the ICB-1300 satellite. The thermospheric composition and density are obtained by a neutral gas mass spectrometer (NACS) on the DE-B satellite. During the period 20 August–20 November, 1981, observations show tht the times and locations of maxima in magnetospheric energy deposition coincide with regions of maximum thermospheric upwelling characterized by composition changes.     

基于间接法在线能力评估和自主规划技术研究

针对运载火箭推力故障条件下的自主救援任务,研究了一种基于间接法的在线能力评估和自主规划方法.构建了以入轨点能量最大为最优性能指标的最优控制问题.通过数值方法探讨了在满足轨道倾角和入轨点路径角约束条件下,入轨点速度、远地点和近地点跟入轨高度之间的关系,设计了一种与入轨高度相关的特征量来对入轨能力进行评估.以近地点最高为救...     

OPTIS – A Satellite test of Special and General Relativity

OPTIS has been proposed as a small satellite platform in a high elliptical orbit (apogee 40,000 km, perigee 10,000 km) and is designed for high precision tests of foundations of Special and General Relativity. The experimental set-up consists of two ultrastable Nd:YAG lasers, three crossed optical resonators (monolithic cavities), an ensemble of atomic clocks, an optical comb generator, laser tracking devices and a drag-free control system. OPTIS enables improved tests of (1) the isotropy and (2) constancy of the speed of light, (3) special relativistic time dilation, (4) the universality of the gravitational redshift by comparison of various clocks, can measure (5) the absolute value of the gravitational redshift, (6) the Lense–Thirring effect and (7) the perigee advance and (8) can make a test of a hypothetical Yukawa part in the gravitational potential. To avoid any influence from atmospheric drag, solar radiation, or Earth albedo, the satellite needs drag-free control to depress the residual acceleration down to 10⁻¹⁴ m/s² in the frequency range between 10⁻² and 10⁻³ Hz. Precise thermal control must be used to stabilize the cavity temperature to within one part in 10⁷ at time scales of 100 s and to one part in 10⁵ on the orbit time scale.     

利用近地点磁场探测数据确定卫星自旋轴参数

阐述了利用近地点磁场探测数据确定卫星自旋轴参数的理论方法和实施步骤,并说明了这种研究对卫星运行和科学探测的重要性.特别强调了需要注意的基本条件,即卫星必须自旋稳定且近地点不很高(1000 km以下).这种方法关键的步骤是,根据卫星轨道数据定出模型磁场数值,比较近地点星载磁强计探测数据和近地点地磁模型数值确定卫星自旋轴的指向.通过对TC-1和TC-2卫星姿态的具体计算,对确定精度和应用效果进行了分析和比较.结果表明,在实际的卫星应用过程中此方法和措施非常有效,在科学分析和将来的卫星运行工程中具有重要的应用意义.      

Optimal two-impulse rendezvous with terminal tangent burn considering the trajectory constraints

The two-impulse orbital rendezvous problem with a terminal tangent burn between coplanar elliptical orbits is studied by considering a lower bound on perigee radius and an upper bound on apogee radius for the transfer orbit. This problem requires that two spacecraft arrive at the rendezvous point with the same arrival flight-path angle after the same flight time. The admissible range of the final true anomaly that meets the perigee and apogee constraints is obtained in closed form. The revolution number of the transfer orbit is expressed as a function of the true anomaly and the revolution numbers of the initial and final orbits. All the feasible solutions are obtained with a bound on the revolution number of the final orbit. Then, the minimum-fuel one is determined by comparing their costs. Finally, two numerical examples are provided to obtain all the feasible solutions for given initial impulse points and the optimal solution with the initial coasting arc. Numerical results show that the minimum-fuel solution for the terminal tangent burn rendezvous is close to that for the cotangent rendezvous when the rendezvous time is long enough; however, the cotangent rendezvous may not exist when the rendezvous time is short.     

利用卫星两行轨道根数反演热层密度

两行轨道根数（TLEs）是基于一般摄动理论产生的用于预报地球轨道飞行器位置和速度的一组轨道参数,通过求解大气阻力微分方程,可反演出热层大气密度. 本文选取近圆轨道CHAMP卫星和椭圆轨道Explorer8卫星,以两行轨道根数数据为基础,计算反弹道系数,并根据不同轨道特征采用两种不同反演方法对热层大气密度进行研究. 结果表明,这两种方法反演得到的大气密度与实测值均符合较好,其中CHAMP卫星的反演结果和经验模式值相对于实测值的误差分别为7.94%和13.94%,Explorer8卫星的误差分别为9.04%和14.32%. 相比模式值,利用两行轨道根数数据反演的热层大气密度更接近于实测值,说明该方法可以作为获取大量可靠大气密度数据的一种有效途径.