Unmodeled perturbation effect on the orbit determination accuracy

The dependence of the estimates of an orbital parameter from unmodeled perturbations is considered that affect a space object but are not taken into account in the mathematical model of motion used in the paper. The expressions for Ensured characteristics of the accuracy in the estimate of the given parameter is obtained under the condition that there are known restrictions on mathematical expectations and the correlation function of these perturbations. The calculated results for the specific problem are given.     

Investigation of the motion of (99942) apophis asteroid using the SKIF cyberia multiprocessor computing system

We present the results of investigation of the dynamics of (99942) Apophis asteroid, which will undergo a very close encounter with the Earth on April 13, 2029. The region of possible motions of the asteroid is considered on the time interval (2004, 2040). In addition, it is shown that an increase of the observational interval (2004, 2006) until 2008 allowed us to reduce significantly the area of possible motions. All investigations were performed by numerical methods with the help of algorithms and software developed by us in the environment of parallel programming using the SKIF Cyberia multiprocessor computer of the Tomsk State University.     

Precise tracking and orbit determination of ERS-1

The application of the ERS-1 altimeter for investigating the global ocean circulation requires that the satellite's orbit, and in particular the radial position component, are known very accurately. Results are presented of orbit determination error analyses for 15 min, 2 revolution and 3 day data arcs, applying laser, TRANET and PRARE tracking systems. For the center part of the short arc radial orbit errors of less than 10 cm are achievable. For the multirevolution arcs the global rms radial error is found to be about 0.6 m and is dominated by the gravity field model error contribution. Finally, the feasibility of applying the altimeter as a tracking device is discussed and orbit determination results are presented from the processing of actual SEASAT altimeter data.     

Estimation of accuracy of close encounter performed by the bootstrap method

Ephemerides of the Solar System’s objects are calculated using dynamical models fitted to observations. The accuracy of these ephemerides can be estimated using statistical methods. The methods consist in constructing a set of possible orbits, based on observations. One of these methods, the bootstrap method of repeated sampling, has many advantages: minimal assumptions about distributions of observational errors, easy implementation, etc.     

基于线性特征的中分辨率航天遥感器MTF在轨评价及其在图像恢复中的应用

文章在简要介绍遥感器在轨MTF评测值在遥感图像处理中的意义基础上，分析了中分辨率遥感卫星成像过程MTF在轨测试的各种方法的适用性、算法和具体指标要求，提出了适合于中分辨率遥感卫星成像过程MTF的在轨评价方法，并剖析了遥感卫星成像过程中影响MTF的多种因素；最终以CBERS-02星CCD图像为对象进行了试验，并有效运用于图像恢复。     

The importance of exploring the asteroid belt

Following life's innate tendency to expand into every available space, technological civilizations will inevitably colonize the entire galaxy establishing space habitats around all its well-behaved stars. The most reasonable place in our solar system to test this possibility is the asteroid belt, which is an ideal source of raw materials for space colonies.     

Radar sounding of Mars from the orbit of the Mars-Express automatic interplanetary station

On the base of the laser altimetry results obtained using the orbital altimeter MOLA (the MGS mission) and the data of radio occultation experiments of transionospheric sounding of the Mars ionosphere, a method for interpretation of the planet radar sounding data is developed. The proposed method includes a program package for numerical simulation of the process of radiowave propagation through the media under study.     

A method of controlling asteroid collision with the Earth

The planet Earth has endured unwelcome “visitations” of space rocks many times. NASA and agencies of other nations have proposed concepts on how asteroids, in possible collision with planet Earth, can be diverted. These methods range from impulsive techniques using explosives, conventional and nuclear, to the slow nudging action of a spacecraft with powerful thrust. A methods not described elsewhere in any research, as far as the author knows, is presented in this paper. The methods of electrostatics will be employed to show how the new deflection concept can be developed to avoid asteroid collision with Earth.     

基于线性特征的中分辨率航天遥感器MTF在轨评价及其在图像恢复中的应用

文章在简要介绍遥感器在轨MTF评测值在遥感图像处理中的意义基础上,分析了中分辨率遥感卫星成像过程MTF在轨测试的各种方法的适用性、算法和具体指标要求,提出了适合于中分辨率遥感卫星成像过程MTF的在轨评价方法,并剖析了遥感卫星成像过程中影响MTF的多种因素;最终以CBERS-02星CCD图像为对象进行了试验,并有效运用于图像恢复。     

Missions to the asteroid anteros and the space of true anomalies

Three opportunities for missions to rendezvous ballistically with the Earth-crossing asteroid Anteros are studied to illustrate the requirements for a trip to a near-Earth minor planet. The rationale, sample payload, spacecraft requirements and trajectory characteristics of these opportunities are typical of a rendezvous mission to an accessible near-Earth object. Round trip ballistic trajectories to return small samples of the asteroid with launch dates between 1985 and 2000 are also presented. Contours of minimum total ΔV drawn in the space of launch and arrival true anomalies, given the designation Prime Rib curves, are introduced as a useful tool for mission design.     

Private property rights on asteroid resources: Assessing the legality of the ASTEROIDS Act

On June 10, 2014, a bill proposing to establish and protect (private) property rights on asteroid resources was introduced in the US House of Representatives.Regardless of its effective chances to become law, the presentation of the Bill raises numerous legal questions, particularly concerning the status of extraterrestrial natural resources and the consistency of what the Bill suggests with international space law.The purpose of the present viewpoint is to address and clarify the above questions.     

Optimization of passive orbit with the use of gravity maneuver

A high-precision method of calculating gravitational interactions is applied in order to determine optimal trajectories. A number of problems, necessary for determination of optimal parameters at a launch of a spacecraft and during its flyby near celestial bodies, are considered. The spacecraft trajectory was determined by numerical integration of the equations of passive motion of the spacecraft and of the equations of motion for planets, the Sun, and the Moon. The optimal trajectory of the spacecraft approaching the Sun is determined by fitting its initial conditions.     

Longitude-dependent effects of fragmentation events in the geosynchronous orbit regime

The effects of on-orbit fragmentation events on localized debris congestion in each of the longitude slots of the geosynchronous orbit (GEO) regime are evaluated by simulating explosions and collisions of uncontrolled rocket bodies in multiple orbit configurations, including libration about one or both of the gravitational wells located at 75°E and 105°W. Fragmentation distributions are generated with the NASA Standard Breakup Model, which samples fragment area-to-mass ratio and delta-velocity as a function of effective diameter. Simulation results indicate that the long-term severity and consequence of a GEO fragmentation event is strongly dependent upon parent body longitude at the epoch of fragmentation, which can spawn bi-annual “fragment storms” in high-risk longitude slots, driven by lower-energy fragments that have been captured and have started librating around the nearby gravitational well.     

Effects of eccentricity of the reference orbit on multi-tethered satellite formations

The paper discusses the relevance of eccentric reference orbits on the dynamics of a tethered formation, when a massive cable model is included in the analysis of a multi-tethered satellite formation. The formations examined in this study are hub-and-spoke (HAS) and closed-hub-and-spoke (CHAS) configurations for in-plane and Earth-facing spin planes. Stability of the formations is studied by means of numerical simulation, together with the evaluation of the effects of eccentricity on tether elongation, agents relative position, and formation orientation and shape.     

轨道转移推进系统及其发展趋势

根据轨道转移系统的应用分类（包括上面级类、空天飞机类、卫星类、飞船类和新概念类）,对各类型典型飞行器的推进系统进行了综合评述,分别总结了相关的技术方案和应用特点,并针对当前的研究热点,简要论述了未来的发展趋势,最后给出了几点结论.     

基于时间最短的SGKW共面打击轨道优化设计

天基对地打击动能武器(SGKW)用于从太空对地面高价值战略目标进行快速、准确的打击。针对最短打击时间要求,研究了SGKW共面打击轨道的优化设计方法。首先建立了SGKW的无量纲化平面运动模型,然后利用庞特里亚金极大值原理将时间最短共面打击轨道的最优控制问题转化为两点边值问题。由于约束条件中存在优化参数,一种基于"遗传算法 序列二次规划"的组合优化算法被用于求解未知参数。仿真结果验证了上述方法的有效性。     

Absolute IR-spectra from the measurement of Fourier-spectrometers aboard Meteor 25 and 28

It is well known that temperature- and watervapour-profiles, ozone concentration, other atmospheric constituents and the surface-radiation of the Earth can be determined by remote sensing in the IR radiation range with the aid of a satellite.

The narrow-band radiation measurements for remote sensing of the atmosphere and the Earth-surface can be realized either by various radiometers working in selected frequency channels or, continuously in a given frequency range, by spectrometers with fixed spectral resolution.

Fourier-spectrometers (FS) have been used in Earth-orbit only four times up to now: Nimbus 3, Nimbus 4, Meteor 25 and Meteor 28.

The most important technical parameters, the working regime and some aspects of date processing of the FSs working aboard of Meteor 25 and Meteor 28 are given. For the determination of calibrated absolute spectra a method is used that is based on the experience of the first experiment and on the long time stability of the spectrometers. The results obtained in laboratory calibration tests and in the orbit are described.     

On the one-body problem in the field of a tall cylinder in orbit

We describe the motion of a material point that is attracted by a tall, homogeneous cylinder. The cylinder moves on a circular orbit and points in the radial direction. The finite solution can be expanded in powers of two small parameters: the initial eccentricity of the orbital motion about the cylinder and the coupling parameter of the Coriolis force. Such expansions are given for the case of the indifferent longitudinal location. Solutions periodic in the polar angle are constructed. We do not find resonance effects or other large cumulative amplitude variations that might be due to the gravity-gradient and Coriolis force.     

Lichens survive in space: results from the 2005 LICHENS experiment

This experiment was aimed at establishing, for the first time, the survival capability of lichens exposed to space conditions. In particular, the damaging effect of various wavelengths of extraterrestrial solar UV radiation was studied. The lichens used were the bipolar species Rhizocarpon geographicum and Xanthoria elegans, which were collected above 2000 m in the mountains of central Spain and as endolithic communities inhabiting granites in the Antarctic Dry Valleys. Lichens were exposed to space in the BIOPAN-5 facility of the European Space Agency; BIOPAN-5 is located on the outer shell of the Earth-orbiting FOTON-M2 Russian satellite. The lichen samples were launched from Baikonur by a Soyuz rocket on May 31, 2005, and were returned to Earth after 16 days in space, at which time they were tested for survival. Chlorophyll fluorescence was used for the measurement of photosynthetic parameters. Scanning electron microscopy in back-scattered mode, low temperature scanning electron microscopy, and transmission electron microscopy were used to study the organization and composition of both symbionts. Confocal laser scanning microscopy, in combination with the use of specific fluorescent probes, allowed for the assessment of the physiological state of the cells. All exposed lichens, regardless of the optical filters used, showed nearly the same photosynthetic activity after the flight as measured before the flight. Likewise, the multimicroscopy approach revealed no detectable ultrastructural changes in most of the algal and fungal cells of the lichen thalli, though a greater proportion of cells in the flight samples had compromised membranes, as revealed by the LIVE/DEAD BacLight Bacterial Viability Kit. These findings indicate that most lichenized fungal and algal cells can survive in space after full exposure to massive UV and cosmic radiation, conditions proven to be lethal to bacteria and other microorganisms. The lichen upper cortex seems to provide adequate protection against solar radiation. Moreover, after extreme dehydration induced by high vacuum, the lichens proved to be able to recover, in full, their metabolic activity within 24 hours.     

Modal control of the planar motion of a long flexible beam in orbit

Attitude control techniques for the pointing and stabilization of very large, inherently flexible spacecraft systems are investigated. The attitude dynamics and control of a long, homogeneous flexible beam whose center of mass is assumed to follow a circular orbit is analyzed. In this study, first order effects of gravity-gradient are included, whereas external perturbations and related orbital station keeping maneuvers are neglected. A mathematical model which describes the system deflections within the orbital plane has been developed by treating the beam as having a maximum of three discretized mass particles connected by massless, elastic structural elements. The uncontrolled dynamics of this system are simulated and, in addition, the effects of the control devices are considered. The concept of distributed modal control, which provides a means for controlling a system mode independently of all other modes, is examined. The effect of varying the number of modes in the model as well as the number and location of the control devices are also considered.