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Launch vehicle The Proton-M heavy-class launch vehicle (LV) is an upgraded version of the Proton-K. The LV is able to deliver payloads directly into designated geostationary orbit points, thus making possible the insertion of satellites which are not equipped with an apogee propulsion unit. It can liftoff from launch pads currently operational at the Baikonur Cosmodrome. The Proton-M is designed as a tandem LV with transverse separation of stages. It is composed of three stages and spacehead with Breeze-M upper stage as forth stage. All stages of the LV and upper stage are fueled by hypergolic propellant components: unsymmetrical dimethyl hydrazine as fuel, and nitrogen tetroxide as oxidizer. The Proton-M has a larger payload fairing as compared with Proton-K in order to double the space available for payloads. Upgrading (replacement) of the control system enables to improve power performance as well as operational and environment characteristics of the LV. The Breeze-M upper stage enables to deliver 3-3.2 ton payloads into geostationary orbit. -
Launch vehicle The Soyuz-FG middle-class launch vehicle (LV) is intended for injection of automatic spacecraft for national economy, scientific research and spacecraft for special purposes as well as manned and cargo spaceships according to the program of the International Space Station. The three-stage Soyuz-FG LV designed on the base of the Soyuz-U LV. It can liftoff from launch pads currently operational at the Plesetsk and Baikonur Cosmodromes. The Soyuz-FG LV is designed as a system with parallel separation of the lateral rocket engine assemblies upon the first stage burnout, and transverse separation of the second stage engine assembly after burnout. Each LV assembly has its own propulsion unit using non-toxic propellants (oxygen and kerosene). In contrast to Soyuz-U launch vehicle modernized engines with heightened specific thrust on units of the 1-st and the 2-nd stages, developed for Soyuz-2 LV, are used for Soyuz-FG LV for increasing load-carrying capacity. Soyuz-FG LV can be equipped with nose fairing of the following diameters: 2.7 m; 3.0 m; 3.3 m; 3.715 m. Fregat kick stage is designed for payload transfer from open intermediate orbit of a launch vehicle to scheduled orbit of spacecraft injection.
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Launch vehicle The Dnepr lightweight launch vehicle (LV) is based on the RS-20 (NATO designation: SS-18, Satan) silo-launched ICBM. The LV offers high performance, accuracy of orbital injection and flight reliability. It can liftoff from launch pads currently operational at the Baikonur Cosmodrome. The LV is fueled by hypergolic propellant components: unsymmetrical dimethyl hydrazine as fuel, and nitrogen tetroxide as oxidizer. The LV includes the first, second and the adapter of the first and second stages, and the nose cone complete with adapter. All components of the configuration, except for the nose cone adapter, have been borrowed unchanged from the original RS-20 ICBM. Payload is mounted in the body of the upper stage on a newly designed spacer pad. The LV launches in a mortar mode from its standart launch canister, with the power unit of the first stage ignited upon release of the LV from the canister. The LV is ability to maintain launch readiness for an unlimited period of time that may be restricted solely by the requirements of the integrated payload.
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Small spacecraft for remote sensing of the land and sea surface The Condor-E small spacecraft (SSC) with a synthetic aperture radar (SAR) is designed to obtain, store and transmit high-resolution microwave remote-sensing (RS) data to ground receiving and processing stations. The SAR provides around-the-clock all-weather acquisition of the Earth's surface.
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21B2 remote-sensing data receiving and processing station based on mobile receiving post The Skorpion remote-sensing (RS) data receiving and processing station can be based on mobile or stationary receiving post. The Skorpion-4S remote-sensing data receiving and processing station is designed to receive and process information from a Resurs-P type remote-sensing spacecraft (S/C) and provide two-way service communications with a Russian remote-sensing data processing and S/C control center (hereinafter Center).
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Radiotelescope (RT 64) The multipurpose microwave band radiotelescope, 64 meters in diameter, is intended for:- fundamental astrophysical researches;
- reception of information signals from spacecraft from deep space;
- control of spacecraft in deep space.
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Mobile antenna system The MAS-3 mobile antenna system is designed to receive radiotelemetry information and operate with receiving-recording stations based on air- and spacecraft. -
Aerial target drone system The Dan aerial target drone system is designed to imitate remote-controlled aircraft, cruise missiles and subsonic tactical aircraft during combat training and testing of air defense missile, small-arms and artillery systems as well as fighter aircraft weapon systems. -
Mobile optoelectronic station The Veresk mobile optoelectronic station is designed to measure trajectories of target aircraft helicopters, missiles and projectiles, to process the results of these measurements and send them together with video images to users in real time, as well as to automatically track the air objects whose trajectories are being measured. The Veresk mobile optoelectronic station is one of the measuring tools used at firing ranges. Its main uses include testing of new weapons and evaluation of the results of live firing exercises held by the Armed Forces.
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Parachute systems The cargo parachute systems MKS-350-9, MKS-350-12 are intended for air drop of armaments, military vehicles and cargo. The parachute systems, designed and developed on the basis of main parachute with area of 350 m2, allow to drop heavy cargos with mass up to 14,400 kg from different type of aircraft. Several types of parachute systems have been developed and have been in service by the present time. -
Parachute systems The cargo parachute systems MKS-350-9, MKS-350-12 are intended for air drop of armaments, military vehicles and cargo. The parachute systems, designed and developed on the basis of main parachute with area of 350 m2, allow to drop heavy cargos with mass up to 14,400 kg from different type of aircraft. Several types of parachute systems have been developed and have been in service by the present time.
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Brake landing parachute systems The brake landing parachute systems:
- reduce the length of aircraft landing run in 1.5 - 2 times;
- are reliably deployed;
- are simple in operation;
- have longterm total service life.
- installation and deployment of parachute system at any variant of its mounting on the aircraft;
- parachute system stable operation in aircraft wake;
- reduced period of time of parachute system preparation for application;
- increase of total service life of the parachute system.
