Long March 3B/E Launch:

Zhongxing-11 has a lift-off mass of around 5,000 kg and a design lifetime over 15 years. The satellite is based on the DFH-4 manufactured by the CAST (China Academy of Space Technology) and features multiple high power fixed and mobile beams and transponder switching capability.

It will provide services for commercial broadcasting and communications via 45 C-band and Ku-band transponders, aimed at meeting the needs of Direct-to-Home, data transmission, digital broadband multimedia and streaming media for clients in Asia, Africa, Australia – whilst covering large regions of China Sea, Indian Ocean and Arabian Sea.

As was the case with Zhongxing-12 (ChinaSat-12) – launched on November 27, 2012 – part of the satellite’s communications payload has been leased to Sri Lanka, co-branded as SupremeSat-II.

In 2012, SupremeSat has entered into a partnership agreement with CGWIC (China Great Wall Industry Corporation) for the design, manufacturing and launch of the SupremeSat-III satellite, a deal that also secured the marketing facilities of many other satellites owned and operated by CGWIC and the China Satellites Communications Corporation.

SupremeSat-III will be based on the DFH-4 platform, to be positioned at 50 degrees East Longitude, once launched by a Long March 3B/E launch vehicle.

The CAST manufactured DFH-4 (Dongfanghong-4) platform is a communications satellite bus featuring high capability and a long operational lifetime. It sports an output power and communication capability equivalent to the similar international bus specifications, and consists of propulsion and service modules, solar arrays and 3-axis stabilization.

The applications for the DFH-4 platform are not limited to high capacity broadcast communication satellites, with the ability to be used as tracking and data relay satellites and regional mobile communication satellites.

The spacecraft has a payload capacity of 588 kg and an output power of 10.5 kW through to the end of its lifetime.

The satellite is equipped with three receiver antennas and two transmission antennas. The DFH-4 satellite also features mitigation hardware to counter hostile jamming.

China’s second launch of 2013 was also the 176th successful Chinese orbital launch and the first from Xichang this year. A total of 78 orbital launches have been conducted out of Xichang.

Developed from the Chang Zheng-3A, the Chang Zheng-3B is the most powerful launch vehicle on the Chinese space launch fleet. The Apstar-7 launch was the 23rd flight of CZ-3B and the 55th flight of CZ-3A series launch vehicles.

The CZ-3B features enlarged launch propellant tanks, improved computer systems, a larger 4.2 meter diameter payload fairing and the addition of four strap-on boosters in the core stage that provide additional help during the first phase of the launch.

The rocket is capable of launching a 11,200 kg satellite to a low Earth orbit or a 5,100 kg cargo to a geosynchronous transfer orbit.

The CZ-3B/E (Enhanced Version) launch vehicle was developed from the CZ-3B, increasing the GTO capacity up to 5,500kg. The CZ-3B/E has nearly the same configurations with CZ-3B bar its enlarged core stage and boosters.

On May 14, 2007, the first flight of CZ-3B/E was performed successfully, accurately sending the NigcomSat-1 into pre-determined orbit. With the GTO launch capability of 5,500kg, CZ-3B/E is dedicated for launching heavy GEO communications satellite.

The Xichang Satellite Launch Centre is situated in the Sichuan Province, south-western China and is the country’s launch site for geosynchronous orbital launches.

Equipped with two launch pads (LC2 and LC3), the centre has a dedicated railway and highway lead directly to the launch site. The Command and Control Centre is located seven kilometers south-west of the launch pad, providing flight and safety control during launch rehearsal and launch. The CZ-3B launch pad is located at 28.25 deg. N – 102.02 deg. E and at an elevation of 1,825 meters.

Other facilities on the Xichang Satellite Launch Centre are the Launch Control Centre, propellant fuelling systems, communications systems for launch command, telephone and data communications for users, and support equipment for meteorological monitoring and forecasting.

The first launch from Xichang took place at 12:25UTC on January 29, 1984, when the CZ-3 Chang Zheng-3 (CZ3-1) was launched the Shiyan Weixing (14670 1984-008A) communications satellite into orbit.

(Images via ChinaDaily.cn, Xinhua).

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China’s 19th Launch Of 2012:

Launch was schedule on December 19, but adverse weather conditions forecast at the launch site prompted a 24 hour advancement of the mission.

The Göktürk-2 Program is an Earth Observation Scientific Research and Technology Satellite Development Project that is the first National Earth Observation Satellite that has been funded by The Scientific and Technological Research Council of Turkey (TÜBİTAK) resources.

The contract for the development of the satellite was signed by the Ministry of Defence (MoD), The Scientific and Technological Research Council of Turkey (TÜBİTAK) and TUBİTAK UZAY-TAI Consortium on 13 April 2007, which became effective on 1st May, 2007.

With the Göktürk-2 Project, not only the Turkish national capabilities and resources for the space systems – such as new technologies, experienced manpower and possession of new infrastructures – will be developed, but the image requirements of the Turkish Armed Forces and other public institutions will also be met.

The development of the Göktürk-2 Project is an effort to develop a satellite system and a subsystem design and development capabilities, as well as to establish a bus platform for future remote-sensing missions.

The main payload consists of a multi-spectral imager (MSI). The spacecraft is specified for an operational life time of five years, in a sun-synchronous orbit at an altitude of approximately 700 km and a local time of descending node between 10:30 and 11:30 a.m.

The satellite will be capable of a 2.5 meter panchromatic resolution and a 10 meter multispectral resolution. Its mission will have a dual civil and military purpose, with applications on disasters management, emergency situations, environmental control, mapping and planning, landcover survey, geology, coastal zone vigilance, ecosystem monitoring, water resources, etc.

Launch mass of Göktürk-2 is 450 kg and the first images sent by the new satellite are expected to be received between December 25 and 30.

The solar panels and the pyro drive module have been developed by SpaceTech GmbH, Immenstaad – Germany. The solar generator system consists of three solar panels including the photovoltaic assembly, the solar panel deployment mechanisms, and the pyro drive module (PDM) electronics executing the deployment sequence of the mechanism.

The solar panel delivery included three flight models and three qualification model units. One of the QM panels has been equipped with active cells, the remaining two are mass dummies.

Each of the three panels on the spacecraft consists of four arrays each with three strings of 20 cells. In addition to the cells temperature sensors for thermal control, thermistors as input to the satellite’s maximum power point tracker as well as bleed resistors for controlled insulation with the spacecraft body are accommodated on each panel.

Third generation AZUR cells with a rated efficiency of 28 percent are used to make up the photovoltaic assembly. Each cell is protected with a by-pass diode and each solar string by a blocking diode. The qualification and flight models of the solar generator system have been delivered to Turkey in 2010 and 2011 respectively.

The PDM development including one mass dummy, one qualification model and one flight model has been performed with support from APCON.

The main task of the PDM is to provide regulated current for a predefined period to release the solar panel deployment mechanisms by activating thermal knifes. The electronics is implemented in cold redundancy (electronic part) and, via internal cross-coupling) allows access to both hot redundant power stages.

For safety reasons a three-level inhibit system is implemented. Also, the PDM operates in different modes that are directly related to the safety inhibits.

The PDM is characterized by a low mass and volume. The design can easily be adapted for a higher number of activation chains, different types of actuators, e.g. pyros, and a different communication interface to the on-board computer.

The Chang Zheng-2D launch vehicle is a two-stage rocket developed by the Shanghai Academy of Spaceflight Technology. With storable propellants is mainly used to launch a variety of low earth orbit satellites.

The development of CZ-2D was started in February 1990. From 2002, to meet the demand of SSO satellites, the payload fairing of 3350mm in diameter and attitude control engine for second stage have been successfully developed; and the discharge of remaining propellant and de-orbit of the second stage have been realized. This launcher is mainly used for launching LEO and SSO satellites.

The CZ-2D can launch a 1,300 kg cargo in a 645 km SSO. The rocket is 41.056m long and the first, second stages and payload fairing are all 3.35m in diameter.

Its first stage is the same of the CZ-4 Chang Zheng-4. The second stage is based on CZ-4 second stage with an improved equipment bay. Lift-off mass is 232,250 kg, total length 41,056 meters, diameter 3.35 meters and fairing length 6.983 meters. At launch it develops 2961.6kN engine thrust.

The first stage has a 27.910 meter length with a 3.35 meter diameter, consuming 183,200 kg of N2O4 / UDMH (launch mass of the first stage is 192,700 kg). Equipped with a YF-21C engine capable of a ground thrust of 2,961.6 kN and a ground specific impulse of 2,550 m/s. Burn time is 170 seconds.

The second stage has a 10.9 meter length with a 3.35 meter diameter, launch mass of 39,550 kg and consuming 45,550 kg of N2O4 / UDMH. Equipped with a YF-24C cluster engine with a main engine vacuum thrust of 742.04 kN and a vernier engine with a vacuum thrust of 47.1 kN (specific impulses of 2,942 m/s and 2,834 m/s, respectively).

The CZ-2D can use two types of fairings depending of the cargo. Type A fairing has a 2.90 meters diameter (total launch vehicle length is 37.728 meters) and Type B fairing with a diameter of 3.35 meters – total launch vehicle length is 41.056 meters.

The first launch of the CZ-2D was on August 9th, 1992 from the Jiuquan Satellite Launch Center orbiting the Fanhui Shei Weixing FSW-2-1 (22072 1992-051A) recoverable satellite.

This launch was the 174th Chinese successful orbital launch and the 174th launch of a Chang Zheng launch vehicle, also becoming the 56th orbital launch from the Jiuquan Satellite Launch Center, the fifth orbital launch from Jiuquan this year and the 19th Chinese orbital launch in 2012.

The Jiuquan Satellite Launch Center, in Ejin-Banner, a county in Alashan League of the Inner Mongolia Autonomous Region, was the first Chinese satellite launch center and is also known as the Shuang Cheng Tze launch center.

The site includes a Technical Centre, two Launch Complexes, Mission Command and Control Centre, Launch Control Centre, propellant fuelling systems, tracking and communication systems, gas supply systems, weather forecast systems, and logistic support systems.

Jiuquan was originally used to launch scientific and recoverable satellites into medium or low earth orbits at high inclinations. It is also the place from where all the Chinese manned missions are launched.

Presently, only the LC-43 launch complex, also known by South Launch Site (SLS) is in use. This launch complex is equipped with two launch pads: 921 and 603. Launch pad 921 is used for the manned program for the launch of the CZ-2F Chang Zheng-2F launch vehicle (Shenzhou and Tiangong).

The 603 launch pad is used for unmanned orbital launches by the CZ-2C Chang Zheng-2C, CZ-2D Chang Zheng-2D and CZ-4C Chang Zheng-2C launch vehicles.

The first orbital launch took place on April 24, 1970 when the CZ-1 Chang Zheng-1 (CZ1-1) rocket launched the first Chinese satellite, the Dongfanghong-1 (04382 1970-034A).

(Images via Turkish TV and ChinaNews.cn).

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China Launch Again:

According to information acquired by nasaspaceflight.com, the new satellite will probably be located at 110.5 degree East on the geostationary orbit, replacing one of the original Beidou-1 satellites (Beidou-1C) that is approaching ten years in orbit.

The Compass Navigation Satellite System (CNSS) is China’s second-generation satellite navigation system approved by the Chinese government in 2004, and is capable of providing continuous, real-time passive 3D geo-spatial positioning and speed measurement.

The long-term goal is to develop a global navigation satellite network similar to the GPS and GLONASS by 2020 eventually consisting a constellation of 35 vehicles, including 27 MEO (21,500 km orbits) satellites, three IGSO satellites (inclined at 55 degrees) and five GSO satellites.

The system will be dual use, based around a civilian service that will provide an accuracy of 10 meters in the user position, 0.2 m/s on the user velocity and 50 nanoseconds in time accuracy; and the military and authorized user’s service, providing higher accuracies. The first phase of the project will see the coverage of the Chinese territory but in the future the Compass constellation will cover the entire globe.

Developed from the DFH-3B satellite platform, the Compass-G satellites orbit the planet on geostationary orbits and have a lifespan of 12 to 15 years. The satellites transmit signals on the: 1195.14-1219.14MHz, 1256.52-1280.52MHz, 1559.05-1563.15MHz and 1587.69-1591.79MHz, carrier frequencies.

The previous Beidou-2 ‘Compass’ launch took place on September 18th, 2012, when a Chang Zheng-3B/E orbited the Beidou-14 ‘Compass-M5′ (38874 2012-050A) and the Beidou-15 ‘Compass-M6′ (38775 2012-050B) satellites. The previous Compass-G orbited was the Beidou-11 ‘Compass-G5′ launched on February 24th, 2012.

DFH-3B is an updated version of DFH-3 bus, a communications satellite bus whose capability is between high and medium ones. It adopts hexahedral structure, consisting of propulsion, service and communication modules, communication antennas and solar arrays and adopts 3-axis stabilized attitude control.

Its dimensions are 2200mm × 2000mm × 3100mm, and its mass is 3,800 kg with a payload mass of 400 kg to 450 kg. This satellite bus is applicable to communications and navigation satellites and deep space probes through adaptive modification.

This was the eight flight of the CZ-3C Chang Zheng-3C launch vehicle that is primarily used for launching satellite to Geostationary Transfer Orbit (GTO).

This rocket was developed to fill the gap between the CZ-3A Chang Zheng-3A and the CZ-3B Chang Zheng-3B, having a payload capacity of 3,800 kg for GTO. This is a three stage launch vehicle identical to the CZ-3B but only using two strap-on boosters on its first stage.

CZ-3C provides two types of fairing and two kinds of fairing encapsulating process and four different payload interfaces, which is the same as CZ-3B launch vehicle. The various fairing and interface adapter and the suitable launch capacity make CZ-3C a good choice for user to choose the launch service.

The development of the CZ-3C started in February 1999. The rocket has a liftoff mass of 345,000 kg, sporting structure functions to withstand the various internal and external loads on the launch vehicle during transportation, hoisting and flight.

The rocket structure also combines all sub-systems together and is composed of two strap on boosters, first stage, second stage, third stage and payload fairing.

The first two stages as well as the two strap on boosters use hypergolic (N2O4/UDMH) fuel while the third stage uses cryogenic (LOX/LH2) fuel. The total length of the CZ-3C is 54.838 meters, with a diameter of 3.35 meters on the core stage and 3.00 meters on the third stage.

On the first stage, the CZ-3C uses a DaFY6-2 engine with a 2961.6 kN thrust and a specific impulse of 2556.2 Ns/kg. The first stage diameter is 3.35 m and the stage length is 26.972 m.

Each strap on booster is equipped with a DaFY5-1 engine with a 704.4 kN thrust and a specific impulse of 2556.2 Ns/kg. The strap on booster diameter is 2.25 m and the strap on booster length is 15.326 m.

The second stage is equipped with a DaFY20-1 main engine (742 kN / 2922.57 Ns/kg) and four DaFY21-1 vernier engines (11.8 kN / 2910.5 Ns/kg each). The second stage diameter is 3.35 m and the stage length is 9.470 m.

The third stage is equipped with two YF-75 engines developing 78.5 kN each and with a specific impulse of 4312 Ns/kg. The fairing diameter of the CZ-3C is 4.00 meters and has a length of 9.56 meters.

The typical flight sequence of the CZ-3C for a standard GTO mission starts at T-0s with the ignition of the first stage engine and the two strap on boosters. Pitch over maneuver comes at T+10s. The strap on boosters end of ignition takes place at T+127.5s followed by boosters separation at T+129.0s.

First stage shutdown takes place at T+145.2 s, followed at T+146.7s by the first stage separation and ignition of the second stage. Separation of the fairing happens at T+258.7s. Second stage main engine shutdown takes place at T+328.0 s and second stage vernier shutdown occurs five seconds latter.

The separation of the second stage and the first ignition of the third stage take place at T+334.0s. This first ignition will last for 5 minutes and 16.6 seconds, ending at T+650.6s. After the first shutdown of the third stage the vehicle enters on a coast phase at T+654.1s, which will end at T+1323.2s with the second ignition of the third stage. This will end at T+1474.9s, beginning the velocity adjustment maneuver that lasts for 20 seconds.

Spacecraft separation occurs at T+1574.9s.

The first launch of the CZ-3C Chang Zheng-3C launch vehicle took place on April 25, 2008 when it orbited the first TL-1 Tianlian-1 tracking and data relay satellite.

The Xichang Satellite Launch Centre is situated in the Sichuan Province, south-western China and is the country’s launch site for geosynchronous orbital launches.

Equipped with two launch pads (LC2 and LC3), the centre has a dedicated railway and highway lead directly to the launch site. The Command and Control Centre is located seven kilometers south-west of the launch pad, providing flight and safety control during launch rehearsal and launch.

Down range Tracking and Control stations of the launch center are located in Xichang City and Yibin City of Sichuan Province, and Guiyang City of Guizhou Province. Each of them houses tracking and measurement equipment for the powered phase of a launch vehicle flight.

Other facilities on the Xichang Satellite Launch Centre are the Launch Control Centre, propellant fuelling systems, communications systems for launch command, telephone and data communications for users, and support equipment for meteorological monitoring and forecasting.

During 1993-1994 Xichang underwent extensive modernization and expansion, in part due to the requirements of the CZ-3 launcher family and in part to meet commercial customer needs.

The first launch from Xichang took place at 12:25UTC on January 29, 1984, when the CZ-3 Chang Zheng-3 (CZ3-1) launched the Shiyan Weixing (14670 1984-008A) communications satellite into orbit.

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Chinese Launch:

The two satellites were developed by the Shanghai Academy of Spaceflight Technology (SAST) for the Chinese Commission of Science, and the Technology and Industry for National Defence (COSTIND).

The mission will conduct on-orbit experiments for electric propulsion, testing the XIPS-20 xenon gas ion thruster system. It will also test high precision and high stability control systems, high efficient power supply and advanced thermal control technology. The satellites features also instruments for Earth observation.

“Shijian” means “Practice” and this series of satellites have previously been used with a variety of configurations and missions for scientific research and technological experiments.

This was the 169th successful Chinese orbital launch, the 169th launch of a Chang Zheng launch vehicle, the 40th successful orbital launch from Taiyuan, the 14th successful orbital Chinese launch in 2012 and the fourth from Taiyuan this year.

The Chang Zheng-2C launch vehicle:

The Chang Zheng-2C a low Earth orbit launch vehicle derived from DF-5 ICBM. The rocket is a two stage hypergolic launch vehicle with a total length of 35.17 meters, a diameter of 3.35 meters and a total mass of 192,000 kg. The CZ-2C is most frequently used version of Long March Launch Vehicles which had 14 consecutive successful flights till October of 1994. In order to meet the user’s need,

China Academy of Launch Vehicle (CALT) developed a new smart dispenser upper stage, the CZ-2C/SD has been used commercially in the late 1990s and conducted seven consecutive successful launches for Iridium program.

The CZ-2C launch vehicle now comes in two versions, with a basic version comprising of a two-stage CZ-2C for LEO with typical launch capability of 3,366 kg, and a three-stage version known as the CZ-2C/CTS with a typical launch capability of 1,456 kg. The CTS upper stage for CZ-2C is a three-axis stabilized stage capable of delivering one or more satellites.

This launcher provides a flexible mechanical and electrical interfaces and length-adjustable fairing for various satellites.

The first stage is equipped with a cluster of four YF-20A engines (YF-21), with a length of 23.72 meters, a gross mass of 151,000 kg (empty mass of 8,600 kg) and a burn time of 130 seconds.

The second stage is equipped with a cluster of one YF-22A engine with fixed nozzles and a swivelling venire motor consisting of four YF-23 chambers motors (the YF-24), with a length of 8.71 meters, a gross mass of 38,200 kg (empty mass of 3,200 kg) with a burn time of 112 seconds (main engine) and 287 second (vernier).

For this launch the CZ-2C used an SMA upper stage – possibly using the SpaB-140C solid motor – increasing the SSO payload capability to 1,900 kg.

Following the opening 120 seconds of the Chang Zheng-2C/SMA ascent, separation occurs at T+122 seconds with the second stage igniting while still attached to the first stage. Fairing jettisoning is usually set for T+3 minutes and 52 seconds.

The shutdown of the second stage takes place in two phases. First, at T+5 minutes and 1 seconds main engine shutdown takes place while the vernier engines keep firing for an additional 10 minutes, with vernier shutdown taking place at T+10 minutes 13 seconds. Separation of the third stage takes place three seconds after vernier engines shutdown.

Depending on the mission, the vehicle the enters a coast phase until T+48 minutes and 8 seconds when solid rocket motor ignition takes place for a final burn. Spacecraft separation usually occurs at T+50 minutes and 13 seconds..

The Taiyuan Satellite Launch Center:

Situated in the Kelan County on the northwest part of the Shanxi Province, the Taiyuan Satellite Launch Center (TSLC) is also known by the Wuzhai designation. It is used mainly for polar launches (meteorological, Earth resources and scientific satellites).

The center is at a height of 1400-1900m above sea level, and is surrounded by mountains to the east, south and north, with the Yellow River to its west.

The annual average temperature is 4-10 degrees C, with maximum of 28 degrees C in summer and minimum of -39 degrees C in winter.

TSLC is suitable for launching a range of satellites, especially for low earth and sun-synchronous orbit missions.

The center has state-of-the-art facilities for launch vehicle and spacecraft testing, preparation, launch and in-flight tracking and safety control, as well as for orbit predictions.

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VRSS-1 Launch:

After the successful launch of the VENESAT-1 ‘Simon Bolivar’ communications satellite on October 29, 2008, the Chinese and Venezuelan governments signed a new contract for the design, development and construction of a new satellite, the VRSS-1 (Venezuelan Remote Sensing Satellite).

The contact was signed on May 26, 2011, at the capital city of Venezuela, Caracas, in the presence of Ricardo Menendez Prieto, Minister of MPPCTII (Ministerio del Poder Popular para la Ciencia, Tecnologia, Inovacion y Industrias Intermédias) and Mr. Yin Liming, president of China Great Wall Industry Corporation (CGWIC).

According to the contract, CGWIC acted as the prime contractor on the $144.8 million dollars deal - broken down into $67.8 million was for the satellite purchase, $22 million for the launch service, $3 million for the first orbital operations, $16 million for the satellite control system in Venezuela, $22 million for the software, $2 million for the simulation system and $7 millions for the technicians training.

VRSS-1 satellite is based on the CAST 2000 platform developed and manufactured by China Academy of Space Technology (CAST). The ground application system, such as remote sensing data and images receiving stations, were also built by CAST. China Satellite Launch and Tracking & Control General (CLTC) was responsible for launch operation and TT&C services.

VRSS-1 is the first remote sensing satellite system for Venezuela, which will be mainly used for earth resource investigation, environmental protection, disaster monitoring and management, crops yield estimation and city planning etc.

According to Mariano Imber, Executive Director of the Agencia Bolivariana para Actividades Espaciales - ABAE (Bolivarian Agency for Space Activities), the satellite will also be used “for the prospect of the productive systems, like the mining, agricultural and fishing, also being used for urban planification by the Ministry of House care and habitat.”

Talking to journalists on September 21, Mariano Imber added “this space project will also be used for the environmental management, disaster detection and emergencies that can happen in several areas of Venezuela.” Also according to Mariano Imber, the satellite will be capable of real time information about what’s happening in the Venezuelan coast line.

Orbiting at an altitude of 639 km, with three daily passes over Venezuela, the satellite will have a 2.5 meter resolution, taking 350 images each day, according to Jorge Arreaza, Ministry of Science, Technology and Innovation. Miranda will pass over the same area of Venezuela each 51 days.

On board the satellite there are two high-resolution cameras and medium resolution cameras. The high resolution cameras have a spatial resolution of 2.5 meters in panchromatic mode and 10 meter resolution in multispectral mode.

The medium resolution cameras have a spatial resolution of 16 meters. At launch, the Venezuelan Miranda satellite had a 880 kg mass. It will operate for a minimum of five years.

After the initial period of in orbit verification and tests, the satellite will be delivered to Venezuela, who will control it from the Base Aeroespacial Capitán Manuel Ríos (Bamari) - Capitán Manuel Rios Aerospace Base, located on El Sombrero city, Guárico state.

Other elements of the agreement between China and Venezuela is the construction of the ‘Centro de Investigación, Diseño y Ensamblaje de Satélites’ (Research, Development and Integration Center), a small satellites factory at Puerto Cabello, Carabobo state, that will be operated by Venezuelan technicians, and the presence in China of Venezuelan technicians and scientist that are learning and preparing future technological developments in their country.

Future plans are looking for the development of a third satellite, this time built by Venezuela.

Born in Caracas on March 28, 1750, Sebastián Francisco de Miranda Rodríguez, is commonly known as ‘Generalissimo’ Francisco de Miranda.

He was a Venezuelan revolutionary that had planned the independence of the Spanish colonies in South America.

This plan failed, but he is usually regarded as a forerunner of Simón Bolívar, who successfully liberated a vast portion of South America from the Spanish domain.

The CAST 2000 is a compact satellite platform characterized by its high performance, expandability and flexibility.

It is fitted with an S-band TT&C sub-system, X-band data transmission sub-system and 3-axis attitude stabilization, and is able to offer highly precise control, large-range sway and flexible orbit control, highly integrated housekeeping and a highly effective power supply.

This platform has already been successfully applied in several Chinese small satellites, including the Huanjing-A, B satellites, and its performance and reliability have proven to be excellent.

This platform is also capable of operating in low, medium and high orbits, and has a life span of more than three years. The CAST 2000 bus mass is between 200 - 400 kg and the payload capability is between 300 - 600 kg. The satellite has a 3-axis stabilisation and a sway attitude control capability.

In general the platform can be used for Earth observation, technology demonstration, scientific exploration, Earth environmental exploration, meteorological research and application, communications and navigation.

VRSS-1 launch:

After launch and after separation from its launch vehicle, the Miranda satellite will enter in one of the most critical phases of the mission with the opening of its solar panels. With the solar panels open, the satellite will settle on a three months evaluation period where all its systems will be checked in orbit, starting on Day 3 of the mission.

Following the calibration phase, the first images taken by the Francisco Miranda cameras will probably be sent back to Earth on October 3.

The Chang Zheng-2D launch vehicle is a two-stage rocket developed by the Shanghai Academy of Spaceflight Technology. With storable propellants is mainly used to launch a variety of low earth orbit satellites.

The development of CZ-2D begin in February 1990. To meet the demand of SSO satellites, the payload fairing of 3350mm in diameter and attitude control engine for second stage have been successfully upgraded since 2002. This launcher is mainly used for launching LEO and SSO satellites.

The 41.056m tall CZ-2D can launch a 1,300 kg payload into a 645 km SSO. Its first, second stages and payload fairing are all 3.35m in diameter, while the entire first stage is the same as the Chang Zheng-4.

The second stage is based on CZ-4 second stage with an improved equipment bay. Lift-off mass is 232,250 kg, total length 41.056 meters, 3.35 meters in diameter and fairing length 6.983 meters.

The first stage is equipped with a YF-21C engine capable of a ground thrust of 2,961.6 kN and a ground specific impulse of 2,550 m/s. It has a burn time is 170 seconds and consumes 183,200 kg of N2O4 / UDMH.

The second stage consumes 45,550 kg of N2O4 / UDMH via a YF-24C cluster engine with a main engine vacuum thrust of 742.04 kN and a vernier engine with a vacuum thrust of 47.1 kN. It can use two types of fairings, depending of the cargo.

The first launch of the CZ-2D was on August 9, 1992 from the Jiuquan Satellite Launch Center, orbiting the Fanhui Shei Weixing FSW-2-1 (22072 1992-051A) recoverable satellite.

This launch was the 168th Chinese successful orbital launch and the 168th launch of a Chang Zheng launch vehicle. It was also the 54th orbital launch from the Jiuquan Satellite Launch Center, the third orbital launch from Jiuquan this year and the 13th Chinese orbital launch in 2012.

The Jiuquan Satellite Launch Center, in Ejin-Banner - a county in Alashan League of the Inner Mongolia Autonomous Region – was the first Chinese satellite launch center and is also known as the Shuang Cheng Tze launch center.

The site includes a Technical Centre, two Launch Complexes, Mission Command and Control Centre, Launch Control Centre, propellant fuelling systems, tracking and communication systems, gas supply systems, weather forecast systems, and logistic support systems.

Jiuquan was originally used to launch scientific and recoverable satellites into medium or low earth orbits at high inclinations. It is also the place from where all the Chinese manned missions are launched.

Presently, only the LC-43 launch complex, also known by South Launch Site (SLS) is in use. This launch complex is equipped with two launch pads: 921 and 603. Launch pad 921 is used for the manned program for the launch of the Chang Zheng-2F launch vehicle (Shenzhou and Tiangong). The 603 launch pad is used for unmanned orbital launches by the Chang Zheng-2C, Chang Zheng-2D and Chang Zheng-2C launch vehicles.

The first orbital launch took place on April 24, 1970 when the CZ-1 Chang Zheng-1 (CZ1-1) rocket launched the first Chinese satellite, the Dongfanghong-1 (04382 1970-034A).

(Images via Venezuelan State TV, ChinaNews.Cn and Wikipedia).

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Chinese Launch:

Developed from the DFH-3B satellite platform, the Compass-M satellites are deployed in 21500~24100 km, 55 degrees inclination intermediate circular orbits.

The first Compass-M (31115 2007-011A) satellite was launched at 2011UTC on April 13th, 2007 by the Chang Zheng-3A (Y13) from the LC3 launch complex of the Xichang Satellite Launch Center.

China has developed two models for Compass-M satellites. The two satellites that where launched today are based on DFH-3B bus and are equipped with an apogee propulsion system for final orbit insertion.

The second model is not equipped with an apogee propulsion system and is completely different from DFH-3 bus. Still under development, this model will not fly until the second construction phase of the Compass constellation starts.

The Compass Navigation Satellite System (CNSS) is China’s second-generation satellite navigation system approved by the Chinese government in 2004, and is capable of providing continuous, real-time passive 3D geo-spatial positioning and speed measurement.

The system is used initially to provide high-accuracy positioning services for users in China and its neighboring regions, covering an area of about 120 degrees longitude in the Northern Hemisphere using five Compass-G, 5 Compass-IGSO and four Compass-M satellites.

The long-term goal is to develop a global navigation satellite network similar to the GPS and GLONASS by 2020, eventually consisting a constellation of 35 vehicles, including 27 MEO (21,500 km orbits) satellites, 3 IGSO satellites (inclined at 55 degrees) and five GSO satellites.

The system will consist of two types of services: a civilian service that will give an accuracy of 10 meters in the user position, 0.2 m/s on the user velocity and 10 nanoseconds in time accuracy; and the military and authorized user’s service, providing higher accuracies.

The first phase of the project will see the coverage of the Chinese territory but in the future the Compass constellation will cover the entire globe. The satellites transmit signals on the: 1195.14-1219.14MHz, 1256.52-1280.52MHz, 1559.05-1563.15MHz and 1587.69-1591.79MHz, carrier frequencies.

The previous double Beidou-2 ‘Compass’ launch took place on April 29th, 2011, when the Chang Zheng-3B/E (Y14) orbited the ‘Compass-M3′ (38250 2012-018A) and ‘Compass-M4′ (38251 2012-018B) satellites.

DFH-3B is an updated version of DFH-3 bus, a communications satellite bus whose capability is between high and medium ones. It adopts hexahedral structure, consisting of propulsion, service and communication modules, communication antennas and solar arrays and adopts 3-axis stabilized attitude control. Its dimensions are 2200mm × 2000mm × 3100mm, and its mass is 3,800 kg with a payload mass of 400 kg to 450 kg.

This satellite bus is applicable to communications and navigation satellites and deep space probes through adaptive modification.

China’s 12th successful orbital launch in 2012 was also the 167th successful Chinese orbital launch, the 167th launch of a Chang Zheng launch vehicle, the 7th launch from Xichang in 2012 and the 75nd successful orbital launch from Xichang.

Launch vehicle:

This was the second dual launch for the CZ-3B Chang Zheng-3B launch vehicle. For this launch, CZ-3B was using the 3700Z fairing. This fairing has an external diameter of 3,700 mm, a total height of 10,796 mm, and is used for dual launch with the LM-3B launch vehicle with the satellite encapsulated in the BS3.

The satellite is mated to the Payload Adapter (PLA) and encapsulated in the fairing, prior to being shipped to the launch pad, completing the assembly when it is mated to the launch vehicle.

This fairing can be used with the 1194 and 1194A Payload Adapter interfaces. For this fairing – like others used on the CZ-3B – the longitudinal release mechanism uses notched bolts, explosive cord, expanding hose, and two explosive bolts. All these parts jointly perform the release functions.

Developed from the Chang Zheng-3A, the Chang Zheng-3B is the most powerful launch vehicle on the Chinese space launch fleet.

The CZ-3B features enlarged launch propellant tanks, better computer systems, a larger 4.2 meter diameter payload fairing and the addition of four strap-on boosters in the core stage that give an additional help in the first phase of the launch.

The rocket is capable of launching a 11,200 kg satellite to a low Earth orbit or a 5,100 kg cargo to a geosynchronous transfer orbit. The rocket has a total length of 54.84 meters and a core diameter of 3.35 meters.

Each of the four boosters has a 15.326 meter length with a 2.25 meter diameter, consuming 37,700 kg of N2O4 / UDMH. Equipped with a YF-25 engine capable of a ground thrust of 740.4 kN and a ground specific impulse of 2,556.2 Ns/kg.

The first stage has a 23.272 meter length with a 3.35 meter diameter, consuming 171,800 kg of N2O4 / UDMH. Equipped with a YF-21C engine capable of a ground thrust of 2,961.6 kN and a ground specific impulse of 2,556.5 Ns/kg.

The second stage has a 19.92 meter length with a 3.35 meter diameter, consuming 49,400 kg of N2O4 / UDMH. Equipped with a YF-24E cluster engine with a main engine capable of a vacuum thrust of 742 kN and a vernier engine with a vacuum thrust of 47.1 kN (specific impulses of 2,922.6 Ns/kg and 2,910.5 Ns/kg, respectively).

The third stage has a 12.375 meter length with a 3.0 meter diameter, consuming 18,200 kg of LH2 / LOX. Equipped with a YF-75 engine capable of a vacuum thrust of 167.17 kN and a specific impulse in vacuum of 4,295 Ns/kg.

In recent years, the CZ-3B/E (Enhanced Version) launch vehicle was developed on the basis of CZ-3B, increasing the GTO capacity up to 5,500kg. The CZ-3B/E has nearly the same configurations with CZ-3B except its enlarged core stage and boosters.

On May 14, 2007, the first flight of CZ-3B/E was performed successfully, accurately sending the NigcomSat-1 into pre-determined orbit. With the GTO launch capability of 5,500kg, CZ-3B/E is dedicated for launching heavy GEO communications satellite.

The CZ-3B and CZ-3B/E launch vehicles are comprised of the vehicle structure, propulsion system, control system, measurement system (telemetry system and tracking & range safety system), propellant management and reaction control system, propellant utilization system, separation system and auxiliary system, etc.

Click here for other Chinese News Articles: http://www.nasaspaceflight.com/news/chinese/

The third stage includes the payload adapter, the vehicle equipment bay (VEB) and the cryogenic propellant tanks and engines. The payload adapter mates the satellite to CZ-3B and bears the mechanical loads. This cargo adapter can be one of the international standard interfaces designated as 937B, 1194 or 1194A.

The CZ-3B/E is now the standard version used for China.

The Xichang Satellite Launch Centre is situated in the Sichuan Province, south-western China and is the country’s launch site for geosynchronous orbital launches.

Equipped with two launch pads (LC2 and LC3), the centre has a dedicated railway and highway lead directly to the launch site.

The Command and Control Centre is located seven kilometers south-west of the launch pad, providing flight and safety control during launch rehearsal and launch. The CZ-3B launch pad is located at 28.25 deg. N – 102.02 deg. E and at an elevation of 1,825 meters.

Other facilities on the Xichang Satellite Launch Centre are the Launch Control Centre, propellant fuelling systems, communications systems for launch command, telephone and data communications for users, and support equipment for meteorological monitoring and forecasting.

The first launch from Xichang took place at 12:25UTC on January 29, 1984, when the CZ-3 Chang Zheng-3 (CZ3-1) was launched the Shiyan Weixing (14670 1984-008A) communications satellite into orbit.

(Images via ChinaNews.cn. Sina.cn

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Chinese Launch:

The Chinese tracking and data relay satellite was developed by the China Academy of Space Technology (CAST). It is similar to the American Tracking and Data Relay Satellite System (TDRSS) in concept.

The system is designed to support near-real-time communications between orbiting spacecraft and the ground control, and will complement the ground-based space tracking and telemetry stations and ships to support future space projects.

Like its predecessors, the Tianlian-1 (3) satellite is based on the DFH-3 bus. The DFH-3 (Dongfanghong-3) platform is a medium-capacity telecommunications satellite platform designed and developed by CAST (Chinese Academy of Space Technology).

The spacecraft can carry multiple telecommunications payloads for providing many kinds of services, such as fixed communication, international satellite communication, national and regional communication, wideband data communication, mobile communication and direct broadcast; military communication, spacecraft tracking and data relay, etc.

The platform comprises six subsystems: control, power, propulsion, measurement & control, structure and thermal control subsystem. The platform configuration features module subdivision, which includes communication module, propulsion module, service module and solar array.

The platform adopts three-axis stabilized attitude control mode, having solar array output power of 1.7 kw by the end of its design lifetime of 8 years. Its mass is 2,100kg with payload capacity 220kg.

The DFH-3 satellite platform has been successfully applied in DFH-3 satellite, Beidou navigation test satellite, and other satellites, all of which are currently operating normally.

During numerous flight missions, the maturity and reliability of the DFH-3 platform has been proved. Moreover, it has strong expansion capacity and can be upgraded to some space exploration missions, such as meteorological satellite, lunar resource satellite services.

At present, Tianlian-1 (1) is positioned at 77 degrees East, after it was launched on April 25, 2008, by the first Chang Zheng-3C launch vehicle.

Tianlian-1 (2) is positioned at 176.77 degrees East, after it was launched on July 11, 2011, by the Chang Zheng-3C (Y8) launch vehicle. With the Tianlian-1 (3), China has full global coverage for its tracking and data relay system. A second generation TL-2 Tianlian-2 is being developed by CAST.

This was the ninth flight of the Chang Zheng-3C launch vehicle. This rocket was developed to fill the gap between the Chang Zheng-3A and the Chang Zheng-3B, having a payload capacity of 3,800 kg for GTO. This is a three stage launch vehicle identical to the CZ-3B but only using two strap-on boosters on its first stage.

CZ-3C provides two types of fairing and two kinds of fairing encapsulating process and four different payload interfaces, which is the same as LM-3B launch vehicle.

The various fairing and interface adapter and the suitable launch capacity make LM-3C a good choice for user to select the launch service.

The development of the CZ-3C started in February 1999. The rocket has a liftoff mass of 345,000 kg. The rocket structure functions to withstand the various internal and external loads on the launch vehicle during transportation, hoisting and flight.

The rocket structure also combines all sub-systems together and is composed of boosters, first stage, second stage, third stage and payload fairing. The first two stages as well as the two strap on boosters use hypergolic (N2O4/UDMH) fuel while the third stage uses cryogenic (LOX/LH2) fuel. The total length of the CZ-3A is 54.838 meters, with a diameter of 3.35 meters on the core stage and 3.00 meters on the third stage.

The first launch of the CZ-3C Chang Zheng-3C launch vehicle took place on April 25, 2008 when it orbited the first TL-1 Tian Lian-1 tracking and data relay satellite.

Wednesday’s launch was the 166th successful orbital mission for China, the 74th successful orbital launch from Xichang, the 11th successful orbital launch for China in 2012 and the 6th successful orbital launch from Xichang this year.

The Xichang Satellite Launch Centre is situated in the Sichuan Province, south-western China and is the country’s launch site for geosynchronous orbital launches.

Equipped with two launch pads (LC2 and LC3), the centre has a dedicated railway and highway lead directly to the launch site. The Command and Control Centre is located seven kilometers south-west of the launch pad, providing flight and safety control during launch rehearsal and launch.

Down range Tracking and Control stations of the launch center are located in Xichang City and Yibin City of Sichuan Province, and Guiyang City of Guizhou Province. Each of them houses tracking and measurement equipment for the powered phase of a launch vehicle flight.

Other facilities on the Xichang Satellite Launch Centre are the Launch Control Centre, propellant fuelling systems, communications systems for launch command, telephone and data communications for users, and support equipment for meteorological monitoring and forecasting.

During 1993-1994 Xichang underwent extensive modernization and expansion, in part due to the requirements of the CZ-3 launcher family and in part to meet commercial customer needs.

The first launch from Xichang took place at 1225UTC on January 29, 1984, when the Chang Zheng-3 (CZ3-1) was launched the Shiyan Weixing (14670 1984-008A) communications satellite into orbit.

(Images via ChinaNews.cn and CCTV).

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Shenzhou-9 Return:

The mission achieved all of its main goals, including the milestone of an automated crew docking, followed by a manual docking midway through the mission.

The crew, consisting of Jing Haipeng, Liu Wang and Liu Yang, enjoyed a normal ride to orbit via their Long March 2F/G launch vehicle, following lift-off from the Jiuquan Satellite Launch Center, prior to docking with unmanned space module Tiangong-1 – a vehicle that was launched back on September 29, 2011.

After the June 18 docking, the crew adapted to the work aboard Tiangong-1, before carrying out their routine medical examinations during the mission, including measuring blood pressure, body temperature and body weight – communicated to medical support specialist on the ground.

Other space experiments included microbiological testes and evaluation of the human biological rhythms, as well as physiological studies and experiments in the microgravity environment.

On June 22, the taikonauts manually changed the attitude control for the joined spacecraft – a first for the Chinese – five days after the historical docking in orbit. The control system on Tiangong-1 was turned off by Liu Wang, prior to testing three different kinds of positioning, with Shenzhou-9 taking charge of the flight.

This was followed by a mission milestone, as the Shenzhou-9 undocked for the manual docking test.

For this event on June 23, the Shenzhou-9 backed to a distance of 400 meters, prior to closing back in to 140 meters, at which point the two vehicles maintained their distance.

The ground then gave their approval for the manual approach, controlled by Liu Wang, from the 140 meter point, prior to a short hold point at 30 meters. Closing in at 0.4 meters per second, the successful completion of the manual docking took place at around 4:50 UTC.

Shenzhou is based on the Russian Soyuz-TM spacecraft and can carry up to three astronauts inside its Re-Entry Module. Like on the Soyuz manned spacecraft, on re-entry, the orbital and service modules are separated and discarded, allowing the re-entry module makes its descent through the atmosphere.

The total mass of the spacecraft was 8,082 kg, with a length of 9.25 meters, diameter of 2.80 meters and a 17 meter span.

The Orbital Module has a length of 2.80 meters, a mass of 1,500 kg and a diameter of 2.25 meters, equipped with two solar panels for power generation (0.5 W) and each panel is 2.0 meters by 3.4 meters. This module sports a propulsion system comprised of 16 small thrusters, in four groups.

The Re-entry Module has a length of 2.50 meters, a mass of 3,240 kg and a diameter of 2.52 meters. This module is equipped with a heat shield with a mass of 450 kg.

The Service Module has a length of 3.05 meters, a mass of 3.000 kg and a maximum diameter of 2.80 meters. Is equipped with two solar panels for power generation (1.5 W) and each panel is 2.0 meters by 7.0 meters.

This module was equipped with the Shenzhou main propulsion system that consists of four high-thrust main engines and 24 smaller-thrust control engines, as well as four 230-litre propellant tanks containing a total of 1,000kg N2O4/MMH liquid propellant.

The four main engines (2.5kN) are located at the base of the spacecraft’s Service Module. The spacecraft also used eight (in four pairs) 150N pitch and yaw thrust vectors, eight (in four pairs) 5N pitch and yaw thrust vectors and eight (in four pairs) 5N roll / translation thrust vectors.

Following a nominal return to Earth – at the primary landing site – the Shenzhou-9 touched down in daylight in what appeared to be a rather bumpy landing. However, the three member crew were all reported to be in good health, after landing crewed arrived at the spacecraft.

The next mission, Shenzhou-10, is expected to involve a three week long docked mission with Tiangong-1.

(Images via CCTV and ChinaNews.cn)

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Chinese Docking:

The approach and docking was very similar to the one seen during Shenzhou-8 last year, an unmanned event that was China’s debut attempt to join the handful of other nations that have the ability to rendezvous and dock vehicles in space.

Shenzhou-8, was launched unmanned on October 31, 2011, via the Long March 2F (Chang Zheng-2F). The main objective of the mission was the docking with the unmanned space module Tiangong-1 that took place at 17:28 UTC on November 2.

The new orbiting complex flew for almost 11 days, with the controllers performing various tests to the complex systems, before first separation occurred at 11:24 UTC on November 14. A second docking took place at 11:28 UTC.

On November 16, at 10:30 UTC, the two vehicles separated for the final time and Shenzhou-8 begin its return to Earth, with landing taking place at 11:32 UTC.

For Shenzhou-9 – which launched on Saturday via a Long March 2F/G (Chang Zheng-2F/G) – the opening phase of the final stage of rendezvous took place at a distance of 52 km from the TG-1 space module, allowing for SG-9 to approaching to within 20 km.

In a similar scenario to the recent arrival of SpaceX’s Dragon to the International Space Station (ISS), several hold points – at 5 km, 400 meters and 140 meters – were required, allowing for a Go/No Go for continuing final approach, as numerous systems checks were conducted.

During this key stage of the mission, Shenzhou-9 held the role as the “active vehicle”, while the Tiangong-1 was placed into the role of the “passive vehicle”.

After soft docking, locks and bolts were secured between the two vehicles, lasting around 15 minutes. This was followed by the control center adjusting the cabin environment, such as temperature, pressure, in accordance with the conditions for crewed flight.

Crew ingress into Tiangong-1 was completed around three hours after docking.

Living in orbit:

During the docked phase, two of the taikonauts will sleep in the module, while the third will sleep on the Shenzhou-9.

Tiangong-1 is equipped with various systems and equipments for the crew, such as exercise equipment and a medical laboratory, in order to evaluate the astronaut’s health during their relatively long-term presence in space for the Chinese. The module also has waste recycling equipment, medical health monitoring equipment, male and female astronauts clothing, and fire extinguishers.

The TianGong-1 spacecraft is expected to stay in orbit for two years and rendezvous and dock with three different spaceships, the latter during the future Shenzhou-10 mission. The taikonauts will stay on board for a maximum of two weeks, a duration expected for the Shenzhou-10 mission.

The 3.35 meter experimental module is composed of a enclosed front cone shaped section, cylindrical section and rear cone shaped section. On the front end of the experiment module are the docking mechanism and the measuring and communication equipment, which are used to support the rendezvous and docking with vehicles.

The experimental module is where the taikonauts will live and work, with 15 cubic meters of space to move around in. This section is also equipped with two sleeping sections with adjustable lighting systems, exercise equipment, entertainment systems, visual communications devices and control systems.

The 2.8 meter resource module will supply the power necessary for flight – containing two solar panels, propellent tanks, and other systems.

In the future, the TianGong will be upgraded to a cargo vehicle to service the Mir-class station, with its core module due to launch in 2020. However, before that, China plans to launch the TG-2 TianGong-2 in 2014 (to develop the necessary technologies for water and oxygen regeneration necessary for short-term stay in orbit and to carry out some scientific experiments) and TG-3 TianGong-3 in 2015/2016.

TG-3 will likely be equipped with two docking ports, allowing a permanent residency of the module. TG-3 mission will involve the development of the technologies necessary for medium to long-term orbital stays and to carry out more sophisticated scientific researches and experiments.

At launch, Shenzhou-9 carried 300 kg of cargo on board, including water, food rations and experiments to be carried out during the mission.

The Chinese – as would be expected – will be focusing on protecting the crew’s health. The measures are designed to combat the influence of the gravity-free environment of spaceflight and to ensure the taikonaut’s health remains as expected.

While in orbit, medical examinations and protection measures will be conducted, including an on-orbit examination of the astronauts’ hearts, lungs and biochemistry conditions.

Equipment, such as a bicycle ergometer, chest developer and neuromuscular electrical stimulation have been prepared on board Tiangong-1 to protect the astronauts against the effects of weightlessness and maintain their cardiac and muscular functions.

Liu Yang will receive a special focus on her medical examinations and exercises, given this is the first time a Chinese woman has been in space.

The Chinese noted that they have three major mission goals for the crew, the first being the health monitoring of the taikonauts that mainly includes astronaut’s nutrition and metabolism, moods, and biorhythm changes in orbit.

Secondly, the crew will make research on the physiological effects mechanism of weightlessness and the countermeasures, which include the impact study on the functions of astronaut’s cardiovascular, vestibule and brain in the orbiting flight. They will also study bone loss in space.

Finally, the taikonauts will conduct research on environmental medicine and the astronaut’s operational capability in space.

(Images via CCTV and ChinaNews.cn).

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Chinese Mission:

The 13 day flight of Shenzhou-9 is centered around the expected docking with unmanned space module Tiangong-1 that was launched on September 29, 2011.

This module is the rudiment of China’s space station and is an experimental space laboratory, launched with the objective to carry out the rendezvous and docking test with the Shenzhou-8, that was launched in November, 2011. The Chinese see this as a key step towards gaining the experience for the construction, management and operation of a space station.

After the launch, Shenzhou-9 will be initially inserted into a parking orbit, before raising its orbital parameters to a near circular orbit with an altitude of 330 km. The spacecraft will take two days to get near Tiangong-1.

Providing everything goes according to plan, the docking is expected to take place on June 18.

Tiangong-1 and Shenzhou-9 will stay docked for a period of 10 days. However, during this time, a second docking manoeuvre will take place. After another period of docking, Shenzhou-9 will return to Earth.

Preparations For launch:

On October 31, 2011 Wu Ping, spokeswoman from the Chinese space program, said the launch of Shenzhou-9 was going to be conducted by 2012. This was followed by comments from Chen Shanguang, director of the Astronaut Center of China, who added China was assessing both male and female astronauts, “to verify if humans could live in space as there was huge differences between man and woman in spite of their common generalities”.

The first female Chinese taikonauts were selected by the space program on March 10, 2010.

The launch was originally scheduled for March/April 2012, but on December 2011 a Chinese internet source revealed that the mission would take place in June 2012. at the same time that the official Xinhua news agency revealed that the Shenzhou-10 mission would also take place in 2012, citing the China National Space Administration.

With the mission preparations proceeding smoothly, China revealed that a group of nine taikonauts, including the two women, had been selected for the flight. Apart from the general training for a spaceflight, special attention was given to the simulations of the rendezvous control and docking elements of the planned mission.

On March 3, it was revealed that the launch vehicle for Shenzhou-9 had passed its testing and that was ready to be shipped to the launch site. According to Liang Xiaohong, “the rocket was designed with a higher degree of reliability and equipped with more advanced positioning software to ensure a more precise entry into orbit.”

The Shenzhou-9 spacecraft arrived at the Jiuquan Satellite Launch Center on April 9, followed one month later by the Chang Zheng-2F/G (Y9) launch vehicle, to begin the final processing and assembly before launch. This took place from May 11 to June 6.

After the launch of Tiangong-1, the Beijing Special Engineering Design and Research Institute, the main designer of the launch system used at the Jiuquan Satellite Launch Center, renovated and upgraded the equipment at the launch site. The new equipment and technologies dramatically increased the reliability of satellite launches and greatly shortened the launch time preparation.

The system for voice communications between the spacecraft and the ground was redesigned for this mission – and is more advanced than that used by Shenzhou-7. These improvements include a wireless signal transmission system, using optical wiring, has improved the quality of voice and image transmission.

At the end of May, the Tiangong-1 module executed the lowering of its orbit, in order to prepare for the mid-June launch window.

The processing and assembly of the three modules of Shenzhou-9 – and the preparations on its docking system – was without problem, allowing for technicians started the fuelling process of the spacecraft on May 28.

With the fuelling process completed, all the processing work was completed on June 3, allowing for the Shenzhou-9 to be transported to the launch vehicle integration building and was hoisted to the top of the launcher on June 7. The next day all the preparatory tasks were completed, and the capsule and the launch vehicle were prepared for transportation to the 921 launch pad, with this process taking place on June 9.

After arriving to the launch pad, Chinese technicians started a series of functional tests on the spacecraft, including joint tests with the selected taikonauts, the capsule, the launcher and the ground systems.

On June 12 the Shenzhou-9 completed its first full-system drill. Starting at 02:07 UTC, the countdown clock at T-4h 30m mark and all relevant systems, including the taikonauts, spacecraft, launcher, launch center and surveillance, control and communications systems, were tested, with all the tasks being coordinated by the launch control center. The drill went without a hitch, paving the way for the final pre-launch phase of launch preparations.

The 72h countdown started on June 13, followed by the final fuelling drill of the Chang Zheng-2F/G launch vehicle.

The Crew:

The selected taikonauts for the mission arrived at Jiuquan on June 8. A photograph published on June 9 allowed the identification of the six person group as Nie Haisheng, Zhang Xiaoguan, Wang Yaping, Jing Haipen, Liu Wang and Liu Yang. At this time there was no information about the crew that had been selected for the flight, but rumours pointed to the Nie Haisheng, Zhang Xiaoguan, Wang Yaping crew.

However, a few days later, the name of Liu Yang was referred to as the first Chinese women to fly in space.

The international space community have tried to determine the composition of the main crew of Shenzhou-9 for several weeks. After many speculations and deductions, China finally revealed the names of the prime crew as Jing Haipeng, Liu Wang and Liu Yang. with the back up crew composed of Nie Haisheng, Zhang Xiaoguan and Wang Yaping. Haipeng, Wang and Liu were internally selected as the prime crew in March 2012.

Born on October 24, 1966 in Yuncheng, Shanxi province, Jing Haipeng is the Commander of Shenzhou-9. He is a fighter pilot in the People’s Liberation Army Air Force, selected as a taikonaut in January 1998. Jing Haipeng first flight took place on Shenzhou-7, serving as Operator. Senior Colonel Jing Haipeng is married and has one child. He joined the PLA in 1985 and has more than 1,200 hours of flying time.

Liu Wang was born on 1970 in the Shanxi province and this is his first flight. He was selected as a taikonaut in January 1998 after joining the PLA in 1988. He has more than 1,000 hours of flying time and is now a Senior Colonel on the Air Force.

33 year old Liu Yang was born in October 1978 in Zhengzhou, Henan province. She was a pilot in the People’s Liberation Army Air Force and she’s the first of the second batch of taikonauts that were selected in March, 2010 to fly in space.

Liu Yang enlisted in the PLA in 1997 and she is a veteran pilot with more than 1,680 hours of flying experience, and also being a deputy head of the flight unit, before being recruited to the Chinese space program. She now is a Major in the Air Force.

Back-up Commander Nie Haisheng was born on September 8, 1964 in Zaoyang, Hubei province. He was selected to the taikonaut detachment in January 1998 and made is first spaceflight on Shenzhou-6 in October, 2005. He is a Lieutenant Colonel in the PLAAF, married, and has a daughter.

Zhang Xiaoguan was born in 1968 in Liaoning province. He was a squadron commander in the PLAAF before being selected to taikonaut team in 1998. He accumulated more than 1,000 hours of flight time.

Wang Yaping was born on January 27, 1980 in Yantai, Shandong province. She was a cargo plane pilot before being selected to the taikonaut team in March 2010.

The Shenzhou-9 Spacecraft:

Considerable modifications – 600 in total, according to Chinese media – have been made to Shenzhou-9 for the manned docking mission, relating to automatic and manual rendezvous, docking capabilities, and to enhance the performance, safety and reliability.

The Shenzhou spacecraft was designed and developed by many of organisations participating on the Chinese human space program.

The primary contractor was China Academy of Space Technology (CAST), responsible for the overall concept of the vehicle. Qi Faren was appointed the chief designer of the Shenzhou design team in 1992, later succeeded in 2004 by Zhang Bai-Nan. Qi Faren was also the chief designer of Dongfanghong, China first satellite.

CAST was responsible for the design of the Orbital and Re-entry Module, and the Shanghai Academy of Spaceflight Technology (SAST) was responsible the design of Service Module, as well as the electrical power system, propulsion system, and telemetry, tracking and communications systems.

The development of onboard applications were made by the China Academy of Science. The development of the environment control and life support system was tasked to the Institute of Space Medicine Engineering, while the Academy of Aerospace Solid Propulsion Technology was responsible for the launch escape system.

Shenzhou is based on the Russian Soyuz-TM spacecraft and can carry up to three astronauts inside its Re-Entry Module. This module provides a fully pressurised and habitable living space for all phases of the mission, but the taikonauts can also use the Orbital Module that provides additional habitable space for conducting scientific experiments.

This module is equipped with navigation, communications, flight control, thermal control, batteries, oxygen tanks, and propulsions systems.

Total mass of the spacecraft is 8,082 kg, with a length of 9.25 meters, diameter of 2.80 meters and a 17 meter span.

The Orbital Module has a length of 2.80 meters, a mass of 1,500 kg and a diameter of 2.25 meters. Is equipped with two solar panels for power generation (0.5 W) and each panel is 2.0 meters by 3.4 meters. This module is equipped with a propulsion system comprised of 16 small thrusters, in four groups.

The Re-entry Module has a length of 2.50 meters, a mass of 3,240 kg and a diameter of 2.52 meters. This module is equipped with a heat shield with a mass of 450 kg.

The Service Module has a length of 3.05 meters, a mass of 3.000 kg and a maximum diameter of 2.80 meters. Is equipped with two solar panels for power generation (1.5 W) and each panel is 2.0 meters by 7.0 meters. This module is equipped with the Shenzhou main propulsion system that consists of four high-thrust main engines and 24 smaller-thrust control engines, as well as four 230-litre propellant tanks containing a total of 1,000kg N2O4/MMH liquid propellant.

The four main engines (2.5kN) are located at the base of the spacecraft’s Service Module. The spacecraft also has eight (in four pairs) 150N pitch and yaw thrust vectors, eight (in four pairs) 5N pitch and yaw thrust vectors and eight (in four pairs) 5N roll / translation thrust vectors.

Like on Soyuz manned spacecraft, on re-entry, the orbital and service modules are separated and discarded, and then the re-entry module makes a ballistic descent through the atmosphere. Primary landing target is located in Inner Mongolia.

The launch vehicle:

Shenzhou-9 will be launched by the Long March 2F/G (Chang Zheng-2F/G), the launch vehicle usually used for manned Shenzhou program.

This launch vehicle, developed by the China Academy of Launch Vehicle Technology under the China Aerospace Science and Technology Corporation, is different from the original ‘Shenjian’ (Divine Arrow) version that was developed from the Chang Zheng-2E launch vehicle, which in turn was based on the proven flight technology of the CZ-2C Chang Zheng-2C.

For Articles on every Chinese launch over recent years: http://www.nasaspaceflight.com/news/chinese/

Conceptual design of the CZ-2E launch vehicle began in 1986, and the vehicle was launched on the launch services market, following a successful test flight in July 1990.

To meet the requirements of the rendezvous and docking mission, the Chang Zheng-2F endured nearly 170 technical modifications and uses five newly developed technologies.

Other characteristics include its capability of a more precise orbit insertion accuracy. This is possible via the introduction of improved navigation systems and complex guidance system, featuring real-time input to the orbital parameters, using GPS data to achieve double redundancy. Also, more propellant is loaded on the boosters, thus increasing the burn time.

Like the CZ-2F, the CZ-2F/G Chang Zheng-2F/G is a two stage launch vehicle that uses four strap-on boosters during the first stage phase. Overall length of the CZ-2F/G is 58.0 meters (including the launch escape system) with a 3.35 meter core stage and a maximum diameter of 8.45 meters. At launch it has a 497,000 kg mass, capable of launching 8,600 kg cargo into a low Earth orbit.

For the CZ-2F launch vehicle, the LB-40 strap-on boosters have a length of 15.326 meters, diameter of 2.25 meters, a gross mass of 40,750 kg and an empty mass of 3,000 kg. Each booster is equipped with a fixed nozzle YF-20B engine that consumes UDMH/N2O4 developing 740.4 kN of sea lever thrust. Burn time is 127.26 seconds.

The L-180 first stage has a length of 28.465 meters, diameter of 3.35 meters, a gross mass of 198,830 kg and an empty mass of 12,550 kg. It is equipped with a YF-21B engine pack that consists of four YF-20B engines that consumes UDMH/N2O4 developing 2,961.6 kN of sea lever thrust. Its burn time is 160.00 seconds.

The L-90 second stage has a length of 14.223 meters, diameter of 3.35 meters, a gross mass of 91,414 kg and an empty mass of 4,955 kg. It is equipped with a YF-24B engine pack that consists of one fixed nozzle YF-22B main motor with a swivelling vernier four YF-23B engines. The engines consume UDMH/N2O4 developing 738.4 kN (main engine) and 47.07 kN (vernier) of vacuum thrust. Total burn time is 414.68 seconds (301.18 seconds burn time for the main engine).

This launch was the 149th Chinese orbital launch, the 149th launch of the Chang Zheng launch vehicle family, the 50th successful orbital launch from the Jiuquan Satellite launch Center, and the 12th successful orbital launch from China this year.

The Launch Site:

The Jiuquan Satellite Launch Center, also known as the Shuang Cheng Tze launch center, was the first Chinese satellite launch center.

The site includes a Technical Centre, two Launch Complexes, Mission Command and Control Centre, Launch Control Centre, propellant fuelling systems, tracking and communication systems, gas supply systems, weather forecast systems, and logistic support systems. Jiuquan was originally used to launch scientific and recoverable satellites into medium or low earth orbits at high inclinations.

The manned program uses the South Launch Site Pad 921. This was built in the late 1990s and later added with the 603 Launch Platform for unmanned satellite launches. Apart of the launch pads, the launch complex has a technical centre where take place the preparations of the launch vehicle and spacecraft.

The technical center is composed of the launch vehicle processing and vertical assembly building, spacecraft processing buildings, solid rocket motor processing building, buildings for liquid-propellant storage and processing and the launch control center.

For the TianGong-1 launch, the launch site was equipped with an updated computer center, command monitoring systems and increased ability to adapt to changes in mission conditions, as well as the resources to handle both the launch and command duties. An integrated simulation training system for space launching has also been developed for the docking mission.

Engineers also conducted a two-month comprehensive technical check on equipment at the launch site from March to May. The safety and reliability of all the instruments have been significantly improved.

Orbital launches from Jiuquan are supervised from the Mission Command and Control Centre that is located in the Dongfeng Space City, 60 km southwest of the satellite launch center.

The umbilical tower is 75 meter-high steel structure that is designed to service the launch vehicle and spacecraft with electricity, gases and fluids, also providing facilities for pre-launch checkouts and crew entrance/emergency exit.

The tower is equipped with a loading crane, a cargo elevator, and an explosion-proof elevator for the mission crew. In time of emergency, a canvas slide escaping system is available for taikonauts to exit the launch pad. Power supply and other support equipment are located inside an underground room underneath the umbilical tower. The umbilical tower comprises a fixed structure and a pair of six-floor rotating platforms.

Once the launch vehicle arrives at the launch pad, the rotating platforms are swung around the vehicle to allow the fuelling and final checkout procedures. The umbilical tower also contains an environmentally controlled and protected area for taikonauts to enter the spacecraft. Rotating platforms are swung open one hour prior to launch. Four swing arms provide connections for electricity, gases and fluids to the launch vehicle, and are retracted few minutes before launch.

The launch vehicle is carried on a mobile launch platform from the vehicle assembly building to the launch pad. The mobile launch platform moves on a 20 meter wide rail track and carries the launch vehicle vertical stack on a maximum velocity of 25 meters/min. The platform has a length of 24.4 meters, width of 21.7 meters, and 8.34 meters height, weighing 750,000 kg. It takes 60 minutes to complete the 1,500 meter journey to the launch pad.

The first orbital launch took place on April 24, 1970 when the CZ-1 Chang Zheng-1 (CZ1-1) rocket launched the first Chinese satellite, the Dong Fang Hong-1 (04382 1970-034A).

(Images via ChinaNews.CN, CCTV, Xinhua, various Chinese media - all linked on the live thread).

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