Chinese Launch:

Developed by the Shanghai Academy of Space Flight Technology (SAST) and China Academy of Space Technology (CAST), this meteorological satellite series had already seen the launch of four operational satellites, with two more scheduled before the new FengYun-4 satellites enters service.

The most important instrument on FY-2F is the IVISSR is a multi-purpose imaging Vis/IR radiometer.

This instrument is designed to address more objectives by appropriate blending of the characteristics of spectral coverage and resolution, spatial resolution, radiometric accuracy, etc. It will cover the full Earth disk and will operate in VIS – TIR with five channels. Spectral coverage in bands of Vis, NIR, SWIR, MWIR and TIR.

The instrument will be used for determining the atmospheric temperature (column/profile), cloud liquid water (column/profile), cloud type, precipitation rate (liquid) at the surface, short-wave Earth surface bi-directional reflectance, sea surface temperature, ocean imagery, land surface temperature, vegetation type and land surface imagery. FY-2F is also equipped with a solar X-ray detector for monitoring and early warning of solar flares.

The development of the FY-2 geosynchronous meteorological satellite series started in the 1980s. The first satellite was ready for launch in 1994, however, when the satellite was being loaded with propellant in the process facilities at the Xichang Satellite Launch Center, it exploded killing one technician and injuring 31 others.

The explosion destroyed the satellite and it took three years to prepare a replacement after the redesign of the propellant tank system. The first FY-2 satellite to reach orbit, FY-2A FengYun-2A (24834 1997-029A), was eventually launched by the CZ-3 Chang Zheng-3 (Y11) launcher from the LC1 launch platform at Xichang on 10 June 1997.

This satellite was operational until April 1998 when problems started. The control of the satellite was regained on December 1998, but the capabilities of the satellite were now very limited with only six images a day. The satellite was later moved to 86.6 degrees East when meteorological operations ended.

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Chinese Launch:

The ZiYuan-3 (ZY-3) is the first of a new series of high-resolution civilian remote sensing satellites, grown from a project that was initiated in March 2008.

The new satellite carries three high-resolution panchromatic cameras and an infrared multispectral scanner (IRMSS). The cameras are positioned at the front-facing, ground-facing and rear-facing positions.

Two cameras (front-facing and rear-facing) have a spectral resolution of 3.5m and 52.3km ground swath while the ground-facing camera has a spectral resolution of 2.1m and 51.1km ground swath. The IRMSS has a spectral resolution of 6.0m and 51.0km ground swath.

At launch the satellite had a mass of 2,630 kg. The satellite is equipped with two 3 meters solar arrays for power generation and will orbit a 505.984 km sun-synchronous solar orbit with 97.421 degree inclination. This orbit will have a re-visit cycle of 5 days.

Operational period will be four years with a possible life extension to five years.

The new satellite will conduct surveys on land resources, help with natural disaster-reduction and prevention and lend assistance to farming, water conservation, urban planning and other sectors, surveying the area between 84 degrees north and 84 degrees south latitude.

The ZiYuan program seems to cover different civil and military earth observation as well as remote sensing programs. The ZiYuan-1 program is focused on Earth resources and looks to have two distinct military and civil branches (this one being operated together with Brazil).

The satellites are operated jointly by the Center for Earth Operation and Digital Earth (CEODE) and the Brazilian INPE (Instituto Nacional de Pesquisas Espaciais - National Institute of Space Research).

The ZiYuan-2 program is probably used for aerial surveillance being operated by the People’s Liberation Army (PLA) while the new ZiYuan-3 series will be used for stereo mapping (like the TH-1 TianHui-1 mapping satellite that is operated by the PLA). ZiYuan-3 will be operated by the State Bureau of Surveying and Mapping.

Together with ZY-3, China also launched the VesselSat-2 microsatellite built by LuxSpace Sarl, an affiliate of OHB AG.

Vesselsat-2 weighs 28 kg and will be integrated into ORBCOMM’s Next Generation (OG2) constellation of 18 AIS-enabled satellites after an in-orbit test and checkout phase.

The exclusive rights to use the data of the Automatic Identification System (AIS) payload belong to ORBCOMM Inc., a global supplier of satellite-based communication and data services.

Launch Vehicle:

The first orbital space launch of 2012 was the 156th successful Chinese orbital launch, the 156th successful launch of the Chang Zheng launch vehicle family and the 37th orbital launch from the Taiyuan Satellite Launch Center.
The CZ-4B Chang Zheng-4B launch vehicle.

The feasibility study of the CZ-4 Chang Zheng-4 began in 1982 based on the FB-1 Feng Bao-1 launch vehicle. Engineering development was initiated in the following year. Initially, the Chang Zheng-4 served as a back-up launch vehicle for Chang Zheng-3 to launch China’s communications satellites.

After the successful launch of China’s first DFH-2 communications satellites by Chang Zheng-3, the main mission of the Chang Zheng-4 was shifted to launch sun-synchronous orbit meteorological satellites. In other hand The CZ-4B Chang Zheng-4B launch vehicle was first introduced in May 1999 and also developed by the Shanghai Academy of Space Flight Technology (SAST), based on the CZ-4 Chang Zheng-4.

The rocket is capable of launching a 2,800 kg satellite into low Earth orbit, developing 2,971 kN at launch. With a mass of 249,000 kg, the CZ-4B is 45.80 meters long and has a diameter of 3.35 meters.

SAST began to develop the Chang Zheng-4B in February 1989. Originally it was scheduled to be commissioned in 1997, but the first launch didn’t take place until late 1999. The modifications introduce on the CZ-4B Chang Zheng-4B included a larger satellite fairing and the replacement of the original mechanical-electrical control on the Chang Zheng-4 with an electronic control.

Other modifications were an improved telemetry, tracking, control, and self-destruction systems with smaller size and lighter weight; a revised nuzzle design in the second stage for better high-altitude performance; a propellant management system for the second stage to reduce the spare propellant amount, thus increasing the vehicle’s payload capability and a propellant jettison system on the third-stage.

The Chang Zheng-4B uses UDMH/N2O4 for all three stages. The first stage uses a YF-21B motor consisting of four 75,000kg thrust YF-20B thrust chambers motors with swinging nozzles. The second stage is similar to that of the CZ-3A, with a YF-24F rocket motor consisting of one 75,000kg thrust YF-22B main motor with fixed nozzles, and a YF-23F swivelling venire motor with four chambers motors (4,700kg thrust in total).

The third stage is a specially designed unit powered by a 98kN YF-40 rocket motor.

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 C, with maximum of 28 C in summer and minimum of -39 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.

The launch center has two launch complexes with a launch pad each (LC7 and LC9), a technical area for rocket and spacecraft preparations, a communications complex, mission command and control complex, and a space tracking complex.

The stages of the launchers are transported by railway, and offloaded at a transit station south of the launch complex. They are then transported by road to the technical area for checkout and testing.

The launchers are assembled at the launch pad using a crane at the top of the umbilical tower to hoist each stage in place. Satellites are airlifted to the Taiyuan Wusu Airport 300 km away, and then transported to the center by road.

(Images via ChinaNews.com and Xinhua)

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Chinese Launch:

China’s launch schedule has been moving around in recent months, partly due to the Long March 2C failure in August and partly because of the large number of missions that have been undertaken in what has been a memorable 2011 for the Chinese.

The launch of the ZiYuan-1 (2C) Earth observation satellite was originally tagged for a December 19 launch, prior to that slot being taken by the successful launch of the Long March 3B/E (Chang Zheng-3B/E), which lofted the NigComSat-1R into orbit on behalf of Nigeria from the Xixhang satellite Launch Center.

Eagle-eyed members of the NASASpaceflight.com forum then noticed Chinese messageboards talking about the launch moving up the schedule, prior to news of spectators arriving at the launch site for what became Thursday’s lift-off.

Not a great deal of information on the ZiYuan-1 (2C) have been revealed in the Chinese media, other than it is another of China’s Earth observation fleet – as much as this one has been confirmed to be for civilian purposes - sporting two High Resolution HR cameras, capable of a spatial resolution of 2.36m, with a joint swath of 54 km.

Its main feature is its panchromatic multi-spectral camera, which boasts a resolution of five meters and ten meters, with a swath of 60 km – suggesting this is an upgraded version of the Sino-Brazilian CBERS satellite – backed up by an alternative call sign of CBERS-02C.

The satellite – weighing in at a mass of 2,100 kg – will be mainly used by the Ministry of Land and Resources. It is designed to have a service life of three years.

This was the 19th orbital launch of the year for China, beating the United States’ 2011 record of 18 orbital launches.

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

The CZ-4B Chang Zheng-4B launch vehicle:

The feasibility study of the CZ-4 Chang Zheng-4 began in 1982 based on the FB-1 Feng Bao-1 launch vehicle. Engineering development was initiated in the following year. Initially, the Chang Zheng-4 served as a back-up launch vehicle for Chang Zheng-3 to launch China’s communications satellites.

After the successful launch of China’s first DFH-2 communications satellites by Chang Zheng-3, the main mission of the Chang Zheng-4 was shifted to launch sun-synchronous orbit meteorological satellites. In other hand The CZ-4B Chang Zheng-4B launch vehicle was first introduced in May 1999 and also developed by the Shanghai Academy of Space Flight Technology (SAST), based on the CZ-4 Chang Zheng-4.

The rocket is capable of launching a 2,800 kg satellite into low Earth orbit, developing 2,960,000 kN at launch. With a mass of 249,000 kg, the CZ-4B is 45.80 meters long and has a diameter of 3.35 meters.

SAST began to develop the Chang Zheng-4B in February 1989. Originally it was scheduled to be commissioned in 1997, but the first launch didn’t take place until late 1999.

The modifications introduce on the CZ-4B Chang Zheng-4B included a larger satellite fairing and the replacement of the original mechanical-electrical control on the Chang Zheng-4 with an electronic control.

Other modifications were an improved telemetry, tracking, control, and self-destruction systems with smaller size and lighter weight; a revised nuzzle design in the second stage for better high-altitude performance; a propellant management system for the second stage to reduce the spare propellant amount, thus increasing the vehicle’s payload capability and a propellant jettison system on the third-stage.

The Chang Zheng-4B uses UDMH/N2O4 for all three stages. The first stage uses a YF-21B motor consisting of four 75,000kg thrust YF-20B thrust chambers motors with swinging nozzles. The second stage is similar to that of the CZ-3A, with a YF-24F rocket motor consisting of one 75,000kg thrust YF-22B main motor with fixed nozzles, and a YF-23F swivelling venier motor with four chambers motors (4,700kg thrust in total).

The third stage is a specially designed unit powered by a 98kN YF-40 rocket motor.

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 based at a location 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.

(Images via weibo.com member “1706892431“, and ChinaNews).

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Chinese Commercial Launch:

NigComSat-1R is built on DFH-4 satellite bus developed by the China Academy of Space Technology (CAST), a subsidiary of China Aerospace Science and Technology Corporation (CASC), and is equipped with 28 transponders on board, including 4 C-band, 14 Ku-band, 8 Ka-band, 2 L-band.

The satellite will be positioned at 42.5 degrees East Longitude, has a lift-off mass of 5,100 kg – and a service lifespan of 15 years.

The satellite, covering Central Western and Southern Africa, Central and Eastern Europe, and some Central Asia area, will be mainly applied to communications, broadcasting, tele-education, broad band multimedia service, navigation service and so on, which will improve the national infrastructure and benefit the people in rural areas.

To further extend the operation and marketing of NigComSat-1R, Ku Kashi Beam was added to NigComSat-1R. The Satellite will supply the communications between Nigeria and China. Moreover, the utilization of satellite capacity will be enhanced without additional extra cost.

Projected orbital injection parameters are 200 km perigee, 41.991 km apogee and 24.8 degree inclination.

China’s 17th launch in 2011 was also the 154th successful Chinese orbital launch, the 154th launch of a Chang Zheng launch vehicle, the 9th launch from Xichang in 2011 and the 68th orbital launch from Xichang. This was the 18th space launch for China this year.

In December 2004 the Nigerian Communications Satellite Limited (NIGCOMSAT LTD) signed a contract with China Great Wall Industry Corporation (CGWIC) for the design, manufacture and launch of the NigComSat-1 (Nigerian Communication Satellite-1). The satellite was based on the DFH-4 platform and was equipped with 4 C-band, 14 Ku-band, 8 Ka-band and 2 L-band transponders.

The satellite was successfully launched on May 13, 2007 on the Z-3B/E Chang Zheng-3B/E (Y9) booster from the LC2 launch platform of the Xichang launch center. In April 2008, NigComSat-1 lost power from the southern solar array and the satellite eventually failed in November 2008 due to a technical error of the satellite’s northern solar array and was sent to a graveyard orbit as it became apparent, that the satellite could not be recovered.

The Nigerian Communications Satellite 1R Contract was signed between NIGCOMSAT LTD and CGWIC on March 24, 2009. Pursuant to the Contract, CGWIC, with its subcontractor China Academy of Space Technology (CAST), China Academy of Launch Vehicle Technology (CALT), and China Satellite Launch & Tracking Control General (CLTC) contributed for the NigComSat-1R launch and deliver it in orbit.

Nigerian Communications Satellite Limited was incorporated as a limited liability company in April 2006, which is a state-owned enterprise responsible for the operation and management of Nigerian Communications Satellites.

The NigComSat-1R, the replacement satellite of NigComSat-1, is the fourth in-orbit delivery contract for communications satellite signed between CGWIC and international customers. By identifying the problem and analyzing the failure mode, numbers of improvements based on tests and experiments have been applied to follow-on satellite programs, and the reliability of satellite has been enhanced constantly.

Furthermore, China Aerospace Science and Technology Corporation (CASC) and its relevant organizations reached a decision to build and launch NIGCOMSAT-1R with no extra cost to Nigerian customer.

NigComSat-1R paves the way for the international marketing development of China Aerospace and further confirms the friendship between Nigerian and China.

The DFH-4 (DongFangHong-4) platform is a large telecommunications satellite platform of new generation, it keeps high capability in output power and communication capacity ranking with international advanced satellite platforms. The applications for the DFH-4 platform aren’t limited to high capacity broadcast communication satellites and can be used to tracking and data relay satellites, regional mobile communication satellites, etc.

The platform comprises propulsion module, service module and solar array. It has a payload capacity of 588 kg and an output power of 10.5 kW by the end of its lifetime. Its design lifetime is 15 years and its reliability by the end of lifetime is more than 0.78. Based on versatility, inheritance, expandability and promptness principles and mature technology, the platform will reach world advanced level to meet the needs of international and domestic large communication satellite markets.

Generally DFH-4 based satellites are equipped with 22 Ku-band transponders (four 54MHz and 18 36MHz), 3 receiver antennas and 2 transmission antennas. With a designed operational life of 15 years, the DFH-4 can support the transmission of 150~200 TV programs simultaneously to ground users using a 0.45 meter antenna device. The DFH-4 satellite also features strong capabilities against hostile disturbance and jamming. The satellite’s power supply includes two 6 meter solar panels.

Launch sequence:

The fuelling of the third stage with LOX and LH2 starts at L-7 hours. First and second stages as well as the four strap-on boosters use hypergolic propellant fuelled earlier.

At L-1h 20m is the launch vehicle control system power on and function checkout followed by the telemetry system power on and function checkout. At L-40m the fairing air-conditioning is turned-off and the air-conditioning pipe is dropped-off. Technicians also proceed with the flight program loading and check-up. The gas pipes for the first stage second and are dropped-off.

The pre-cooling of the third stage engines takes place at L-20m and at L-13m takes place the third stage propellants topping. Between L-15m and L-10m the spacecraft umbilical disconnection takes place and at L-3m the telemetry and tracking systems power is switch-over and the third stage propellant fueling pipe is disconnected.

The disconnection of the gas pipe for the third stage is disconnected at L-2m followed by the control system power switch-over at L-1m 30s. Control system, telemetry system and tracking system umbilical disconnection take place at L-1m as well as the swinging-off of the rods. The TT&C systems start at L-30s and ignition comes at L-0s.

Eleven seconds after lift-off takes place the pitch-over maneuver. Boosters separation occurs at T+2m 21s followed at T+2m 39s by the separation between the first and second stages. Fairing jettison comes at T+3m 55s. Separation between the second and third stage takes place at T+5m 44s, with the third stage igniting for the first time. This burn ends at T+10m 12s.

The vehicle is now on a preliminary orbit until T+20m 56s when the third stage starts its second burn. This burn will last for 3 minutes and 6 seconds, ending at T+24m 2s. After the third stage shutdown takes places at T+24m 22s an attitude adjustment before spacecraft separation at T+25m 42s.

The companies:

Established in 1980, China Great Wall Industry Corporation (CGWIC) is the sole commercial organization authorized by the Chinese government to provide satellites, commercial launch services and to carry out international space cooperation.

As the professional company promoting international cooperation for China’s space industry, CGWIC is devoted to the internationalized development of China’s space industry. CGWIC has developed into a system integrator for space products and services.

It can meet customer’s multi-directional needs by providing comprehensive solutions for commercial launch services, satellite export, satellite ground tracking and control station construction, satellite applications, project financing, project insurance and technical training, etc. Through extensive international cooperation, CGWIC enjoys an excellent reputation in the international aerospace industry, the financial community and the insurance circle.

In addition, CGWIC is actively involved in the international marketing of civilian products and services utilizing space technology and provides high quality products and specialized services in diversified fields including satellite technology applications, green energy, information & electronic products, petroleum & petrochemical equipment, new materials, consulting services, international trade, international exhibition, international logistics, project contracting, international bidding, etc.

The Company Nigerian Communications Satellite (NIGCOMSAT) Limited was incorporated on April 4, 2006 as a company under the auspices of the Federal Ministry of Science and Technology. The company mission is “to manage and exploit the commercial viability of the Nigerian Communication Satellite for the social economic benefit of the nation”. The company is charged with the management and operation of the first geostationary communications satellite in sub-Sahara Africa.

Launch vehicle:

Developed in the basis of the CZ-3A Chang Zheng-3A, the CZ-3B 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.

The first launch of the CZ-3B took place on February 14, 1996, but ended in failure in what is now known has the “St. Valentine’s Day Massacre”. (Raw video available on L2). 

This was caused by the first CZ-3B failing two seconds after liftoff before crashing in a near by village killing dozens of people. The first successful launch took place on August 19th, 1997 when the second CZ-3B orbited the Agila-2 ‘Mabuhay’ (24901 1997-042A) communications satellite.

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 Xi Chang 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 Xi Chang 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 Xi Chang 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: NTAi TV, L2 and Nigcomsat.

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Chinese Taikonauts:

A space collectibles website is offering a postal cover for sale – apparently signed by the five men and two women who make up the group. The cover is dated 10th May 2010 which is the date which the Chinese have previously mentioned as the official date that the group were appointed to the Chinese Astronaut Team.

The two women taikonauts are named as Liu Yang and Wang Yaping. Wang had previously been identified, and exclusively revealed as a taikonaut by these authors (Tony Quine, Igor Lissov) in November 2010, when sources close to the Chinese programme had, when pressed, confirmed her inclusion in the group.

Liu Yang is also known to be a member of the same generation of Peoples Liberation Army Air Force female transport pilots as Wang, and has previously featured in the Chinese media for her aviation exploits. As such, her inclusion in the group is logical and there need be little doubt about the accuracy of her name appearing on the offending cover. Liu is believed to hold the military of Major, whilst Wang is a Captain.

Recent reports from China during the Tiangong 1 and Shenzhou 8 missions had mentioned that two women, together with seven men from the original 1998 taikonaut selection, formed the nine person training group for the anticipated Shenzhou 9 and 10 flights, planned to visit Tiangong 1 in 2012.

We can now be certain that the two women are Wang and Liu, and that, in all probability, one of them will become the first Chinese woman is space, within the next year.

The names of the five men were recorded in the note accompanying the postal cover as Zhang Lu, Chen Dong, Cai Xuzhe, Tang Hongbo and Yi Guangfu. It is possible, even likely, that these names have been read from the handwritten signatures on the envelope, although Chinese space forum sources have helped to verify these names as far as possible, from interpretation of the signatures.

These five men are not involved in the Shenzhou 9 and 10 missions, suggesting that they will have to wait until at least the Tiangong 2 series of missions scheduled no earlier than 2013 to reach orbit.

The new astronauts will certainly participate on the manned missions for TianGong-2 and TianGong-3, and we should expect that China will select a new taikonau class within two years.

The TianGong-1 spacecraft is expected to stay in orbit for two years and rendezvous and dock with three different spaceships. Beyond the Shenzhou-8, Shenzhou-9 and Shenzhou-10 will make similar missions and at least one of the two is to be manned.

The taikonauts will stay a maximum of two weeks on board. Before taikonauts climb on board TianGong-1, the conditions inside its experimental module will be adjusted to ensure they can live in an environment that contains enough oxygen, moisture and heat to be safe.

TianGong-1 will be placed on a near circular 350 km orbit after two orbiting manoeuvres and prior to the Shenzhou-8 launch this orbit will be reduced to 343 km. Two days after launch, the docking between the two vehicles will take place.

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, but 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 probably be equipped with two docking ports, this way allowing a permanent residency of the module. TG-3 mission is going to be the development of the technologies necessary for medium- to long-term orbit stay and to carry out more sophisticated scientific researches and experiments.

The Shenzhou spacecraft:

Considerable modifications have been made to the previous versions of the Shenzhou vehicle to prepare Shenzhou-8 for the docking mission. According to Chinese media, more than 600 modifications have been made, while nearly devices account for about 15 percent of the total.

These modifications had the objective to arm the vehicle with automatic and manual rendezvous and docking capabilities, as well as to enhance the performance, safety and reliability. The chief designer of China’s spacecraft systems, Zhang Bainan, said that Shenzhou 8 was going be the last vehicle to see significant modifications from previous ones and the next missions will use the same design that is intended for mass production.

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) and was responsible for the overall concept of the vehicle. Qi Faren was appointed the chief designer of the Shenzhou design team in 1992, being later succeeded in 2004 by Zhang Bai-Nan.  Qi Faren was also the chief designer of DongFanf Hong, 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 application payloads was 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 and the Academy of Aerospace Solid Propulsion Technology was responsible for the launch escape system.

Shenzhou was 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 in all phases of the mission, but the taikonautas 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, length 9.25 meters, maximum diameter 2.80 meters and a 17.00 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 distributed by 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 space craft, 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.

(Images via ‘Tony Quine Collection’, ChinaNews.cn, CCTV, Xinhua)

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China’s Record:

This launch was the 16th successful orbital launch this year for China, breaking the previous launch record of 15 successful missions in 2010. Taking into account the launch failure on August 18th, this was the 17th space launch for China this year.

The satellite that was orbited is the fifth BeiDou-2 IGSO (Inclined GSO) satellite of the system. The satellites were developed in the basis of the DFH-3B satellite platform and have a lifespan of eight years.

This constellation of Compass satellites will consist of 35 vehicles, including 30 MEO (21,500 km orbits) and IGSO (inclined at 55 degrees) satellites and five GSO satellites.

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 was initially used 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. The long-term goal is to develop a global navigation satellite network similar to the GPS and GLONASS by 2020.

The system will have two kinds 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 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.

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 July 26 when a Chang Zheng-3A orbited the ‘Compass-I4′ (37763 2011-038A) satellite.

This was the 22nd flight of the CZ-3A Chang Zheng-3A launch vehicle. The CZ-3A is a three-stage liquid launch vehicle, which has inherited the mature technology of the CZ-3 Chang Zheng-3. An upgraded liquid hydrogen and liquid oxygen cryogenic third stage has been developed to enable CZ-3A performing greater geostationary transfer orbit (GTO) capability.

The CZ-3A is equipped with a more flexible and sophisticated control system which supports substantial attitude adjustments to orient the payloads before spacecraft separation and provides adjustable satellite spin-up rotation rate. It has paved the way for the development of CZ-3B Chang Zheng-3B and CZ-3C Chang Zheng-3C, and become the basic type of GTO launch vehicles.

The CZ-3A is mainly used for GTO missions; it also can be used for LEO, SSO and polar orbit missions, as well as dual-launch and multiple-launch missions. The launch capacity of the CZ-3A to GTO is 2,650 kg, the lift-off mass is 241,000 kg, the overall length is 52.5 meters, the diameter of first stage and second stage is 3.35 meters, the diameter of third stage is 3.0 meters, and the maximum fairing diameter is 3.35 meters.

The first stage and second stage of CZ-3A employ storable propellants, i.e. unsymmetrical dimethy1 hydrazine (UDMH) and nitrogen tetroxide (N­2O4), and the third stage uses cryogenic propellants, i.e. liquid hydrogen (LH2) and liquid oxygen (LOX).

On the first stage the CZ-3A uses a DaFY6-2 engine with 2961.6 kN of thrust, while the second stage is equipped with a DaFY20-1 main engine (742 kN) and four DaFY21-1 vernier engines (11.8 kN each). The third stage is equipped with two YF-75 engines (78.5 kN each).

The fairing diameter of the CZ-3A is 3.35 meters and has a length of 8.89 meters.

CZ-3A consists of rocket structure, propulsion system, control system, telemetry system, tracking and safely system, coast phase propellant management and attitude control system, cryogenic propellant utilization system, separation system and auxiliary system, etc.

The launch success rate of CZ-3A is 100 percent since its maiden flight on February 8, 1994 when it successfully launched two experimental satellites (the Shi Jian-4 and the Kua Fu-1, a DFH-3 model). And it was awarded the “Gold Launch Vehicle” title by China Aerospace Science and Technology Corporation in June 2007.

This was the 153rd successful Chinese orbital launch, the 153rd launch of a Chang Zheng launch vehicle, the 8th launch from Xichang in 2011 and the 67th orbital launch from Xichang.

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 fueling 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) was launched the Shiyan Weixing (14670 1984-008A) communications satellite into orbit.

Before the end of the year China plans two more launches. The launch of the NigComSat-1R communications satellite for Nigeria is schedule to take place on December 19. Launched by a CZ-3B/E Chang Zheng-3B/E rocket from Xichang, this satellite will replace the NigComSat-1 satellite that lost power from the southern solar array and latter failed in November 2008 due to a technical error of the satellite’s northern solar array.

The other launch schedule for December will orbit the ZiYuan-1 (2C) Earth resource satellite using a Chang Zheng-4B launch vehicle from Taiyuan.

(Images via Chinanews.cn and Reuters)

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Chinese Launch:

The Shiyan Weixing-4 bird is a technology demonstrator satellite and will be used for experiments on new technologies. The satellites separated from the second stage of the launcher at around 0030UTC.

Also known as Tansuo-1 (28220 2004-012A), the first technological demonstrator SW-1 Shiyan Weixing-1 was launched at 1559UTC on April 18, 2004 by the CZ-2C Chang Zheng-2C (Y14) from the Xichang Satellite Launch Center. Supposedly, this satellite was part of China’s first digital imaging system capable of stereo Earth-terrain mapping.

The second satellite of this series, SW-2 (28479 2004-046A) was launched at 1045UTC on November 18, 2004 by the CZ-2C Chang Zheng-2C (Y15) also from the Xichang Satellite Launch Center and its mission was similar to the SW-1 mission.

SW-3 Shiyan Weixing-3 (33433 2008-056A), launched at 0015:06.909UTC on November 5, 2008, by the CZ-2D Chang Zheng-2D (Y12) was a technology demonstrator satellite and was used for experiments on new technologies in atmospheric exploration, according to its developer, the Harbin Institute of Technology.

The second satellite on board, the Chuang Xin-1 (3), was developed by the China Academy of Sciences and according to the state media the main mission objectives are atmospheric space environment detection system validation of new technologies and domestic components, assemblies and a variety of on-orbit testing and evaluation of a new payload.

The new satellite is also testing a system on the basis of satellite platform optimization, implemented around the flexible integration of payloads with high functionality.

The first Chuang Xin-1 (28058 2003-049B) satellite was launched piggyback on the CBERS-2 satellite at 0316UTC on October 21, 2003 by the CZ-4B Chan Zheng-4B (Y4) from the Taiyuan Satellite Launch Center and the second satellite of the series was launched at November 5, 2008, together with SW-3.

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

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.

The CZ-2D is a two stage launch vehicle mainly used for launching LEO and SSO payloads. It is 41.056 meters long and 3.35 meters in diameter, with a launch mass of 232,250 kg. it is capable of launch a 3,500kg cargo in a 200 km circular orbit or 1,300 kg to a Sun-synchronous orbit. 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.

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 151st successful Chinese orbital launch, the 51st orbital launch from the Jiuquan Satellite Launch Center, and the 5th orbital launch from Jiuquan this year.

Shenzhou-8 successful docking mission:

November 17 marked the return to Earth of the SZ-8 Shznhou-8 unmanned spacecraft, ending a completely successful mission with two dockings with the TG-1 TianGong-1 Unmanned space module.

Shenzhou-8 was launched on October 31 and immediately after entering orbit started a two day pursuit of the unmanned module. The first docking took place at 2011UTC on November 2. This was decisive moment for the future of China space program.

The two vehicles stayed docked until 1126UTC on November 14, when they separated with the objective of making a second rendezvous and docking, but this time during the daily orbital phase of its orbits. The second docking took place at 1153UTC.

Shenzhou-8 and TianGong-1 separated a second time at 1030UTC on November 16 and initiated the return to Earth. This return is very similar to the return and reentry procedures make by the Russian Soyuz. Landing took place at 1132UTC, November 17, on Siziwang Banner, Inner Mongolia.

With the successful dockings in orbit, China saw the door opening for the next step in space and now prepares for the launch of two new missions in 2012.

At least one of these missions will be manned and probably will carry the first female taikonaut. Also, Shenzhou-8 was the last Shenzhou vehicle to suffer significant modifications in relation to the previous flight models.

Future missions will now use the same spacecraft design, which is intended for mass production.

(Images via: ChinaDaily and CCTV)

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Another Chinese Launch:

Once again, the Chinese media classed the satellite as a new remote sensing bird that will be used for “scientific experiments, land survey, crop yield assessment, and disaster monitoring.”

Also on board the launch vehicle was the small TX-1 Tian Xun-1 satellite, which is equipped with a 2.5 kg CCD camera that was built by Suzhou University, sporting a maximum resolution of 30 meters. The satellite is 0.60 m x 0.75 cm in size, with a weight of 35 kg.

As was the case for the other launches of the YaoGan Weixing series, Western analysts believe this class of satellites is being used for military purposes. The previous satellite in the series, YaoGan Weixing-11, was launched September 22, 2010 from the Jiuquan Satellite Launch Center by a CZ-2D Chang Zheng-2D.

Looking back to the YaoGan Weixing launch series we can calculate the potential purpose of this new new electro-optical observation spacecraft.

The first YaoGan Weixing satellite (29092 2006-015A) was launched by a CZ-4C Chang Zheng-4C (Y1) from the Taiyuan Satellite Launch Center on April 27, 2006. Developed by Shanghai Academy of Spaceflight Technology (SAST), the details about this satellite were closely guarded, but later it was said that this was the first Jian Bing-5 satellite, equipped with the first space-based synthetic aperture radar (SAR).

The second satellite on the series, the YaoGan Weixing-2 (31490 2007-019A), was launched on 25 May, 2007, by a CZ-2D Chang Zheng-2D (Y8) from the Jiuquan Satellite Launch Center. Details were also restricted, though it is claimed that this spacecraft is an electro-optical military observation satellite, complementing the results of the YaoGan Weixing-1. This satellite was developed by the China Academy of Space Technology (CAST).

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Another SAR mission was launched on November 11, 2007 with the YaoGan Weixing-3 (32289 2007-055A) satellite orbited by a CZ-4C Chang Zheng-4C (Y3) launch vehicle from Taiyuan. Other SAR missions were the YaoGan Weixing-6 (34839 2009-021A), launched by a CZ-2C Chang Zheng-2C-III (Y19) from Taiyuan on April 22, 2009, and the YaoGan Weixing-8 (36121 2009-072A), launched on December 15, 2009, by the CZ-4C (Y4) also from Taiyuan.

On December 1, 2008, YaoGan Weixing-4 (33446 2008-061A) – the second electro-optical satellite on the series – was launched by a CZ-2D Chang Zheng-2D (Y9) from Jiuquan, and on December 15, 2008, YaoGan Weixing-5 (33456 2008-064A) was launched by a CZ-4B Chang Zheng-4B (Y20) from Taiyuan. It is now believed that this satellite was the fourth electro-optical bird on the series, as well as the YaoGan Wexing-7 (36110 2009-069A) launch on December 9th, 2009 from Jiuquan by a Chang Zheng-2D (Y10).

The YaoGan Weixing-9 mission, launched March 5th 2010 from Jiuquan, had an architecture different from the previous missions on the series. Launched by CZ-4C Chang Zheng-4C (Y5) rocket, the mission put not one but a triplet of satellites in Earth orbit. Flying in formation this three satellites form what looks like a type of NOSS system.

So, looking back at the launch sequence on the series and taking into account that this launch took place from Taiyuan and used a CZ-4B Chang Zheng-4B launch vehicle, is possible that YG-12 YaoGan Weixing-12 is a new electro-optical observation satellite developed by CAST.

This was the 145th successful Chinese orbital launch, the 144th launch of a Chang Zheng launch vehicle, the 33rd successful orbital launch from Taiyuan (the 1st in 2011) and the 8th orbital Chinese launch in 2011.

The CZ-4B Chang Zheng-4B launch vehicle:

The feasibility study of the CZ-4 Chang Zheng-4 began in 1982 based on the FB-1 Feng Bao-1 launch vehicle. Engineering development was initiated in the following year. Initially, the Chang Zheng-4 served as a back-up launch vehicle for Chang Zheng-3 to launch China’s communications satellites.

After the successful launch of China’s first DFH-2 communications satellites by Chang Zheng-3, the main mission of the Chang Zheng-4 was shifted to launch sun-synchronous orbit meteorological satellites. In other hand The CZ-4B Chang Zheng-4B launch vehicle was first introduced in May 1999 and also developed by the Shanghai Academy of Space Flight Technology (SAST), based on the CZ-4 Chang Zheng-4.

The rocket is capable of launching a 2,800 kg satellite into low Earth orbit, developing 2,960,000 kN at launch. With a mass of 249,000 kg, the CZ-4B is 45.80 meters long and has a diameter of 3.35 meters.

SAST began to develop the Chang Zheng-4B in February 1989. Originally it was scheduled to be commissioned in 1997, but the first launch didn’t take place until late 1999.

The modifications introduce on the CZ-4B Chang Zheng-4B included a larger satellite fairing and the replacement of the original mechanical-electrical control on the Chang Zheng-4 with an electronic control.

Other modifications were an improved telemetry, tracking, control, and self-destruction systems with smaller size and lighter weight; a revised nuzzle design in the second stage for better high-altitude performance; a propellant management system for the second stage to reduce the spare propellant amount, thus increasing the vehicle’s payload capability and a propellant jettison system on the third-stage.

The Chang Zheng-4B uses UDMH/N2O4 for all three stages. The first stage uses a YF-21B motor consisting of four 75,000kg thrust YF-20B thrust chambers motors with swinging nozzles. The second stage is similar to that of the CZ-3A, with a YF-24F rocket motor consisting of one 75,000kg thrust YF-22B main motor with fixed nozzles, and a YF-23F swivelling venire motor with four chambers motors (4,700kg thrust in total).

The third stage is a specially designed unit powered by a 98kN YF-40 rocket motor.

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 based at a location 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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Chinese Mission:

The mission of Shenzhou-8 is scheduled for a mission of three weeks, during which time it is expected to dock twice with unmanned space module TianGong-1 that was launched on September 29.

This module is part of China’s space station and is an experimental space laboratory that will be mainly used to carry out the rendezvous and docking test, as well as the mastering of the technologies related to rendezvous and docking and accumulate the experience for the construction, management and operation of a space station.

Providing everything continues to go according to plan, and after all the systems are verified on both vehicles, the first docking is expected to take place on November 3.

TianGong-1 and Shenzhou-8 will stay docked for 12 days, after that undocking will occur and a second docking manoeuvre will take place. After another period of docking, the unmanned spacecraft will be commanded via autonomous flight to return to Earth.

Preparing for launch:

Large-scale testing of the Shenzhou-8 has begun at the end of March 2011 after functional and mechanical tests. Launch was originally schedule to take place at the end of October, but the SJ-11 ShiJian 11-04 loss - due to a CZ-2C Chang Zheng-2C second stage failure on August 18 - led to a delay to the docking mission launch.

Eventually, the capsule arrived at the Jiuquan Satellite Launch Center on August 26 and the CZ-2F Chang Zheng-2F launch vehicle for the Shenzhou-8 launch arrived at Jiuquan on September 24, just five days before the TG-1 TianGong-1 launch.

At the end of September the state news media said that “the unmanned Shenzhou-8, part of China’s first spacecraft rendezvous and docking mission, would be launched in early November.”

Citing Niu Hongguang, deputy commander-in-chief of the program, Xinhua then said that “the launch was not been affected by the postponed lift-off of the Tiangong-1 space module.” With the successful launch of TianGong-1 on September 29, rumours started to surface about a possible November 1 launch date for Shenzhou-8.

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 transmitting between the spacecraft and the ground in this mission is newly designed and is more advanced than that used in Shenzhou-7 – via the replacement of a wireless signal transmission system using optical fibber for improved the quality of voice and image transmission.

On October, 26 the Chang Zheng-2F launch vehicle with the Shenzhou-8 capsule was transported to the launch platform and on October 29 specialists and technicians conducted a simulated launch of Shenzhou-8 with all the equipments and systems working normally. The exercise was under the coordination of the Beijing Aerospace Flight Control Center, the command center for Chinese space program.

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During the exercise, the compatibility and connectivity of different systems involved in the mission were tested, and results indicated that the systems were all ready for the launch.

Experiments on Shenzhou-8:

There are several experiments on board Shenzhou-8 in a total of 17 research programs, including the Project SIMBOX, a cooperation project between China and Germany.

Among the research programs, 10 will be conducted by China, six by Germany and one is a joint research program. The cooperation agreement was signed in May, 2008 – and this is the first time China manned space program will carry out an international cooperation in the field of space life sciences.

The leadership and organization of the German side is up to the DLR (German Aerospace Center) and the technical requirements are implemented by Astrium.

SIMBOX is the first non-Chinese experiment equipment aboard Shenzhou, the showpiece of China’s manned space flight. On board Shenzhou-8 are 17 German and Chinese experiments in the field of biomedicine participate, including plants, animals and human cells of the immune and nervous system that will be exposed to the environment of space for a period of three weeks. The effects of spaceflight on the samples will then be examined after the end of the mission.

DLR’s Space Agency has funded the program and is the project leader of the National Space Program SIMBOX. The science plant consists of a centrifuge and oven, including over 100 experimental chambers and the six experiments of German research institutions. Industrial prime contractor for the development and construction of the experimental apparatus is Astrium.

The overall responsibility for the mission is on the Chinese side at CMSEO. The Chinese Organization of Space Science (Gessa) is responsible for the coordination and technical support within the scientific payload of the Chinese manned space program.

In 2008, the first draft of the experiment was reviewed for technical feasibility (available volume, materials, etc.) and on January 2009 the first prototype was handed over to the Working Group for its first tests. The materials used on the experiment were tested for biocompatibility. In February the first prototype test was carried out successfully and the experiment went on to further development with more biocompatibility tests starting in March.

In 2010, the hardware was developed at Astrium and in December 2010, the final flight hardware was delivered to the SIMBOX team.

In April 2011, a complete test sequence under starting conditions was carried out successfully in Beijing. In October the German team travelled to the Jiuquan Satellite Launch Center to prepare the experiment for launch. In the meantime in Beijing, all the partners as the German Aerospace Center and the Chinese organization for manned space flight simulated the complete sequence of the science mission. The result: “Green light” for a launch on 30 October 2011.

Other items on Shenzhou-8 include the “dreams” of more than 40,000 people that are stored as text and video on a micro chip. The 42,891 “dreams” were selected from a pool of 12 million in line with the criteria of “positive and passionate”, said Feng Chunping, president of China Space News, the activity sponsor.

Proposed by Chinese citizens, university students and children from orphanages, most dreams expressed longing for space, hopes for a stronger nation, and a greener and better society.

Some are bold hopes, like the one one person wrote saying that China’s future space station should develop a function to collect space debris. Others are practical. Zhou Maocuo and Jia Linlin from an orphanage in Beijing said their dream is to have a stable home.

The docking:

Prior to the launch of Shenzhou-8 spacecraft the TianGong-1 orbit was adjusted to a 343 km altitude near circular orbit. This phase adjustment was needed to achieve the right height and the right place for docking. At 1134UTC on October 30, the unmanned module completed a 180 degree turn to align for the upcoming Shenzhou-8.

The first phase of the docking manoeuvre will take place at a distance of 52 km from TianGong-1 with the monitoring center system analysing the parameters of Shenzhou-8. At this distance both spacecrafts will be able to read the relative position and velocity of each other.

The docking manoeuvres will start when the two vehicles are 20 km apart. In the second stage of the process there will be three parking points at 5 km, 400 m, 140 m. In the parking points, their relative positions have to remain according to plan, so the ground staff can determine their status and decide whether to continue or revoke the docking. Shenzhou-8 will act as the “active vehicle”, while the TianGong-1 will act “passive vehicle”.

Sensors on both will start given information about the velocity and distance. With the distance getting closer the data sent to the ground control data will be more accurate, so that ground-based monitoring and control personnel can carefully monitor the operations.

The relative velocity of the two vehicles will slowdown to 0.2 meters per second relative speed and the lateral deviation of no more than 18 cm. Final command for docking will take place at 1,000 meters distance.

After soft docking, it will take 15 minutes to tighten the locks and then the control center will adjust the cabin environment, such as temperature, pressure, in accordance with manned conditions for future manned flight.

The two spacecrafts will remain docked for 12 days and after that they will separate to try a new docking at an yet undetermined date. After another (shorter) period of docking operations, Shenzhou-8 will return to earth within a day.

For the docking Shenzhou-8 and TianGong-1 are equipped with a docking mechanism similar to the Russian APAS-89/95. The mechanism consists of a docking port, radio beacons and transponders, communication antenna, UHF radar, laser rangefinder, and a electro-optical tracking system. The diameter of the hatch is 0.8 meters.

The future:

The TianGong-1 spacecraft is expected to stay in orbit for two years and rendezvous and dock with three different spaceships. Beyond the Shenzhou-8, Shenzhou-9 and Shenzhou-10 will make similar missions and at least one of the two is to be manned.

The taikonauts will stay a maximum of two weeks on board. Before taikonauts climb on board TianGong-1, the conditions inside its experimental module will be adjusted to ensure they can live in an environment that contains enough oxygen, moisture and heat to be safe.

TianGong-1 will be placed on a near circular 350 km orbit after two orbiting manoeuvres and prior to the Shenzhou-8 launch this orbit will be reduced to 343 km. Two days after launch, the docking between the two vehicles will take place.

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, but 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 probably be equipped with two docking ports, this way allowing a permanent residency of the module. TG-3 mission is going to be the development of the technologies necessary for medium- to long-term orbit stay and to carry out more sophisticated scientific researches and experiments.

The Shenzhou-8 spacecraft:

Considerable modifications have been made to the previous versions of the Shenzhou vehicle to prepare Shenzhou-8 for the docking mission. According to Chinese media, more than 600 modifications have been made, while nearly devices account for about 15 percent of the total. These modifications had the objective to arm the vehicle with automatic and manual rendezvous and docking capabilities, as well as 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 the China Academy of Space Technology (CAST) and was responsible for the overall concept of the vehicle.

Qi Faren was appointed the chief designer of the Shenzhou design team in 1992, being later succeeded in 2004 by Zhang Bai-Nan.  Qi Faren  was also the chief designer of DongFanf Hong, 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 application payloads was 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 and the Academy of Aerospace Solid Propulsion Technology was responsible for the launch escape system.

Shenzhou was 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 in all phases of the mission, but the taikonautas 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, length 9.25 meters, maximum diameter 2.80 meters and a 17.00 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 distributed by 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 space craft, 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-8 was launched by the CZ-2F Chang Zheng-2F, possibly the CZ-2F/G variant of the launch vehicle usually used for the previous 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” (Devine Arrow) version that was developed from the CZ-2E Chang Zheng-2E launch vehicle, which in turn was based on the proven flight technology of the CZ-2C Chang Zheng-2C launch vehicle.

Conceptual design of the CZ-2E launch vehicle began in 1986, and the vehicle was launched on the world 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 suffered nearly 170 technical modifications and used five newly developed technologies. After it was transported to the Jiuquan launch center on September it was submitted to different technical tests in preparation for launch.

This vehicle is going to be used for the launch of the TianGong-1 module and the future cargo vehicles until a more powerful launch vehicle is available.

A substantial difference on this rocket with the previous that was used for the FG-1 launch is the use of the launch escape tower and usual fairing, similar to the Russian model used on the manned program.

Other characteristic of this version is the fact that is capable of more precise orbit insertion accuracy. This is possible with the introduction of improved navigation systems and complex guidance system features real-time input to the rocket to orbit parameters, and use GPS data outside the measurement error correction parameters so as to achieve double redundancy. Also, more propellant is loaded on the boosters, thus increasing the firing 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, being capable of launching 8,600 kg cargos 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 burning 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. 3D rendering by Junior Miranda).

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Chinese Launch:

According to Eutelsat, the new W3C satellite will provide significant new capacity for broadcasting, telecommunications and broadband services, replacing existing Eutelsat satellites at 16 degrees East. This is a leading position for broadcast markets in Central and Eastern Europe, and also provides video services to the islands in the Indian Ocean.

16 degrees East is one of Eutelsat’s most long-standing orbital locations, as satellites have been in service there continuously since 1988. Over more than two decades, it has developed into one of the company’s largest video locations, with more than 400 channels broadcast to an audience of over 11 million households.

Markets in the areas served by 16 degrees East have been experiencing solid growth, particularly in Central and Eastern Europe.

The availability of W3C will significantly increase capacity at 16 degrees East. The satellite will have four main coverage zones: high-power Ku-band coverage of Europe with a beam centred over Central Europe, particularly optimised for Direct-to-Home (DTH) reception in this region; extensive coverage across Extended Europe, including North Africa, the Middle East and Central Asia, via a Ku-band beam optimised for professional video links and data networks.

Ku-band coverage will include Sub-Saharan Africa and Indian Ocean islands for regional telecommunications and internet services (interconnection with Europe will also be possible with the African coverage through a combination of Ka-band frequencies in Europe and Ku-band frequencies in Africa); and a high-power Ku-band beam over Madagascar and the Indian Ocean Islands for DTH applications.

The W3C Satellite was designed and manufactured by Thales Alenia Space France for EUTELSAT. The satellite is based on the Spacebus 4000 C3 platform with a lift-off mass of 5,400 kg. With a design life of over 15 years, it has 56 operational transponders (53 in Ku-band and 3 in Ka-band) onboard, with an end-of-life power of 12kW.

On February, 2009 Eutelsat had picked China’s CZ-3B to launch its W3B satellite. However, on February 18, 2010, Thales Alenia Space announced that the W3B would be launched by an Ariane-5 ECA – announcing also that the W3C satellite would be launched by a Chinese vehicle.

W3B would be launched on October 28th, 2010 but the satellite suffered a sizeable leak in the propulsion system immediately after launch and was declared a total loss.

The Launcher:

To meet demand of the international satellite launch market – especially for high power and heavy communications satellites – the development of Chang Zheng-3B launch vehicle started in 1986 on the basis of the fight proven technology of Long March launch vehicles. The CZ-3B 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.

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 for 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.

This was the 148th successful Chinese orbital launch, the 148th launch of a Long March (Chang Zheng) launch vehicle, the seventh launch from Xichang in 2011 (the 66th overall from Xichang), and the 11th successful orbital launch for China in 2011.

Launch Procedures:

Launch countdown procedures started at T-7h 30m with the LOX fuelling of the third stage of the launch vehicle, followed with the LH2 fuelling at T-6h. At T-1h 20m the controllers powered on the control system of the launch vehicle and conduct a functional checkout. At 60 minutes prior to launch the telemetry system was powered up, followed by functional tests.

The air-conditioning to the fairing was ceased and disconnected at T-40m, followed by the uploading of the flight profile of the rocket. The pre-cooling of the third stage engine took place at T-22m followed at T-13m by the topping of the third stage propellants.

Between T-15m to T-13m the umbilical to the satellite was disconnected and at T-3m the Telemetry and Tracking Systems power was switched over. The fuelling lines were disconnected from the third stage, followed by the umbilical disconnections of Control System and the swing off of supporting arms of the umbilical tower. At T-30 seconds before the ignition the Telemetry and Tracking Systems were started.

Ignition of the four liquid strap-on boosters and the YF-25 first stage engine took place at T-0s. After clearing the launch tower, the launcher executed a pitch-over manoeuvre at T+10s. Booster separation took place at T+1m 21s, followed by first stage/second stage separation at T+1m 39.4s. The jettison of the fairing took place at T+3m 55.5s.

Second stage/third stage separation – and third stage first start – occurred at T+5m 44.2s at an altitude of 169 km. The shutdown of the third stage came at T+10m 20.4s, with the second third stage ignition taking place at T+21m 3.9s. This burn lasted for almost 3 minutes.

Spacecraft separation occurred at T+25m 42.8. Initial orbital parameters will be: perigee of 200 km altitude, apogee of 35,746.2 km altitude and inclination of 26,1 degrees. The satellite will then use its own engine to manoeuvre to geostationary orbit.

Launch site:

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, focusing on broadcast, communications and meteorological satellites.

The center’s headquarters is in Xichang City, a distance of 65 km from the launch site. The climate in the region is subtropical, with an average annual temperature of 16 degrees C. Ground wind in the region is generally very mild all the year round.

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 kilometres south-west of the launch pad, providing flight and safety control during launch rehearsal and launch.

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 and Eutelsat).

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