Adiabatic invariants of the solar system and exo-planet systems and soliton-like disturbances of Alfvenic plasma proto-ring

Some new results are presented concerning quantization of observed parameters of the Solar System and exo-planet systems, as well as some functions of these parameters. General adiabatic invariants are introduced including (for the Solar System) orbital quantum numbers of planets and quantum numbers characterizing their proper rotation (spin). The quantization of parameters relating to satellite and exo-planetary systems is considered. Some arguments are presented about the influence of nonlinear disturbances of Alfvenic plasma proto-ring of the type of Frenkel-Kontorova (FK) and Russell-Korteweg-de Vries (KdV) solitons on formation of elite rings and their evolution with conservation of corresponding invariants. A mechanical model is synthesized that describes nonlinear FK soliton type disturbances of magnetized plasma.     

On the deployment dynamics of tether connected two-body systems

A general formulation of the deployment dynamics of tether connected two-body systems taking into account the three dimensional librational motion, longitudinal and transverse vibrations of the continuous tether, eccentricity of the orbit and aerodynamic drag in a rotating, oblate atmosphere, is presented. Three simple deployment procedures (uniform, exponential and their combination) are considered. In the beginning analytical solutions are obtained for the degenerate case of negligible vibrations in a circular orbit, which help in establishing trends for the more general situation. This is followed by the general dynamics of the system investigated through integration of the linearized autonomous equations of motion numerically. Typical plots are presented which describe the effects of various system parameters on the tether dynamics during deployment of a subsatellite from the Space Shuttle.     

Ballistics, navigation, and motion control for a spacecraft during its landing on the surface of Phobos

Basic concepts and algorithms laid as foundations of the scheme of landing on the Martian moon Phobos (developed for the Phobos-Grunt project) are presented. The conditions ensuring the landing are discussed. Algorithms of onboard navigation and control are described. The equations of spacecraft motion with respect to Phobos are considered, as well as their use for correction of the spacecraft motion. The algorithm of estimation of the spacecraft’s state vector using measurements with a laser altimeter and Doppler meter of velocity and distance is presented. A system for modeling the landing with a firmware complex including a prototype of the onboard computer is described.     

应用变速控制力矩陀螺的卫星姿态机动的非线性控制

研究了以变速控制力矩陀螺(VSCMG)作为执行机构的卫星多目标快速机动的控制问题。首先建立了带有多个变速控制力矩陀螺的航天器姿态动力学模型,采用修正的罗德里格斯参数(MRP)描述姿态运动。在考虑执行机构饱和、机动速率限制、控制带宽限制等情况下,设计了基于Lyapunov理论的非线性姿态反馈控制器。针对外部干扰会使控制力矩陀螺的框架角偏移其标称值的情况,采取磁补偿控制来保持框架角在一定范围变化。以采用VSCMG为执行机构的某卫星为例进行了数值仿真,仿真结果验证了提出的非线性姿态反馈控制器的有效性,采取的磁补偿控制也很好地抑制了变速控制力矩陀螺框架角的偏移。     

Study of the Microphonics for Prospective Space-Based Neutron and Gamma-Ray Detectors and Methods for its Suppression

The results of testing a number of space-based detectors that contain PMTs or high-voltage electrodes for the noise from the microphonics that occurs in the signal path due to external mechanical action have been presented. A method for the vibration isolation of instruments aboard a spacecraft has been proposed to reduce their responsivity to vibrations.     

First results of investigating the space environment onboard the Universitetskii-Tatyana satellite

The complex of scientific pay load installed onboard the research and educational Universitetskii-Tatyana microsatellite of Moscow State University is described. The complex is designed to study charged particles in the near-earth space and ultraviolet emissions of the atmosphere. Data of the measurements of charged particle fluxes in the microsatellite orbit are presented, spectra are calculated, and the dynamics of penetration boundaries for protons of solar cosmic rays (SCR) during geomagnetic disturbances in 2005 is investigated. Intensities of the ultraviolet emission are measured in the entire range of variation of the atmospheric irradiation, as well as intensities of auroras in the polar regions of the Northern and Southern hemispheres. The experimental data on flashes of ultraviolet radiation (transient light phenomena in the upper atmosphere) are considered, and some examples of oscillograms of their temporal development and their distribution over geographical coordinates are presented. Original Russian Text ? V.A. Sadovnichy, M.I. Panasyuk, S.Yu. Bobrovnikov, N.N. Vedenkin, N.A. Vlasova, G.K. Garipov, O.R. Grigorian, T.A. Ivanova, V.V. Kalegaev, P.A. Klimov, A.S. Kovtyukh, S.A. Krasotkin, N.V. Kuznetsov, S.N. Kuznetsov, E.A. Muravyeva, I.N. Myagkova, N.N. Pavlov, R.A. Nymmik, V.L. Petrov, M.V. Podzolko, V.V. Radchenko, S.Ya. Reisman, I.A. Rubinshtein, M.O. Riazantseva, E.A. Sigaeva, E.N. Sosnovets, L.I. Starostin, A.V. Sukhanov, V.I. Tulupov, B.A. Khrenov, V.M. Shakhparonov, V.N. Sheveleva, A.V. Shirokov, I.V. Yashin, V.V. Markelov, N.N. Ivanov, V.N. Blinov, O.Yu. Sedykh, V.P. Pinigin, A.P. Papkov, E.S. Levin, V.M. Samkov, N.N. Ignatiev, V.S. Yamnikol, 2007, published in Kosmicheskie Issledovaniya, 2007, vol. 45, No. 4, pp. 291–305.     

Observations of the auroral hectometric radio emission onboard the <Emphasis Type="Italic">INTERBALL-1</Emphasis> satellite

The results of five-year (1995–2000) continuous observations of the auroral radio emission (ARE) in the hectometric wavelength range on the high-apogee INTERBALL-1 satellite are presented. Short intense bursts of the auroral hectometric radio emission (AHR) were observed at frequencies of 1463 and 1501 kHz. The bursts were observed predominantly at times when the terrestrial magnetosphere was undisturbed (in the quiet Sun period), and their number decreased rapidly with increasing solar activity. The bursts demonstrated seasonal dependence in the Northern and Southern hemispheres (dominating in the autumn-winter period). Their appearance probably depends on the observation time (UT). A qualitative explanation of the AHR peculiarities is given.     

惯性仪表误差补偿技术在提高战略导弹精度中的应用

本文对有关战略导弹惯性仪表主要误差源的分类及对精度的影响；惯性仪表误差补偿的各种方法及其优缺点等内容作了介绍，对美国洲际导弹误差补偿方法也作了介绍，最后对惯性仪表误差的几种补偿方案作了分析。     

基于LMS算法的自适应数字预失真技术研究

文章研究了基于查找表LUT方法的功率放大器自适应数字预失真技术。针对传统的基于线性收敛算法的自适应收敛速度较慢的不足,文章根据自适应滤波理论中的LMS算法,推导并仿真验证了适用于功率放大器自适应数字预失真技术的LMS算法,并从功率放大器的传输特性、输出频谱等方面将此算法与线性收敛的Rascal算法进行比较,仿真结果表明了LMS算法收敛速度更快、预失真效果更好。     

A Study of the Destruction of Spacecraft Surfaces at Contact Interactions with Microparticles of the Space Environment

The results of studying the high-velocity impact interactions of a particle flux of space’s meteoric background with satellites have been presented. The effects that arises during the microparticle motion in the material have been described; the models of solid particle interactions with spacecraft’s onboard hardware protection have been presented. The experimental and analytical dependences have been given. The basic factors have been revealed, and their effect on the erosion wear of satellite’s surface has been estimated. The dependences for calculating the rectilinear (horizontal, inclined and vertical) sections of satellite’s surface have been given. The presented dependences represent the results of experimental and analytical studies.     

高性能馈源喇叭综述

对高性能馈源喇叭进行了一些综述性研究。对国内外高性能馈源喇叭的发展现状进行了一些阐述,这对于在不同的馈源指标要求,选用合适的馈源形式具有重要的指导和借鉴意义。此外,对于高性能馈源喇叭的发展趋势也提出了个人建议,并对设计高性能喇叭馈源的一些实现途径及措施进行了阐述。     

高原发射地空导弹二级发动机点火参数计算

建立了高原条件下地空导弹二级发动机点火参数的计算模型。对地空导弹Ａ型及其改进后的Ｂ型两种导弹进行了，并通过了部队高原条件下的实弹打靶试验。试验的圆满成功雇地研究其它地空导弹高原条件下二级发动机点火性能具有参考价值。     

The Solution of Some Problems of Optimizing the Processes of a Flexible Correction of Motion of Satellite Systems: II.

In a previous paper [1], as a result of group-theoretic decomposition, one of the problems of the optimization of the flexible correction process was reduced to a series of subproblems. In this paper, the analytical solutions to these subproblems are obtained by the sweep method. A series of other similar problems with different variants of flexibility is also considered; the decomposition of these problems is performed, and their analytical solutions are presented. It is shown for some numerical examples that flexible corrections require essentially lower fuel consumption than the rigid correction, where all parameters characterizing the absolute motion of a satellite system are corrected to their nominal values.     

Multiple continuous coverage of the earth based on multi-satellite systems with linear structure

A new and wider definition is given to multi-satellite systems with linear structure (SLS), and efficiency of their application to multiple continuous coverage of the Earth is substantiated. Owing to this widening, SLS have incorporated already well-recognized “polar systems” by L. Rider and W.S. Adams, “kinematically regular systems” by G.V. Mozhaev, and “delta-systems” by J.G. Walker, as well as “near-polar systems” by Yu.P. Ulybyshev, and some other satellite constellations unknown before. A universal method of SLS optimization is presented, valid for any values of coverage multiplicity and the number of satellites in a system. The method uses the criterion of minimum radius of a circle seen from a satellite on the surface of the globe. Among the best SLS found in this way there are both systems representing the well-known classes mentioned above and new orbit constellations of satellites.     

液氧/煤油发动机摇摆测控系统技术要求及实现

分析了伺服机构对发动机摇摆系统的技术要求,在总结以往摇摆系统研制经验的基础上,提出了一套可行的系统实现方法。对部分关键技术和子系统进行了较深入论述,给出了系统构成方案技术实现方法。     

Novel reaction control techniques for redundant space manipulators: Theory and simulated microgravity tests

This paper presents two novel redundancy resolution schemes aimed at locally minimizing the reaction torque transferred to the spacecraft during manipulator manoeuvres. The subject is of particular interest in space robotics because reduced reactions result in reduced energy consumption and longer operating life of the attitude control system. The first presented solution is based on a weighted Jacobian pseudoinverse and is derived by using Lagrangian multipliers. The weight matrix is defined by means of the inertia matrix which appears in the spacecraft reaction torque dynamics. The second one is based on a least squares formulation of the minimization problem. In this formulation the linearity of the forward kinematics and of the reaction torque dynamics equations with respect to the joint accelerations is used. A closed-form solution is derived for both the presented methods, and their equivalence is proven analytically. Moreover, the proposed solutions, which are suitable for real-time implementation, are extended in order to take into account the physical limits of the manipulator joints directly inside the solution algorithms. A software simulator has been developed in order to simulate the performance of the presented solutions for the selected test cases. The proposed solutions have then been experimentally tested using a 3D free-flying robot previously tested in an ESA parabolic flight campaign. In the test campaign the 3D robot has been converted in a 2D robot thanks to its modularity in order to perform planar tests, in which the microgravity environment can be simulated without time constraints. Air-bearings are used to sustain the links weight, and a dynamometer is used to measure the reaction torque. The experimental validation of the presented inverse kinematics solutions, with an insight on the effect of joint flexibility on their performance, has been carried out, and the experimental results confirmed the good performance of the proposed methods. In particular, two test cases have been analyzed in order to validate and evaluate the performance of both the unconstrained solution and the solution which takes into account the robot physical limits.     

A model for the evolution of the on-orbit man-made debris environment

A model for the evolution of the low Earth orbit man-made debris population is presented and the results of several test cases discussed. Debris sources include normal operations in space, explosions occurring on spacecraft in orbit, and collisions between objects in orbit; the stochastic occurrence of these deposition events is modeled using Monte Carlo techniques. A technique for discriminating between objects populating long-life vs rapid-decay orbits is discussed and applied to the analysis of debris contributions from collisions of comparable sized objects. In varying degrees, each of the cases presented indicate there is cause for concern for spacecraft and space operations from the 1990s onward-man-made debris will play a role which may vary from presenting a considerable hazard to certain operations or certain spacecraft to effectively prohibiting the use of certain spaceccraft or space operations.     

Ballistics of a fragmenting meteor body with allowance made for ablation in the non-isothermal atmosphere. II

The second part of the work is devoted to studying the motion of fragmenting meteor bodies with ablation by fragments in a planet’s atmosphere, taking into account its non-isothermal character in altitude. The mechanical fragmentation of a meteoroid under the action of aerodynamic drag is considered in the context of statistical strength theory. An analytical solution for ballistics of a fragmenting body is obtained at a constant parameter of ablation. A theoretical analysis of the derived regularities is made and an example of their usage in the problem of a comet-asteroid hazard is presented.     

The visual stress model--a psycho-physiological method for the evaluation of operational reliability of pilots and cosmonauts.

An experimental psycho-physiological method is presented for the evaluation of visual-cognitive performance preconditions and operational reliability of pilots and cosmonauts. As visual-cognitive stress are used tachistoscopically presented instrument symbols under conditions of individual speed of work and time pressure. The results of the compared extreme groups consisting of pilots with good and insufficient flight performance showed that the pilots with impairments to the quality of flight activity differ already before the test in their individual habitual characteristics and actual motivation, during the stress in their operational parameters, in the dimensions of their cardiorespiratory activation as well as in their efficiency and after the stress in their subjective experience of the stress. Conclusions are drawn for the evaluation of the aptitude of pilots and cosmonauts.     

固体火箭发动机压强曲线上升段预示的一种实用方法

介绍了一种预示固体发动机火箭压强曲线上升段的实用方法。用该方法编制的程序具有结构简单,精度高的优点,能够满足工程需要。