The problems of assessing a risk of damaging a spacecraft by meteoroids and space debris are fairly important. The probability of not damaging a SC depends on the properties of its structural elements, particle flux density and velocity of hypervelocity meteoroids and/or space debris. This article offers an analytical review of papers (primarily foreign ones) assessing velocity of meteoroids based on the experimental evidence. Stated are general requirements for experimental data acceptable for acquiring reliable meteoroid velocity data. Compared are meteoroid velocity values obtained from different models, including the data presented in the current national domestic standards. Based on the analysis of experimental data accumulated so far, the most probable values of meteoroid and space debris velocities to be used in ballistic limit equations have been proposed. Key words: meteoroid, space debris, spacecraft shielding against meteoroids, meteoroid environment, meteoroid flux density and velocity.

Anthropogenic space debris pose a serious threat to operation of spacecraft (SC), including a real threat of damage and destruction of Soviet spacecraft carrying Nuclear Power Systems (NPS) onboard, which ceased their active functioning in orbit thirty years ago. Collisions of space debris with elements of SC structure may both have catastrophic consequences and cause local damage (for example, penetration of thermal control elements), resulting in the loss of spacecraft ability to function, or loss of some of their functionality. In the case of SC carrying NPS, an impact on the structure may result in debris with residual radioactivity, which calls for a continued focus on the status of this type of spacecraft in disposal orbits. In order to predict generation of space debris in near-Earth space, to evaluate SC survivability, as well as to develop engineering facilities for protection, the software package REACTOR was developed, which makes it possible to use a desktop computer to solve the problems of impact effects on complex technical objects including the function of computing the number of generated fragments (debris) and their velocity spectra. As a subject for research, a schematic SC model and a space NPS REACTOR model were constructed, calculations have been performed. As a result of calculations, qualitative and quantitative characteristics of the resulting fragments were obtained. Key words: space debris, spacecraft, collision, software package, computer, fragments, models, calculation nuclear power system.

The paper provides an overview of the main activities of JSC NPO Lavochkin from the 30s of the last century till present, and also a description of promising projects. Diversified programs for development and production of space complexes for scientific investigations of deep and adjacent space objects are presented. For the 75th anniversary of the foundation of RSC Energia, touchpoints between the veteran space enterprises are discussed. Consideration is given to the issue of transferring the lunar and planetary subject of OKB-1 to the team of S.A. Lavochkin machine-building plant and assigning Georgy Nikolaevich Babakin to a position of the chief designer. The tasks being solved by spacecraft and the ways of their implementation are briefly analyzed. The near-term prospects of national and international space programs are outlined. Keywords: Lavochkin, Babakin, Luna, Venera, Mars series spacecraft, astrophysical observatories, hydrometeorological spacecraft, Fregat upper stage.

The article briefly discusses the key achievements of the enterprise over 75 years from the formation of OKB-1 headed by S.P. Korolev for producing intercontinental range missiles to the current status of RSC Energia being the country’s and world leader in manned space flight. The developed intercontinental missiles R-7 and a closed-loop oxygen-hydrocarbon liquid-propellant rocket engine provided the basis for developing integrated launch vehicles which were used to launch the world's first Earth satellite, the first cosmonaut on the Earth, automatic interplanetary stations to the Moon, Venus, Mars. The diversification of the enterprise impeded S.P. Korolev to concentrate on manned space flights, and he initiated the transfer of development and manufacture of combat missiles to Makeyev DB, integrated launch vehicles to TsSKB Progress, communication and other satellites to M.F. Reshetnev ISS, lunar and interplanetary stations to S.A.Lavochkin NPO. In the 1980s under the guidance of V.P. Glushko the Energia super-heavy launch vehicle and Energia-Buran system in unmanned configuration were developed and successfully launched on the first try. The Salyut manned single-module orbital stations, Mir multifunctional multi-module space laboratory and successfully operating upgraded manned transportation (Soyuz) and logistics (Progress) spacecraft were developed. In the hard times of 1990s, RSC Energia under the guidance of Yu.P. Semenov saved the national cosmonautics through commercial research performed on the Mir station. At present, by launching three additional modules RSC Energia is completing assembly and integration of the Russian Segment into the International Space Station. Keywords. ОKB-1, S.P.Korolev RSC Energia, V.P. Glushko, Yu.S. Semenov, integrated launch vehicle, orbital station, crew transportation spacecraft, logistics transportation spacecraft, International Space Station.

It is proposed to develop a small spacecraft for an experiment using high-temperature superconductors (HTS) and shape memory materials. The purpose of the experiment is to test a technological capability of creating a strong magnetic field on the small spacecraft using HTS and shape memory materials for deployed large-area structures, and study the magnetic field interaction with the solar wind plasma and the resulting force impact on the small spacecraft. This article is of a polemical character and makes it possible to take a fresh look at the applicability of new technologies in space-system engineering. Key words: high-temperature superconductors, shape memory materials, solar wind, spacecraft.

It is proposed to develop a small spacecraft for an experiment using high-temperature superconductors (HTS) and shape memory materials. The purpose of the experiment is to test a technological capability of creating a strong magnetic field on the small spacecraft using HTS and shape memory materials for deployed large-area structures, and study the magnetic field interaction with the solar wind plasma and the resulting force impact on the small spacecraft. This article is of a polemical character and makes it possible to take a fresh look at the applicability of new technologies in space-system engineering.

In view of the considerable number of elements in space and ground segments of a heterogeneous space ERS system, a mechanism is required for developing its concepts with obtaining refined baseline data for determining measures to optimize the ERS ground segment configuration geography-wise and outfit receiving systems for receiving mission payload data from high-performance ERS satellites. The development trends for equipment and technologies for mission payload data are given, in particular the status of the high backbone network in order to determine possible locations for of a space ERS system. Indicators are introduced which the capabilities of a wide-area network of remote sensing ground transmitting ERS data rate optical segment elements systemically characterize data receiving stations. Based on the obtained data, system-level patterns were determined in the development of the ground segment for receiving the ERS mission payload data depending on the state of the ERS satellite constellation, driving further development of strategy for the ERS ground infrastructure.

The paper presents results of conceptual design studies to determine configuration of an electrically propelled upper (a space tug) with main engines arrays. It addresses the problem stage (EPUS) — a space transportation stage based on electric propulsion powered by solar of deploying a multi-plane orbital constellation of to in of small spacecraft (SSC) using an electrically propelled upper stage. It proposes change the SSC operational orbital planes based on the effect of precession rates between the parking and the working orbits eccentricity in the Earth gravitational field. Requirements owing have the difference to the effect been defined for the EPUS electrical propulsion system that take into account the need to operate it to offset the aerodynamic drag while waiting in the parking orbit for the SSC operational orbital plane to turn. It demonstrates the feasibility of employing four EPUS that use Stationary Plasma Thruster-type electric propulsion as their main engines and gallium arsenide solar arrays for deployment in a 600 km orbit in four planes an orbital constellation of 24 small spacecraft with a mass of ~250 kg each using one launch of a medium capacity launch vehicle of Soyuz-2.1b type.

The paper discusses small oscillations of a panel in an incompressible medium. Air can be considered an incompressible medium during modal tests of solar array panels for spacecraft deployed on the ground in a lab environment. A panel is represented as a two-sided boundary surface. Conditions are determined for applicability of the potential motion of the medium. Calculation of the attached mass is reduced to the solution of the Neumann boundary value problem. To solve the boundary value problem, the method of boundary elements is used in the piecewise constant approximation variant, which provides a solution of the hypersingular boundary integral equation. Numerical solutions are obtained for the three fundamental modes of rectangular panels. The obtained numerical values are refined using non-linear Shanks transformation. Dependence of attached mass on panel elongation and the amount of the gap between its fragments is studied. For any in-plane oscillation mode of a panel fragment, the attached mass is determined using the principle of linear superposition. An estimate is given of the effect of the distance from the panel to the wall on the attached mass value. Key words: oscillations, incompressible medium, air, attached mass, rectangular panels, boundary elements method.

At the initiative of S.P.Korolev, in 1959, Special Design Bureau No.1 (now RSC Energia) established the High-temperature Power Engineering and Electric Propulsion Center which was tasked with development of nuclear electric propulsion for heavy interplanetary vehicles. Selected as the source of electric power was a nuclear power unit based on a thermionic converter reactor, and selected as the engine was a stationary low-voltage magnetoplasmodynamic (MPD) high-power (0.5–1.0 MW) thruster which had thousands of hours of service life. The paper presents the results of extensive efforts in research, development, design, materials science experiments, and tests on the MPD-thruster, including the results of development and 500-hours life tests of an MPD-thruster with a 500-600 kW electric power input that used lithium propellant. The world’s first lithium 17 kW MPD-thruster was built and successfully tested in space. The paper points out that to this day nobody has surpassed the then achievements of RSC Energia neither in thruster output during long steady-state operation, nor in performance and service life. Key words: Martian expeditionary vehicle, nuclear electric rocket propulsion system, electric rocket thruster, magnetoplasmodynamic thruster, lithium, cathode, anode, barium, electric propulsion tests in space.