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Ground-Based Infrastructure

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Launch Services

ILV «Zenit-3SLBF» with US «Fregat-SB»
Works of Landfill Type and Deliveries

Technical Maintenance (the works with the objects of infrastructure)
Services for Space Activity
Deliveries of Space Facilities
Deliveries of Propellant Components
The insurance of space risks

- design and production of SRT
- transportation of SRT
- pre-launching procedure
- launch and injection of SV into orbit
- flight testing and operation of SC into orbit
Third Party insurance
Background

Payloads
The Launch Vehicles
The Upper Stage Booster
Launches

Kanopus-V, BKA, MKA-FKI, ExactView 1, TET-1 spacecrafts launch


Kanopus-V.jpg    
July 22 at 10:00 Moscow time 41 minutes from the launch site Baikonur site 31 companies starting the calculations of rocket-space industry is made of a space rocket launch Soyuz-FG with the upper block Fregat, designed for launching into orbit spacecraft  - Russian Kanopus-V and MCA-FCI (Zond-PP), Belarus BKA, TET-1 (Germany) and ADS-1B (Canada).

In accordance with the flight cyclogram head unit in the  Fregat and the block of five spacecraft separated cleanly from the third stage of the launch vehicle, followed by removal of RB continued to target the spacecraft's orbit.



Kanopus-V2.jpg    
The Kanopus-V 1 spacecraft is part of the Kanopus-Vulkan disaster monitoring constellation being deployed by the All-Russian Research Institute of Electrical Engineering with the Iosifyan Plant (VNIIEM) under a contract to Roscosmos, the Russian space agency. The Kanopus-V project is also supported by the Russian Ministry for Civil Defense, Emergencies and Elimination of Consequences of Natural Disasters (EMERCOM of Russia), Russia’s Ministry of Natural Resources and Environment  (Minprirody of Russia), the Russian Academy of Sciences (RAS), and Russia’s Federal Service for Hydrometeorology and Environment Monitoring (Roshydromet).

Kanopus-V will provide users with climate and weather data for a number of applications:

• disaster monitoring and weather phenomena;
• mapping;
• detecting forest fires and toxic waste dumps;
• detecting environmental anomalies to predict earthquakes;
• agriculture, water and coast monitoring;
• land use;
• high-efficiency observation of target regions.

Kanopus-V Major Specifications

Applications
Remote sensing
Spacecraft Mass
400 kg
Payload Mass 110 kg
Dimensions 0,9 m х 0,75 m
Design Lifetime
5 years
Orbit
Sun-synchronous
Altitude approx. 510 km
Inclination approx. 98°
Period 94,75 min.
Orientation Accuracy
5 ang. min
Stabilization Accuracy 0,001 °/s
Reorientation Time (±40°) 2 min
Average Day Power 300 W
Imaging Instruments
Panchromatic Camera
Swath 23 km
Resolution 2,1 m
Spectral Band 0,52–0,85 μm
Мультиспектральная камера
Swath 20 km
Resolution 10,5 m
Spectral Band 0,54–0,6; 0,63–0,69; 0,69–0,72; 0,75–0,86 μm
Command Radio Link
Memory 24 Gb
Operating Frequencies 8084–8381,5 MHz
Channels 2
Data Rate 61,4 Mbps


MKA-FKI 1



MKA-FKI.jpg    
The MKA-FKI 1 spacecraft is part of the small satellite complex for fundamental space studies (MKA-FKI) being deployed by the Lavochkin Research and Production Association (Lavochkin NPO) under a contract to Roscosmos. The 2006–2015 Russian Federal Space Program that manages the constellation calls for the launch of five MKA-FKIs.

MKA-FKI 1 will use an L-band radiometer to study physical phenomena and processes in the atmosphere and on the surface.

The MKA-FKI 1 investigations will include:

• Temperature and moisture of forests and swamps.
• Biometric information of vegetation.
• Salinity of oceans and rivers.
• Glaciers.
• Ocean-atmosphere and surface-atmosphere interactions.
• Geothermal activity.
• Soil moisture mapping.

MKA-FKI 1 Specifications

Applications
Remote sensing, science
Spacecraft Mass 110 kg
Design Lifetime
3 years
Orbit
Sun-synchronous
Altitude
approx. 817 km
Inclination
approx. 97.4°
Orientation Accuracy
6 ang. min
Stabilization Accuracy
0,0015 °/s
Average Day Power
220 W
Operating Frequencies
Transmitter
2,268.946–2,271.054 MHz
Receiver
2,289.238–2,091.346 MHz
Memory
8 Gb
Data Rate
3 Mbps
Payload  Small two-channel L-band UHF radiometer (Zond-PP)
Mass
13 kg
Swath
800 km
Antenna Petal Width 22°x15°


BKA



bka.jpg    
The Belarus BKA spacecraft is part of the Belarus satellite remote sensing system being developed by VNIIEM under a contract to the Belarus National Academy of Sciences. The contract follows an agreement between the Belarus National Academy of Sciences and the Russian space agency to build and launch a remote sensing satellite for Belarus and deploy a ground control complex in Belarus.

The Belarus space system is to provide:

• high-resolution remote sensing information for Belarus users on a regular and timely basis;
• prompt reception of satellite data by ground stations;
• BKA control during the satellite’s entire lifetime;
• potential for future multi-satellite Earth observation constellations.

Major applications of the Belarus space system are:

• Land use and agriculture.
• Renewable and non-renewable natural resources.
• Emergency monitoring.
• Land survey and mapping.
• Environment monitoring.

BKA Major Specifications

Applications
Remote sensing
Spacecraft Mass
400 kg
Payload Mass 110 kg
Dimensions 0,9 m х 0,75 m
Design Lifetime
5 years
Orbit
Sun-synchronous
Altitude approx. 510 km
Inclination approx. 98°
Period 94,75 min.
Orientation Accuracy
5 ang. min
Stabilization Accuracy 0,001 °/s
Reorientation Time (±40°) 2 min
Average Day Power 300 W
Imaging Instruments
Panchromatic Camera
Swath 23 km
Resolution 2,1 m
Spectral Band 0,52–0,85 μm
Мультиспектральная камера
Swath 20 km
Resolution 10,5 m
Spectral Band 0,54–0,6; 0,63–0,69; 0,69–0,72; 0,75–0,86 μm
Command Radio Link
Memory 24 Gb
Operating Frequencies 8084–8381,5 MHz
Channels 2
Data Rate 61,4 Mbps


ExactView 1 (ADS-1B)



EV-1.jpg    
ExactView 1 (EV 1) is a ship-monitoring microsatellite built by Surrey Satellite Technology Ltd. (SSTL), a leading small satellite manufacturer, for COM DEV Canada, a designer and manufacturer of space hardware.

EV 1 is based on an SSTL-100 platform and will form part of COM DEV’s exactEarth AIS constellation used by ships and traffic to, for example, monitor ship movements through busy shipping channels and harbors and to provide information on global shipping movements.

Automatic Identification System (AIS) is an RF-based communications system designed primarily as a collision avoidance system for large vessels. By broadcasting key details over VHF every few seconds about their identification, current position, heading and speed, passing ships can select a safe course even when conditions prevent visual contact.

Since 2004, the International Maritime Organization (IMO) has required AIS transponders to be aboard all vessels that exceed 300 gross tons. Over 60,000 ships worldwide have installed these transponders at a combined cost of several hundred million dollars, making AIS one of the most successful maritime technology deployments of all time. Additionally, AIS technology is increasingly being deployed in smaller vessels and is also being installed in Aids-To-Navigation (AtoN) and Search and Rescue (SAR) transponders.

EV 1 Specifications

Applications
Ship monitoring
Orbit
Sun-synchronous
Altitude 817 km
Inclination 98,88°
Customer COM DEV Canada
Prime Contractor SSTL
Platform SSTL-100
Spacecraft Mass 95 kg
Design Lifetime
5 years
Orientation Accuracy
Roll and Pitch < 3°
Yaw < 5°
Average Day Power 66 W
Payload
C-Band Transmitter 1
Frequency
5,183 MHz
Rate
20 Mbps
VHF Receiver 1
Frequency
162 MHz
S-Band Command Link
Memory
16 GB
Channels 3
Transmitter Rates
Low Rate
38.4 Kbps
High Rate
8 Mbps
Transmitter Frequencies
Low Rate 2,230 MHz
High Rate 2,233.333 MHz
Transponder
2,275.11 MHz


TET-1



tet1.jpg    
TET-1 is a technology demonstration microsatellite built by Germany’s Kayser-Threde GmbH for DLR, the German space agency.

The Technology Demonstration Carrier (TET) is the core of DLR’s OOV (On Orbit Verification) Program initiated to offer on-orbit verification possibilities to the German industrial and scientific aerospace community.

TET является центральным элементом программы орбитальных испытаний (OOV) DLR, которая дает возможность немецкому промышленному и научно-космическому сообществу проводить демонстрацию технологий на орбите.

TET-1 is based on the successful bus concept of the BIRD satellite (Bi-Spectral Infra-Red Detection), which was launched in 2001. It was adapted with regards to new available components to achieve better performance, more payload volume and mass and a much higher reliability of the system. The new satellite bus differs from its predecessor in a changed onboard data management. Also, the satellite’s sensors and actuators have been modified and a new payload has been added.

The TET-1 mission accommodates 11 different payloads, including three different types of next generation solar cells; a lithium polymer battery; two GPS receiver systems; a sensor bus system; a picosatellite propulsion system; an infrared camera; computer hardware; and an RF communication system. Nine payloads are hosted in the payload segment, and the other three are placed on the middle solar panel and the payload panel.

Характеристики КА TET-1

Applications
Technology demonstration
Orbit
Sun-synchronous
Altitude 539–560 km
Inclination 97,6°
Customer DLR
Prime Contractor Kayser-Threde GmbH
Spacecraft Mass 117,3 kg
Design Lifetime
1 year
Payload Power Consumption
Continiuous 20 W
Peak 160 W
Receiver Frequencies
GPS Antenna 1,575.42 MHz
S-Band Antenna 2,032.5 MHz
Transmitter Frequency 2,203.707 MHz


   
The Soyuz-FG launch vehicle is a modified version of the production Soyuz launcher. The upgrade includes incorporation of improved performance engines originally developed for the Soyuz-2 launch vehicle into the core section and lateral assemblies.

Soyuz-FG is developed and manufactured by the Progress State Research and Production Rocket Space Center (TsSKB Progress) of Samara under a contract awarded by the Federal Space Agency.

In terms of design, the Soyuz-FG launch vehicle is a system with parallel separation of the lateral rocket engine assemblies upon 1st stage burnout, and transverse separation of the 2nd stage engine assembly after burnout. While the engines of the four lateral assemblies and the core section are fired in concurrence at the initial phase of flight, only the engines of the core section continue firing after separation of the lateral units.

Compared to the power units of the Soyuz launcher, the main engines of the Soyuz-FG 1st and 2nd stages show improved thrust performance due to the monopropellant injectors provided in the injector assemblies for better mixing.

Soyuz-FG places into orbit all kinds of spacecraft launched by the Soyuz launch vehicle.

The control system of the Soyuz-FG launch vehicle borrowed from the Soyuz prototype ensures high injection accuracy.

The first and second stages are equipped with telemetric monitoring systems borrowed from the Soyuz rocket to control the launch vehicle’s assemblies and structures.

The first stage consists of 4 lateral assemblies conical in shape. These assemblies are attached to the central core unit by means of spherical joints. Each lateral assembly consists of a load-bearing cone, conical load-bearing oxidizer tank, intertank module, conical load-bearing fuel tank, hydrogen peroxide and liquid nitrogen tanks section, and cylindrical tail section.

An RD-107A self-contained liquid engine is located in the tail section of each lateral assembly. These engines use liquid oxygen and kerosene as propellants. The engines accommodate four cruising thrust chambers and two steering nozzles.

Flight is controlled by means of air rudders mounted on a small pylon opposite the core section, on the outer side of each lateral assembly. These rudders are designed as low-aspect triangle wings. An electric actuating unit is used as a rudder driver.

The engines of the lateral assemblies burn approximately 118 seconds, following which they are shut down. The shutdown occurs according to comparison of current and nominal velocity values. After shutdown the lateral assemblies are separated from the core section and jettisoned.

The second stage (core section) consists of a tail section, hydrogen peroxide tank with an inside-mounted liquid nitrogen toroidal tank, fuel tank, oxidizer tank, and equipment bay. The tail section contains an RD-108A liquid engine, comprised of four cruise thrust chambers and four steering nozzles.

The liquid engines of the core section and lateral assemblies are fired on the ground that makes it possible to control engine operation in transient mode and to cancel the launch in the event of a malfunction. This procedure increases operation safety.

Flight is controlled in three axis using four steering nozzles of the RD-108A engine. The designed burn duration of the core section engine is approximately 280 – 290 seconds. The second stage separates from the third stage using the so called "hot profile."

The third stage (Assembly I) consists of an adapter module, fuel tank, oxidizer tank, tail section and engine. The stage is mounted on the core section and is connected with it by a truss structure.

The Assembly I hosts a propulsion system similar to that on the Soyuz launch vehicle. This system includes an engine with four thrust chambers, and four pivoted steering nozzles for three-axis flight control. The cruise engine of the third stage is fired about 2 sec prior to the core section hutdown. Gases, flowing out of the third stage engine nozzles, directly separate this stage from the core section. The burn duration of the third stage engine is approximately 230 sec. After engine shutdown and fourth stage separation, the third stage performs a collision avoidance maneuver.

Soyuz-FG Characteristics

 
First stage
(Lateral Assembly)
Second stage
(Core Unit)
Third stage
(Assembly I)
Number 4 1 1
Length, m 19,6 27,1 6,7
Diameter, m 2,68 2,95 2,66
Charged Unit Mass, t 43,4 99,5 25,3
Dry Mass, t 3,80 6,55 2,41
Engine RD-107А RD-108А RD-0110
Number 1 1 1
Propellant Components:
Oxidizer / Fuel Liquid oxygen / Kerosene Liquid oxygen / Kerosene Liquid oxygen / Kerosene
Thrust, kN:
Ground / Vacuum 838,5 / 1021,3 792,48 / 990,18 - / 297,93
Burn Duration, s 118 280 230


fregat-a.jpg     
The Fregat upper stage is designed by the Lavochkin Research and Production Association under the Federal Space Program of Russia.

Fregat is intended to place a variety of spacecraft in orbit using both existing or future launch vehicles of the R-7A family.

The upper stage makes it possible to appreciably increase power and performance of launch vehicles. Fregat enables to deliver spacecraft practically to any Earth orbit or interplanetary trajectory.

The Fregat upper stage is designed to:

•  transfer one or more spacecraft from their support orbits to working orbits or escape trajectories;
• distribute craft between working orbits in multi payload launches;
• move payload from open-end trajectories into support orbits (final injection maneuvering);
• stabilize payload both at coasting and launch phases;
• ensure the required attitude prior to craft separation;
• remove the upper stage from working orbit after injection to prevent pollution of outer space.

The structure of the Fregat upper stage is formed by the pack of tanks for the main propulsion system. These tanks are configured as six hemispheres of equal diameter, welded together. Four spheres act as the propellant tanks, the remaining two operate as sealed instrumentation bays. Oxidizer tank and fuel tank are separated one from another by tri-metallic partition walls. A strengthening beam passes through each propellant tank, one per tank, and two beams per tank are used for pressurized containers. These beams form a connection truss.

Fregat Characteristics

Launch Mass, kg 6415 – 6535
Dry Mass, kg 980 – 1100
Overall Dimensions, mm Height 1500
Diameter (circumscribed) 3350
Main Propulsion System Designation С5-92
Dry Mass, kg 75
Propellant Components Oxidizer nitrogen tetroxide
Fuel UDMH
Propellant Components Ratio 2
Fuel Operation Reserve (max), kg 5350
Main Engine Thrust, kN 20
Engine Specific Impulse, N x s/kg
3285
Combustion Chamber Pressure, MPa 9,80
Maximum Firings 20
Stability, Orientation Control and Launch Support Power Unit
Fuel hydrazine
Fuel Operation Reserve (max), kg 85
Thrusters 12
Thrust, N 50
Thruster Specific Impulse, N x s/kg 2250


pl31-pu6.jpg

Soyuz-2 launch vehicle
    

Baikonur’s Pad 31 hosts launches of boosters derived from the first Soviet intercontinental ballistic missile, R-7.

The pad’s Launcher 6 was first used on January 14, 1961, to test an R-7A ICBM.

Pad 31 has seen launches of Meteor, Molniya, Pronoz, Resurs, IRS and Kosmos satellites. Soyuz crew missions were deployed from this pad in the 1970s and early 1980s.

By 2006, it was upgraded to launch the Soyuz-2 vehicle and is now used to dispatch commercial flights of Soyuz-FG/Fregat or Soyuz-2/Fregat launch systems.

When the International Space Station transitioned to a six-person crew in 2009, part of Progress resupply flights, which are boosted Soyuz-U rockets, were moved to Pad 31.

Customers Launch




Federal Space Agency

The Russian Federal Space Agency (Roscosmos) is a governmental organization which manages space exploration activities for the national economy, science and engineering and implements the Russian Space Program.


Participants Launch




Progress State Research and Production Rocket Space Center

The Progress State Research and Production Rocket Space Center is Russia’s leading developer of medium launch vehicles, space complexes and defense, commercial, research and applied systems. The Center has designed highly reliable launch vehicles for spacecraft, manned and cargo spaceships and a number of complexes for technological research and imaging.



VNIIEM Corporation Joint Stock Company

VNIIEM develops and manufactures onboard equipment for manned space stations and builds automatic spacecraft of the Meteor, Resurs-01, and Elektro series for hydrometeorology, natural resources and environment monitoring.



Lavochkin Research and Production Association

One of the Russian leaders in development and implementation of projects concerned with exploration of the Solar System planets, the solar weather, space information systems, the Earth’s surface monitoring, and astrophysical studies.



The Center for Ground-Based Space Infrastructure Facilities Operation

The Center for Ground-Based Space Infrastructure Facilities Operation (FGUP TsENKI) was established in 1994 to improve and develop Russia’s space infrastructure.



Yuzhny Space Center, TsENKI Division

Founded in 2009, the Yuzhny Space Center is a division of the Center for Ground-Based Space Infrastructure Facilities Operation (TsENKI) based on the organizations and facilities of Baikonur Cosmodrome in Kazakhstan.



Glushko Research and Production Association for Power Engineering

The Glushko Research and Production Association for Power Engineering (NPO Energomash) is the leading organization in development and manufacture of liquid propellant engines.



Automatic Chemical Machinery Design Bureau

KBKhA is one of Russia’s leading design bureaus in the development of liquid propellant rocket engines and power plants for defense, research, and commercial rocketry.



Kuznetsov Joint Stock Company

Kuznetsov Joint Stock Company makes RD-107/RD-108 that are installed on the first and second stages of Soyuz, Soyuz-2 and their variants generated Progress State Research and Production Rocket Space Center.



Scientific-Production Association of Measuring Equipment

Company Scientific-Production Association of Measuring Equipment (NPO IT) - one of the leading Russian companies to develop, manufacture and maintenance of the telemetry system for rocket and space technology.



COM DEV International

COM DEV manufactures advanced products and subsystems that are sold to major satellite builders for use in communications, space science, and remote sensing.



Surrey Satellite Technology Limited

SSTL provides complete in-house design, manufacture, launch and operation of small satellites; delivers complete mission solutions for remote sensing, science, navigation and telecommunications; supplies avionics suites and subsystems; and builds and installs ground infrastructure.



DLR

DLR is Germany’s national research center for aeronautics and space. Its extensive research and development work in aeronautics, space, transportation and energy is integrated into national and international cooperative ventures.



Kayser-Threde GmbH

Founded in 1967, Kayser-Threde is a leading provider of high-technology solutions for the industrial, aerospace and scientific sectors.



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UPCOMING LAUNCH

Предстоящий запуск Date: September 26, 2014
Launch Vehicle: Soyuz-FG
Payload: Soyuz TMA-14M
Launch Site: Baikonur, Pl. 1, Launcher 5



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