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Efanov V.V.,Federal Enterprise Lavochkin Association | Gorovtsov V.V.,Saint Petersburg State University | Kotomin A.A.,Saint Petersburg State University | Dushenok S.A.,Federal State Unitary Enterprise
Solar System Research | Year: 2015

The use of pyro separation devices based on high-energy elastic substances for the ExoMars mission is proposed and substantiated. A description is given of their design and of the method for design calculations. The underlying design and engineering solutions were successfully flight qualified on the “Electro-L” and “Spectr-R–Radioastron” spacecraft, as well on the multifunction Versatile Space Tug “Fregat-SB”. © 2015, Pleiades Publishing, Inc.


Vago J.L.,European Space Agency | Lorenzoni L.,European Space Agency | Calantropio F.,Thales Alenia | Zashchirinskiy A.M.,Federal Enterprise Lavochkin Association
Solar System Research | Year: 2015

The European Space Agency (ESA) and Roscosmos ExoMars 2018 joint mission is planned to deliver a rover and a surface platform to the surface of Mars. The rover’s payloads are designed to search for signs of life; those of the surface platform are to conduct environmental and geophysical measurements. A necessary condition for meeting these objectives is to land safely at a scientifically appropriate location. This article describes the procedure followed by the two agencies to select a suitable landing site for the mission. © 2015, Pleiades Publishing, Inc.


Grant
Agency: Cordis | Branch: FP7 | Program: CP-FP-SICA | Phase: SPA.2010.3.2-04 | Award Amount: 736.01K | Year: 2011

Objects re-entering the atmosphere of the Earth from space require systems to decelerate the object during its descent phase as well as protection against temperatures of several hundreds of degrees of centigrade caused by the atmospheric friction. We propose to study the feasibility of using with the Earth re-entry a system developed for entering the Martian atmosphere. The focus of this work will be in analyzing and measuring the dynamical stability in transonic phase of a brand new re-entry and descent system for low mass payloads. We are to investigate an entry, descent and landing system developed for Mars. This system is based on brand new technology involving inflatable structures saving a considerable amount of mass compared to traditional rigid structures. The project behind is MetNet Precursor, which is a planetary exploration mission to Mars, aimed to deploy on its surface a meteorological station based on a new type of semi-hard landing vehicle called MetNet Lander (MNL). This work will investigate the feasibility to use the MetNet entry and descent system at Earth allowing for scaling modifications for the key systems assuming deorbitation from a LEO orbit. Specifically, this work will analyze by simulations and by wind tunnel testing the stability of the entry and descent system during the supersonic and transonic phases of the descent in the atmosphere of the Earth. This work will foster collaboration between Russian and European organizations, and will provide brand-new knowledge on the re-entry systems. This project will effectively reduce duplication of research efforts and will open new avenues for joint space technology research and development.


Sabirov T.R.,Federal Enterprise Lavochkin Association
CriMiCo 2013 - 2013 23rd International Crimean Conference Microwave and Telecommunication Technology, Conference Proceedings | Year: 2013

This paper considers the results of development of broadband space-based AESA. In particular, it concerns the results of calculation of one element of AESA in computer-aided design system using numerical methods of electrodynamics by parametric synthesis and provides radiation characteristics, frequency characteristics and the distribution of the normal component of the electric field. © 2013 CriMiCo'2013 Organising Committee, CrSTC.


Kazakevich Y.V.,Federal Enterprise Lavochkin Association | Zefirov I.V.,Federal Enterprise Lavochkin Association
Solar System Research | Year: 2015

This article reviews the history of the Lavochkin Association Mission Operation Center (Laspace MOC), the reasons for its building, purposes and objectives to support Fregat multipurpose rocket booster (FMRB) launch tracking, as well as the basic principles of information exchange. Hardware and software are described in detail. © 2015, Pleiades Publishing, Inc.


Telepnev P.P.,Federal Enterprise Lavochkin Association | Efanov V.V.,Federal Enterprise Lavochkin Association | Kuznetsov D.A.,Federal Enterprise Lavochkin Association | Ermakov V.Y.,Federal Enterprise Lavochkin Association
Solar System Research | Year: 2015

The paper considers some operational modes of a high gain antenna drive in order to determine the minimum perturbing influences that impact precision equipment of the SPEKTR-R spacecraft. © 2015, Pleiades Publishing, Inc.


Asyushkin V.A.,Federal Enterprise Lavochkin Association | Vikulenkov V.P.,Federal Enterprise Lavochkin Association | Ishin S.V.,Federal Enterprise Lavochkin Association
Solar System Research | Year: 2015

The article gives a brief justification of approaches, applied during development of Versatile Space Tugs of the Fregat type, summarizing a more than ten-year history of their operations. © 2015, Pleiades Publishing, Inc.


Khartov V.V.,Federal Enterprise Lavochkin Association | Romanov V.M.,Federal Enterprise Lavochkin Association | Pichkhadze K.M.,Federal Enterprise Lavochkin Association
Solar System Research | Year: 2015

This paper is dedicated to the life and creative career of Georgii N. Babakin, the outstanding designer of native robotic space complexes for fundamental scientific studies of the Moon, Venus, and Mars, and Chief Designer of the S.A. Lavochkin machine building enterprise. © 2015, Pleiades Publishing, Inc.


Finchenko V.S.,Federal Enterprise Lavochkin Association | Ustinov S.N.,Federal Enterprise Lavochkin Association | Ivankov A.A.,Federal Enterprise Lavochkin Association
Solar System Research | Year: 2015

The article briefly describes a design of the Versatile Space Tug (VST) Fregat, analyses the processes occurring during its descent in the Earth’s atmosphere after performing its primary function, a thermal destruction scenario of the VST Fregat is developed, a procedure and results of the calculation of heat loads, impacting the VST, and the remaining mass of its structural components reaching the Earth’s surface, are presented. © 2015, Pleiades Publishing, Inc.


Finchenko V.S.,Federal Enterprise Lavochkin Association | Ivankov A.A.,Federal Enterprise Lavochkin Association | Shmatov S.I.,Federal Enterprise Lavochkin Association | Mordvinkin A.S.,Federal Enterprise Lavochkin Association
Solar System Research | Year: 2015

The article presents the initial data for the ExoMars landing module aerothermodynamic calculations, used calculation methods, the calculation results of aerodynamic characteristics of the landing module shape and structural parameters of thermal protection selected during the conceptual design phase. Also, the test results of the destruction of the thermal protection material and comparison of the basic characteristics of the landing module with a front shield in the form of a cone and a spherical segment are presented. © 2015, Pleiades Publishing, Inc.

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