Khrunichev State Research and Production Space Center

Moscow, Russia

Khrunichev State Research and Production Space Center

Moscow, Russia

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Ignatov A.I.,Khrunichev State Research and Production Space Center | Sazonov V.V.,RAS Keldysh Institute of Applied Mathematics
Cosmic Research | Year: 2013

The mode of monoaxial solar orientation of a designed artificial Earth satellite (AES), intended for microgravitational investigations, is studied. In this mode the normal line to the plane of satellite's solar batteries is permanently directed at the Sun, the absolute angular velocity of a satellite is virtually equal to zero. The mode is implemented by means of an electromechanical system of powered flywheels or gyrodynes. The calculation of the level of microaccelerations arising on board in such a mode, was carried out by mathematical modeling of satellite motion with respect to the center of masses under an effect of gravitational and restoring aerodynamic moments, as well as of the moment produced by the gyrosystem. Two versions of a law for controlling the characteristic angular momentum of a gyrosystem are considered. The first version provides only attenuation of satellite's perturbed motion in the vicinity of the position of rest with the required velocity. The second version restricts, in addition, the increase in the accumulated angular momentum of a gyrosystem by controlling the angle of rotation of the satellite around the normal to the light-sensitive side of the solar batteries. Both control law versions are shown to maintain the monoaxial orientation mode to a required accuracy and provide a very low level of quasistatic microaccelerations on board the satellite. © 2013 Pleiades Publishing, Ltd.


Shumov A.E.,Khrunichev State Research and Production Space Center | Novikov L.S.,Moscow State University | Shaevich S.K.,Khrunichev State Research and Production Space Center | Aleksandrov N.G.,Khrunichev State Research and Production Space Center | And 14 more authors.
Advances in Space Research | Year: 2015

The Komplast materials experiment was designed by Khrunichev State Research and Production Space Center together with Skobeltsyn Institute of Nuclear Physics, Lomonosov Moscow State University and other Russian scientific institutes, and has been carried out by Mission Control Moscow since 1998. The purpose of this experiment is to study the complex effect of the low Earth orbit environment on samples of various spacecraft materials. On November 20, 1998 the Komplast experiment began with the launch of the first International Space Station module Zarya, or Functional Cargo Block (FGB). Eight Komplast panels with samples of materials and sensors were installed on the outer surface of FGB module. Two of eight experiment panels were retrieved during Russian extravehicular activity in February 2011 after 12 years of space exposure and were subsequently returned to Earth by Space Shuttle ''Discovery" on the STS-133/ULF-5 mission in March 2011. The article presents the results obtained from this unique long-duration experiment on board of the International Space Station. © 2015 COSPAR. Published by Elsevier Ltd. All rights reserved.


Shumov A.E.,Khrunichev State Research and Production Space Center | Shaevich S.K.,Khrunichev State Research and Production Space Center | Aleksandrov N.G.,Khrunichev State Research and Production Space Center | Novikov L.S.,Moscow State University | And 7 more authors.
European Space Agency, (Special Publication) ESA SP | Year: 2013

The impact of micro meteors and space debris on the spacecrafts is the most important factor which leads to their damage and destruction. For this reason, the study of the processes of high-speed impact of solid body is a topical task. These studies help specialists to developing protection methods of spacecraft. Experiment "Komplast" provides valuable information in studying the interaction of solid particles with the materials of the spacecraft and helps to explore the composition of meteor particles and space debris. This paper presents the Komplast experiment preliminary results of micro meteors and space debris analysis. Copyright © 2013 European Space Agency.


Shaevich S.K.,Khrunichev State Research and Production Space Center | Aleksandrov N.G.,Khrunichev State Research and Production Space Center | Shumov A.E.,Khrunichev State Research and Production Space Center | Novikov L.S.,Moscow State University | And 4 more authors.
International SAMPE Technical Conference | Year: 2014

The Komplast materials experiment was designed by the Khrunichev Space Center, together with other Russian scientific institutes, and has been carried out by Mission Control Moscow since 1998. The purpose is to study the effect of the low earth orbit (LEO) environment on exposed samples of various spacecraft materials. The Komplast experiment began with the launch of the first International Space Station (ISS) module on November 20, 1998. Two of eight experiment panels were retrieved during Russian extravehicular activity in February 2011 after 12 years of LEO exposure, and were subsequently returned to Earth by Space Shuttle "Discovery" on the STS-133/ULF-5 mission. The retrieved panels contained an experiment to detect micrometeoroid and orbital debris (MMOD) impacts, a temperature sensor, several pieces of electrical cable, both carbon composite and adhesive-bonded samples, fluoroplastic samples, and many samples made from elastomeric materials. Our investigation is complete and a summary of the results obtained from this uniquely long-duration exposure experiment will be presented. Copyright 2014. Used by the Society of the Advancement of Material and Process Engineering with permission.


Kamath U.,Boeing Company | Grant G.,Boeing Company | Kuznetsov S.,Khrunichev State Research and Production Space Center | Shaevich S.,Khrunichev State Research and Production Space Center | Spencer V.,NASA
51st AIAA/SAE/ASEE Joint Propulsion Conference | Year: 2015

The International Space Station (ISS) is a result of international collaboration in building a sophisticated laboratory of an unprecedented scale in Low Earth Orbit. After a complex assembly sequence spanning over a decade, some of the early modules launched at the beginning of the program would reach the end of their certified lives, while the newer modules were just being commissioned into operation. To maximize the return on global investments in this one-of-a-kind orbiting platform that was initially conceived for a service life until 2016, it is essential for the cutting edge research on ISS to continue as long as the station can be sustained safely in orbit. ISS Program is assessing individual modules in detail to extend the service life of the ISS to 2024, and possibly to 2028. Without life extension, Functional Cargo Block (known by its Russian acronym as FGB) and the Service Module (SM), two of the early modules on the Russian Segment, would reach the end of their certified lives in 2013 and 2015 respectively. Both FGB and SM are critical for the propulsive function of the ISS. This paper describes the approach used for the service life extension of the FGB propulsion system. Also presented is an overview of the system description along with the process adopted for developing the life test plans based on considerations of system failure modes, fault tolerance and safety provisions. Tests and analyses performed, important findings and life estimates are summarized. Based on the life extension data, FGB propulsion system, in general, is considered ready for a service life until 2028. © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.


Kudinov A.,Khrunichev State Research and Production Space Center | Yurchenko I.,Khrunichev State Research and Production Space Center | Karakotin I.,Khrunichev State Research and Production Space Center | Vaganov A.,Hypersonic Air Dynamic Dep. | And 2 more authors.
50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition | Year: 2012

Based on experimental data in supersonic wind tunnels the flow patterns, which cause peak pressure and peak heat fluxes at hypersonic speed were obtained. Physical interpretations for each flow pattern are presented. Peak areas dimensions were specified. Influence of aerospike fluxes was investigated. Copyright © 2012 by Khrunichev State Research and Production Space Center. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.


Petukhov V.P.,Moscow State University | Kulikauskas V.S.,Moscow State University | Novikov L.S.,Moscow State University | Petrov D.V.,Moscow State University | And 4 more authors.
Journal of Surface Investigation | Year: 2014

Using methods of X-ray fluorescence analysis (XRFA), the Rutherford backscattering of ions (RBS) and spectral X-ray microanalysis (SXRM) in combination with scanning electron microscopy (SEM), we study the elemental composition and structure of contaminants on the surface of a metallic panel with samples of different materials exposed to outer space for 12 years. It turns out that the main elements of the contaminants are C, O, Si, S, Ca, Fe, and Zn. Since these elements are the constituents of materials located on the panel, they are present as a result of destruction of the materials under the action of outer-space factors. X-ray phase analysis (XRPA) of the contaminants shows that carbon is present in the form of an amorphous graphite phase with a small addition of crystalline graphite, while the other components are in an amorphous state. Crystalline silicium dioxide and other silicium compounds are not found. © Pleiades Publishing, Ltd., 2014.


Kuzin A.I.,Khrunichev State Research and Production Space Center | Nesterov V.E.,Khrunichev State Research and Production Space Center | Lozin S.N.,Khrunichev State Research and Production Space Center | Lechov P.A.,Khrunichev State Research and Production Space Center | Semenov A.I.,Khrunichev State Research and Production Space Center
Proceedings of the International Astronautical Congress, IAC | Year: 2012

The report presents basic requirements to the layout, configuration and main specifications of the future-oriented space transportation launch system featuring fly-back 1st stage boosters returned to the launch point. The report provides basic results of engineering work for the early stage of the system development. It also shows the role of the fly-back booster propulsion system to achieve required performance factors of the system. The report covers basic principles on how to develop and use a propulsion system featuring re-usable liquid- propellant rocket engines (multi-engine configuration of a propulsion system, presence of the on-board malfunction monitoring and shutdown system, utilization of new efficient liquid propellants, possibility to accomplish the task in case of a one-engine failure, maintainability and serviceability in-between flights with minimal resources etc.). The report provides experimental data obtained during fire tests of a liquid-propellant rocket engine (a prototype of the fly-back booster engine using the compressed natural gas/liquid oxygen propellant components. It formulates the direction of subsequent efforts to develop a re-usable transportation system. Copyright © (2012) by the International Astronautical Federation.


Bahvalov Y.O.,Khrunichev State Research and Production Space Center | Pugachenko S.E.,Khrunichev State Research and Production Space Center | Shaevich S.K.,Khrunichev State Research and Production Space Center
62nd International Astronautical Congress 2011, IAC 2011 | Year: 2011

General description of Low Earth Orbit infrastructure and Lunar Settlement with their main characteristics is given. Comparative assessment of cargo flow for Low Earth orbital infrastructure and Lunar Settlement operation is considered. We've analyzed orbital infrastructure and lunar settlement hardware parameters from reliability point of view to minimize expenses for transport service. Orbital infrastructure model analysis results are correlated with statistic data about "Mir" station cargo supply and allow to determine transport vehicle payload mass and lunar transport system flight frequency.


Davydov A.A.,Khrunichev State Research and Production Space Center
Cosmic Research | Year: 2011

A communication satellite (small spacecraft) injected into a geosynchronous orbit is considered. Flywheel engines are used to control the rotational spacecraft motion. The spacecraft after the emergency situation has passed into a state of uncontrolled rotation. In this case, no direct telemetric information about parameters of its rotational motion was accessible. As a result, the problem arose to determine the rotational satellite motion according to the available indirect information: current taken from the solar panels. Telemetric measurements of solar panel current obtained on the time interval of a few hours were simultaneously processed by the least squares method integrating the equations of rotational satellite motion. We present the results of processing 10 intervals of the measurement data allowing one to determine the real rotational spacecraft motion and to estimate the total angular momentum of flywheel engines. © 2011 Pleiades Publishing, Ltd.

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