DubaiSat-2,STSat-3,SkySat-1,БПА-3,BRITE-PL,14ИСЗ – Днепр - 21.11.2013 - Домбаровский

[Lanista]

Сало положил им сайт =)

[cross-track]

SOE пишет:
Вот как надо денежки экономить.

Интересно, куда смотрят страховщики? Или спутники не застрахованы?

[PIN]

cross-track пишет:
Или спутники не застрахованы?

Понятия не имею. Но предположил, что, скорее, не застрахованы. По такому самопалу премии должны быть недешевые, зачем тратиться на аппараты, которые сами же для себя и делают?

[cross-track]

SOE пишет:
Понятия не имею. Но предположил, что, скорее, не застрахованы. По такому самопалу премии должны быть недешевые, зачем тратиться на аппараты, которые сами же для себя и делают?

Да, наверное страховать смысла нет. Тогда кантовать вполне допустимо 

[che wi]

КА «ДубайСат-2» и «СТСАТ-3» доставлены на БП КА "Ясный"
http://www.kosmotras.ru/news/134/

24 октября 2013г. космические аппараты «ДубайСат-2» (заказчик – Институт передовых исследований и технологий ОАЭ (EIAST)) и «СТСАТ-3» (заказчик – Корейский институт аэрокосмических исследований (KARI)) прибыли на Базу подготовки космических аппаратов «Ясный».




Тем временем в МИКе БП КА «Ясный» продолжаются работы по автономным проверкам космических аппаратов, которые были доставлены на базу на прошлой неделе (на фото ниже – КА СкайСат-1 (заказчик – Скайбокс Имэджинг, Инк.) в чистовом зале МИКа.



———
МКК "Космотрас" | 25.10.2013

[che wi]

Дата пуска ракеты «РС-20Б» с группой космических аппаратов
http://www.kosmotras.ru/news/136/

Дата пуска ракеты «РС-20Б» с группой космических аппаратов из позиционного района Домбаровский назначена на 21 ноября 2013 года в 07:10:11 UTC. Резервная дата пуска – 22 ноября 2013 года, 07:10:11 UTC.

———
МКК "Космотрас" | 01.11.2013

[Liss]

По сообщению Ронни Надера, второй эквадорский спутник NEE-02 Kryosar тоже на борту:

https://twitter.com/EXA_ec/status/396619221611728896

OFICIAL: Kosmotras confirma fecha de lanzamiento del NEE-02 KRYSAOR para Nov. 21 a las 07h10m11s...

[Alex-DX]

Два блога по теме.
http://www.pe0sat.vgnet.nl/2013/upcoming-dnepr-launch/
http://blog.isilaunch.com/

Как вставлять картинки? Например такую http://blog.isilaunch.com/wp-content/uploads/2013/11/DSC_1457.jpg

[ZOOR]

Alex-DX пишет:
Как вставлять картинки? Например такую http://blog.isilaunch.com/wp-content/uploads/2013/11/DSC_1457.jpg

Переходя в режим bb code ручками обрамляете тэгами [ img ]  [ /img ] (пробельчики в скобках лишние)

ЗЫ Это уже прибивать где-то в "Правилах форума" надо  

[Alex-DX]

Спасибо ZOOR.
Добавлю еще одну ссылку.
http://st2nh-blogger.blogspot.co.uk/

[PIN]

Если потрясти и спрессовать весь этот самопал, получится приличный КА, Криосат-2. Судя по картинке.

[ZOOR]

Alex-DX пишет:
 [ img ] [ /img ]

Ну я же говорил, что они еще на орбите почковаться будут

[Alex-DX]

Жаль, что не будет видео почкования рекордной группировки КА  

[che wi]

Интеграция КА с КГЧ
http://www.kosmotras.ru/news/138/

13 ноября 2013г. в МИКе Базы подготовки космических аппаратов «Ясный» была завершена интеграция спутников заказчиков с космической головной частью ракеты.





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МКК "Космотрас" | 14.11.2013

[che wi]

1 Rocket – 32 Satellites – Dnepr to make record-setting Launch
http://www.spaceflight101.com/denpr-2013-cluster-launch-updates.html

A Dnepr launch vehicle is being prepared for a record-setting cluster mission that will deliver a total of 32 satellites of various sizes to orbit. This launch will set the record for most active satellites launched on a single rocket. The launch is planned on November 21, 2013 at 7:10:11 UTC fr om the Dombarovsky missile range at Yasny Launch Base, Russia. This mission comes just two days after the planned launch of a Minotaur I rocket that will launch a total of 29 satellites.

Dnepr is a Russian/Ukranian Launch System based on the R-36M Intercontinental Ballistic Missile that is now operated by launch provider ISC Kosmotras for orbital launches. The Dnepr Launch Vehicle stands 34.3 meters tall and is 3.0 meters in diameter with a liftoff mass of 211,000 Kilograms. The launcher has three stages in its basic configuration. Dnepr can deliver payloads of up to 4,500 Kilograms to Low Earth Orbit.

Cluster Overview

Dubaisat-2

The primary payload of this flight is the Dubaisat-2 spacecraft, an electro-optical Earth observation satellite that was built by the Satrec Initiative and is operated by the Emirates Institution for Advanced Science and Technology. Imagery provided by the satellite will be commercialized for users in the United Arab Emirates and beyond. The satellite is based on the hexagonal SI-300 satellite bus being 1.5 by 1.95 meters in size with a mass of ~300 Kilograms.

Спойлер

The satellite bus consists of two decks and an upper sunshield. The decks and the side panels facilitate the satellite electronics. Longerons and and rails are making up the bus structure frame. Carbon Fiber Reinforced Plastic struts are used to hold the sun shield at the baffle of the main payload, the High Resolution Advanced Imaging System that is installed on the internal deck structure.

Four solar panels are attached to the sides of the satellite and deploy shortly after launch. Each array consists of six individual panels that each contain 26 cells. The solar arrays generate 450 Watts of power. The four solar arrays provide electrical power to a triple-redundant Battery Charging Regulator that manages the sate of charge of a Li-Ion battery. A Primary Power Conditioning Module and a Secondary Power Conditioning Module provide the satellite's power bus.

A regulated 28-Volt power bus is converted into unregulated buses at 15, 12 and 5 Volts. These voltages are distributed by the Primary & Secondary Power Distribution Modules. The EPS is a stable system that includes Safety and Separation Modules.

Dubaisat-2 is three-axis stabilized and its Attitude and Orbit Control Subsystem provides satellite pointing capability for single-strip, multi-strip and single-pass stereo imaging. Five reaction wheels are used for attitude control along with four Fiber Optic Gyros. Attitude data is provided by Star Trackers for fine-pointing and magnetometers and sun sensors for coarse pointing in safe and acquisition mode. Dubaisat-2 has a pointing accuracy of 0.12 degrees on all axes. A Hall Effect Propulsion System is used for orbit maintenance and orbit adjustments. It uses electric propulsion utilizing Xenon gas and a microwave cathode.

The HEPS system consists of a XFU (Xenon Fuel Unit), THU (Thruster Head Unit), PPU (Power Processing Unit) and the MCU (Microwave Cathode Unit). The XFU holds about two Kilograms of Xenon fuel that is held at a pressure of 150 bar. Via pressure valves and orifices, Xenon is allowed to flow into two smaller tanks, each at 3 bar for the anode and cathode. The thruster head includes magnets for ion motion detection while the PPU provides the different voltages for the HEPS system to accelerate generated Xenon ions to high velocity for ejection. The HEPS provides 7 Millinewtons of thrust consuming about 300 Watts of power.

The Command and Data Handling System handles all telecommands sent to the satellite and collects all telemetry from the satellite's subsystems. Two CAN networks with data rates of 500kbit/s are using a series of Interface Boards to connect all satellite modules to the networks. The Interface Boards are in charge of formatting telemetry data and handling messages received from the main computer. The Actuator Interface Board controls the speed of the reaction wheels and provides a speed feedback to the computers.

Gyro telemetry is provided by a Gyro Interface Board while a Primary and Secondary Power Interface Board controls the Power Modules. Attitude sensor data is provided by a Sensor Interface Board while the Thermal Interface Board takes temperature readings for heater actuation. X-Band antenna driving units control the communications system and a dedicated HEPS control board drives the Orbital Control System.

Two Telemetry and Telecommand Boards are operated in hot-redundancy to perform all telecommand decoding and telemetry encoding directly interfacing with the S-Band system that is used for command uplink and telemetry downlink. The On-Board Computer is the central processing unit of the vehicle that communicates with all modules through the CAN network. All telemetry data from the various subsystems is processed and recorded. All telecommands are handled and executed by the system to control all the satellite's functions. The computers run flight software using the VxWorks operating system. Onboard data storage us accomplished by Solid State Recorder Units  with a total capacity of 256 Gbit.

The satellite is equipped with an S-Band communications system for command uplink and telemetry downlink. Payload Data is downlinked via a high-speed X-Band terminal that achieves data rates of 160Mbit/s. The system uses a one-axis steerable antenna.

The main instrument of the satellite is the High Resolution Advanced Imaging System that provides Earth imagery with a ground resolution of 1 meter for panchromatic images and 4 meters for multispectral imagers. The imager covers a ground swath of 12 Kilometers.

The payload features a Korsch-type telescope with a five-mirror design. The main mirror of the satellite is 41.5 centimeters in diameter. Three mirrors are used to create a total focal length of 5.7 meters. A Flat Mirror reflects the light onto the Focal Plane Assembly. The mirrors are made from Zerodur that provides high-thermal stability. The telescope structure consists of Reinforced Carbon Fiber. A feedback heating system is used to keep the telescope components in perfect alignment featuring accurate thermostats and heaters along with passive heat-rejection systems.

Located on the Focal Plane Assembly is a pushbroom-type Charged Coupled Device that acts as detector and provides an analog signal that is converted into a 10-bit digital data stream that is processed by the Onboard Computer for storage and eventual downlink.

[свернуть]

STSat-3

The second of the two primary payloads is STSat-3 – the Science and Technology Satellite-3 which is a multi-purpose microsatellite that was designed and developed by the Satellite Technology Research Center of the Korea Advanced Institute of Science and Technology. The satellite weighs 150 Kilograms and is 1.024 by 1.030 by 0.885 meters in size. It carries two main payloads, the Multi-purpose Infrared Imaging System and the Compact Imaging Spectrometer.

Спойлер

The satellite is three-axis stabilized with a pointing accuracy of 0.13 degrees. Attitude data is provided by Coarse Sun Sensors, four gyros, two star trackers and a Tri-Axis Magnetometer. A GPS receiver provides on-orbit position and timing. Attitude control is provided by a Reaction Wheel Assembly consisting of four wheels. Satellite propulsion is provided by a 679-Watt Hall-thrust Propulsion Subsystem.

The HPS is an experimental payload weighing 14.6 Kilograms. Using Xenon, the system provides 10 Millinewtons of thrust.

The satellite is equipped with two solar arrays, a Solar Array Power Regulator, Power Supply Unit and a Power Distribution unit as well as a 20 Amp-hour Li-Ion battery for power storage. The arrays provide 286 Watts of power. The electronics manage battery state of charge and generate an unregulated power bus that is then converted to regulated 5, 12 and 20-Volt buses. The satellite uses an RS-422 analog data bus for telemetry and command handling and a high-speed LVDS bus that achieves data rates of 1.2Mbit/s for payload data handling. The Command & Data Handling Subsystem manages the spacecraft and payload functions according to uplinked ground commands. It also stores the payload data and provides them for downlink to the ground. The satellite is equipped with a Mass Memory of 32 Gbit.

The spacecraft uses an S-Band system with up to 9.6kbit/s for uplink and 38.4kbit/s for downlink. S-Band is used for command uplink and housekeeping telemetry downlink. Payload data is downlinked via a high-speed X-Band system.

The main payload of the STSat-3 spacecraft is the Multipurpose Infrared Imaging System – MIRIS. The instrument will survey the Galactic plane to detect the cosmic infrared background using two infrared cameras – MSOC (MIRIS Space Observation Camera) for near IR observations of the diffuse warm ionized medium in the Galaxy plane with a Field of View of 360º x 6°, and MEOC (MIRIS Earth Observation Camera) to conduct Earth observations.

MSOC covers a spectral range of 0.9 to 2 micrometers. The imager has an aperture diameter of 80 millimeters. The optics consist of five lenses – all of them are spherical with the exception of the rear of the fifth lens which is asymmetrical. A Winston Baffle is attached in front of the telescope to block strong radiation from Earth's surface. MSOC is equipped with an actively cooled infrared detector of 256 by 256 pixels creating a detector field of view of 3.67 by 3.67 degrees.

The MEOC instrument features a Cassegrain telescope and relay lens systems. The telescope utilizes zerodur aspherical mirrors and germanium and silicon lenses attached behind the telescope. A warm stop is ins erted behind the lens system to reduce thermal noise using a bandpass filter of 3.8 to 4.8 micrometers.

MEOC covers a spectral range of 3 to 5 micrometers using an effective aperture diameter of 100mm. It uses an HgCdTe detector that is cooled to 80K. The detector is 320 by 326 pixels in size creating a detector field of view of 1.1 by 1.1 degrees and a pixel field of view of 12.4 by 12.4 arcsec. MEOC achieves a ground pixel size of 42 meters and covers a 13.4-Kilometer ground swath. MEOC can take up to 5 images per second, but will usually be operated at 1fps. Its exposure time can vary from 1ms to 655ms.

The Compact Imaging Spectrometer – COMIS is an imaging spectrometer to acquire hyperspectral images over a 28km swath with a 30 or 60-meter spatial resolution that can be ground-commanded. The instrument covers a spectral range of 0.4 to 1.05 micrometers and achieves a spectral resolution of 2 to 15 nanometers.

COMIS uses a Maksutov catadioptric telescope and an imaging spectrometer. The telescope provides an image of the ground swath onto the spectrometer entrance slit. The spectrometer then re-images the collected light, disperses it in the direction perpendicular to the slit image, and focuses it on the detector. COMIS uses a CCD array detector system with pixel sizes of 13 by 13 micrometers.

[свернуть]

Secondary Payloads

The SkySat-1 satellite is a small satellite built and operated by Skybox Imaging that is licensed to acquire high resolution panchromatic and multispectral images of Earth. The satellite weighs approximately 100 Kilograms and features body-mounted solar panels as well as a protective cover that shields the imager during launch. The spacecraft will acquire high-resolution images and video of Earth.

WINSAT-1 – the Weather News Inc. Satellite 1 is a 10-Kilogram satellite dedicated to Arctic Sea and atmospheric monitoring. The spacecraft is 27 by 27 by 27 centimeters in size. It is equipped with a three-axis control system with navigation data provided by a magnetometer, gyroscopes, Sun sensors and star trackers while attitude control is provided by magnetic torquers and reaction wheels.

Спойлер

Power is provided by ultra triple-junction and triple-junction solar arrays mounted on five sides of the satellite providing 12.6 Watts of power. A UHF Communication System achieves data rates of up 38.4kbit/s for downlink and 9.6kbit/s for command uplink.

The satellite is equipped with two cameras – one for the visible spectrum and the other covers Near-Infrared Radiation. The two imagers have focal lengths of 8 millimeters and use 1024 by 1024-pixel detectors with 6.7 by 6.7-micrometer pixels. The cameras have a field of view of 56.4 by 56.4 degrees to cover a ground frame of 500 by 500 Kilometers with a sample distance of 500 meters. 10 frames are acquired per day. The two imagers are used to monitor Arctic Sea Ice.

The second payload of the satellite is the Laser Mission Unit that is being used to monitor the Carbon Dioxide Density in the atmosphere. Two lasers (1570nm and 1556nm) emit pulses in the nadir direction which are measured by a ground station using a parabolic antenna. The 1570nm beam is strongly absorbed by Carbon Dioxide while the 1556nm beam is not attenuated. Comparing the intensity of the two beams allows the CO2 column density to be determined.

[свернуть]

UniSat-5 is a satellite developed at the University of Rome. The satellite weighs 28 Kilograms and is 50 by 50 by 50 centimeters in size using reinforced aluminum honeycomb panels. Four deployable solar arrays provide 200 Watts of power, reaction wheels are used for attitude control and a VHF/UHF, C-Band and S-Band communication system is used for command uplink and data downlink. The payload of the satellite is called the Digital Imaging Payload that will be used to monitor space debris in orbit. The optical payload is comprised of a Schmidt Cassegrain telescope and a camera. The payload has an aperture of 127 millimeters, a focal length of 1250mm and a tube length of 330mm. It uses a 2592 by 1936 pixel detector that provides imagery that is stored in a 128MB SDRAM and 128MB NAD memory.

The BRITE-PL satellite - BRIght-star Target Explorer – Poland is a 6-Kilogram satellite that is 20 by 20 by 20 centimeters in size. The spacecraft is equipped with an attitude determination and control system with pointing accuracy of better than one degree. Power generation is accomplished by body mounted solar cells that provide up to 10 Watts of power. The satellite uses an S-Band system for data downlink of up to 256kbps and a UHF system for telemetry downlink. The spacecraft has a data storage capacity of 256MB. The satellite carries an imaging payload that will examine some of the brightest stars in the sky in order to examine these stars for variability with an accuracy ten times that of ground-based observations. The satellite uses a Wide-Field Camera for sky imaging that will focus on 500 to 800 bright stars.

AprizeSat 7 and 8 are part of a constellation of Low Earth Orbit satellites that provide global communication services for data transmission and fixed and mobile asset tracking and monitoring. The 12-Kilogram satellites carry ten radio receivers, two power-agile transmitters and 12MB of solid sate data storage. The radios operate in the UHF frequency band to collect data from more than 100,000 user terminals each day. These are the 9th and 10th satellites to be launched since 2002. The expected satellite lifetime is 10 to 12 years and the planned constellation will consist of a total of 64 satellites.

The 3U CubeSat Delfi-n3Xt is a 3-Kilogram spacecraft developed at the Technical University of Delft. The satellite uses four deployable solar arrays to provide 12W of power to its two payloads. A micro-propulsion system will be demonstrated as an in-orbit reconfigurable, high-efficient platform. The experimental micro propulsion system uses eight Cool Gas Generators to supply gaseous Nitrogen from a solid charge to build up a chamber pressure of about 4.5 bar. The small thruster is operated in blowdown mode providing a thrust of 6 to 100 Millinewtons. The Cool Gas Generators each are loaded with 0.3 grams of propellant that can be used to generate 0.1 liter of N2 gas.

Спойлер

Delfi-n3xt also carries a Multifunctional Particle Spectrometer which is a radiation detector that can measure the energy and incidence angle of alpha particles, protons, electrons and gamma radiation. The system is 7.5 by 7 by 8 centimeters in size, weighing 600g. It is capable of detecting gamma rays at energies of 0.2 to 3 MeV, electrons from 1 to 20 MeV, protons from 1-200MeV and ions from 6 to 400 MeV/n.

Testing a compact and power-efficient device in orbit could qualify the unit as a satellite health monitor that would be used on operational satellites to detect the cause of radiation-related problems of spacecraft electronics.

The satellite also carries a Solar Cell Degradation Measurement payload that will expose new types of solar cells to the space environment and measures the performance of the cells over time to assess their degradation. Additionally, the satellite carries a Space Flash system that uses commercial SD memory cards and additional electronics that make the storage medium immune to radiation over a two-year period. The performance of that system will be evaluated throughout the mission.

Low data rate VHF and UHF communications are used for telemetry downlink and command uplink while S-Band is used for data downlink.

[свернуть]

Dove 3 and Dove 4 are 3U CubeSats flying an experimental mission that is dedicated to the acquisition of Earth imagery. The satellites have a launch mass of 5 Kilograms featuring body-mounted solar panels and 25 by 30-centimeter deployable solar arrays. Using magnetometers, the satellites will determine their orientation while magnetic torquers are used to keep the spacecraft in Earth pointing attitude for imagery acquisition.

The Triton-1 satellite is also a 3U CubeSat developed by Innovative Solutions In Space BV. It will demonstrate new technologies in the space environment. The spacecraft tests a radio science payload, an advanced AIS (Automatic Identification System) receiver, telemetry decoding software and flight software. Telemetry decoding software is being made available to amateur satellite trackers so that they can pick up periodic downlink broadcasts that contain telemetry, payload data and AIS messages.

The CINEMA 2 and CINEMA 3 satellites are 3U CubeSats each weighing about 4 Kilograms. The Cubesat for Ion, Neutral, Electron, Magnetic fields mission carries two instruments – the MAGIC (MAGnetometer from Imperial College), and the STEIN (SupraThermal Electrons Ions & Neutrals) particle detector.

Спойлер

STEIN will be used to perform space weather studies and to demonstrate the technology of a miniaturized instrument that is capable of detecting electrons, ions, and neutrals for a wide variety of space and planetary physics missions.

The MAGIC instrument features a dual three-axis Anisotropic MagnetoResistive sensor that is installed on a one-meter boom that deploys from the satellite. An inboard magnetoresistive sensor can be used to process the data and subtract spacecraft induced fields. The sensor has a range of +/-57,000 nanotesla and a 0.22nT resolution.

[свернуть]

The OPTOS satellite is a project of Instituto Nacional de Tecnica Aerospacial. It is a 3U CubeSat dedicated to technical demonstrations in orbit. The 3-Kilogram spacecraft will test a distributed OBDH (On-Board Data Handling) subsystem based on FPGAs (Floating Point Gate Arrays), new Complex Programmable Logic Devices, and an optical wireless communication system (OBCom) with a reduced CAN (Controller Area Network) protocol.

Спойлер

The satellite carries an Athermalized Panchromatic Image Sensor to study the degradation of lenses in space by imaging the space environment in identical lighting conditions. A Fiber Bragg Gratings for Optical Sensing payload will measure temperature by studying the wavelengths of a laser beam traveling across the Bragg gratings.

The Giant Magnetic-Resistance System is planned to determine the intensity of magnetic fluxes produced by Earth's magnetic field. The spacecraft also carries a new Dose Monitoring system to measure the radiation environment around the satellite.

[свернуть]

CubeBug-2 is a 2-Unit CubeSat from Argentina which will serve as a demonstrator for a new CubeSat platform design. The satellite will verify new hardware and software concepts that will be released as Open Source and Open Hardware for its use in Amateur projects, University projects and research labs. It is equipped with a number of Commercial Off The Shelf COTS components that will undergo testing in space.

GOMX1 is a 2U CubeSat dedicated to radio research in orbit. It carries a payload that can track trans-oceanic flights by reception of the Automatic Dependent Surveillance-Broadcast (ADS-B) signal sent by the aircraft. This ADS-B signal is used for air traffic control in areas that are covered by ground-based receivers, but not over the oceans due to lim ited signal range. GOMX1 will demonstrate whether the signals can be received by a satellite in Earth orbit for possible future use in air traffic control. The satellite is equipped with a Software Defined Radio. The mission will also test the use of open source Cubesat Space Protocol.

The NEE-02 Krysaor satellite is a 1U CubeSat and the second satellite of Ecuador. It uses two deployable solar arrays and body mounted solar panels. It will test a number of systems in orbit including real time video transmission, a thermal and radiation shield, a multiphase solar array, passive antenna deployment and carbon nanotubes for thermal control. The satellite will complete a number of demonstration and education tasks including the relay of imagery from orbit.

FUNCube-1 is a 1U CubeSat carrying a single U/V linear transponder with a beacon carrying telemetry and data for educational demonstrations from space involving amateur radio satellite trackers. The satellite will serve a number of educational purposes using simple receivers and display software for use at schools.

The HiNCube, or Høgskolen i Narvik CubeSat, is a 1U CubeSat that carries a color camera that will be taking photos of Earth for downlink to ground stations. A number of temperature sensors are installed on the satellite to study the variation of the satellite's thermal environment.

ZACUBE-1 - South Africa CubeSat-1 is a 1U CubeSat developed by Students at the Cape Peninsula University of Technology, Cape Town. Its primary payload is a high-frequency beacon transmitter (8-22MHz) that will be used for ionospheric measurements and calibrations of the auroral radar installation at the South African National Space Agency Base in Antarctica.

ICube-1 is the first CubeSat of Pakistan. The 1U spacecraft was developed at the Institute of Space Technology, Islamabad.

It carries a low-resolution camera, three-axis magnetometer and several temperature sensors. Earth pointing is achieved by using Earth's magnetic field.

Also a 1U satellite, HumSat-D was developed by the University of Vigo, Spain. It will perform an educational mission to allow students hands-on experience conducting a space mission. Also, the satellite serves as a pathfinder for the concept of a HumSat constellation of communication satellites to provide service to areas with no infrastructure through a series of small orbiting satellites. The satellites feature receivers, onboard storage and transmitters to test a simple store-and-forward architecture. The satellite is not equipped with an attitude control system.

The PUCPSat1 is the first Peruvian satellite that was built at the Institute for Radio Astronomy of the Pontificia Universidad Católica del Perú. It will be installed on the Unisat-5 satellite for release after separation from the launch vehicle. In turn, the 1.27-Kilogram PUCPSat1 satellite will release the 127-gram Pocket-PUCP picosatellite once in orbit. PUCPSat1 itself will transmit temperature readings of 19 sensors installed on the vehicle.

First-MOVE (First Munich Orbital Verification Experiment) is a 1U CubeSat that was built at the Technical University of Munich, Germany. The satellite uses two deployable solar arrays and body-mounted solar panels for power generation. It carries a CCD sensor with a resolution of 1.3MP and a field of view of 75 degrees for Earth imagery. The purpose of the satellite is a series of solar cell tests to be performed in orbit. The cells will be run in different operating modes and performance data will be obtained for downlink to Earth.

The UWE-1 satellite is also a German 1U CubeSat that was developed at the University of Würzburg. It will be used to demonstrate and test the adaption of internet protocols in the space environment. The mission will assess the significant signal propagation delays due to the large distances and much higher noise levels in the space environment. It is the third UWE satellite after the first was launched back in 2005.

The Velox-P2 satellite is a 1U CubeSat developed at the Nanyang Technological University, Singapore to demonstrate a number of technologies in space. It will demonstrate an in-house developed Attitude Determination and Control System, advanced power subsystems and a dual Field-of-View sun sensor payload.

The Beakersat 1 (also known as Eagle 1 or SWEsat) is a 2.5U PocketCube satellite. It was developed at Morehead State University. The spacecraft hosts a number of electronics that will be tested in space including a Pic18F25K22 processor along with circuitry to measure battery current & voltage, electronics temperatures, solar panel voltages, current, and temperature. Those telemetry val ues will then be transmitted to the ground via Morse Code.

Also a 2.5U PocketCube, the QubeScout S1 satellite was developed at the University of Maryland. The spacecraft will test a fine sun sensor for future attitude determination systems. It will also monitor the change in rotation of QubeScout as a function of changing moment of inertia during solar panel/ de-orbiter ops. The satellite is also hosted on the UniSat-5 payload for deployment after spacecraft separation.

Wren is a crowd-funded satellite built by STADOKO UG. The 1U CubeSat hosts a number of miniaturized µPP-Thrusters to demonstrate them in orbit along with a 3-axis control system and an innovative image-based navigation system.

Спойлер

The satellite is equipped with a camera for Earth, sun and deep-space imaging. Using imagery acquired by the camera, the satellite's computer will use an algorithm to identify the Earth's nadir relative to the sun as part of an adaptive feedback guidance system that also features conventional gyro- and magnetic field attitude sensors which could precisely navigate the satellite on its own using the four micro pulsed plasma thrusters of the satellite.

Wren uses a reconfigurable onboard computer and its communication system will be used for command uplink and data downlink.

[свернуть]

$50SAT, also known as Eagle 2, is a 1.5U PocketCube developed at Morehead State University. The spacecraft uses commercial electroncis and will use a micro radio transceiver, the HOPE RFM22 to demonstrate that it is sufficient for transmitting and receiving data from the satellite in Low Earth Orbit. Data to be downlinked includes a morse callsign and housekeeping telemetry. The satellite is also hosted on the UniSat-5 spacecraft.

BPA-3 – the Blok Perspektivnoy Avioniki-3 payload is attached to the upper stage of the Dnepr launcher to test navigation equipment for use on civil planes and spacecraft. The payload is attached to the Dnepr upper stage and is not separated.

Добавлю, что (возможно) вместо Beakersat 1 летит MagPocketQube.
Также ранее мелькала информация об итальянском eSt@r-2.

[che wi]

Стыковка КГЧ с ракетой
http://www.kosmotras.ru/news/142/

15 ноября произведена транспортировка Космической головной части с космическими аппаратами на стартовую позицию и ее стыковка с ракетой. В настоящее время проводятся заключительные проверки ракеты с КГЧ. Запуск планируется на 21 ноября 2013 года в 11:10 мск (07:10 UTC).

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МКК "Космотрас" | 15.11.2013

[LL_]

Не вопрос. За РС-20 записываем 32 боезаряда.
По договору предел 1550 боезарядов. Нарушаем...

[Salo]

http://www.kosmotras.ru/news/142/

[Salo]

http://forum.nasaspaceflight.com/index.php?topic=32780.30

Skyrocket пишет:
My count is 33 (with the same payloads as in this article) - but this probably just a question of definition - if you count BPA-3 as a satellite.

1   DubaiSat 2
2   STSAT 3
3   SkySat 1
4   WNISAT 1
5   BRITE-PL (Lem)
6   AprizeSat 7
7   AprizeSat 8
8   UniSat 5
9   Delfi-n3Xt
10   Dove 3
11   Dove 4
12   Triton 1
13   CINEMA 2 (KHUSAT 1)
14   CINEMA 3 (KHUSAT 2)
15   OPTOS
16   CubeBug 2 (Manolito)
17   GOMX 1
18   NEE 02 Krysaor
19   FUNcube 1
20   HiNCube
21   ZACUBE 1
22   ICube 1
23   HumSat-D
24   PUCP-SAT 1
25   First-MOVE
26   UWE 3
27   VELOX-P 2
28   BeakerSat 1 (Eagle 1)
29   $50SAT (Eagle 2)
30   QubeScout S1
31   Wren
32   Pocket-PUCP
33   BPA 3

[Ярослав]

bpa-3 - это ребята из днепра свои железячки дебажат ? ))