In an important step for the next phase of its manned space program, China has launched its second tracking and data relay satellite, Tian Lian-1B (TL-1B). The launch took place at 15:41 UTC on Monday from the Xi Chang Satellite Launch Center, in Sichuan Province, utilizing a Long March 3C (Chang Zheng-3C) launch vehicle.
The launch of Tian Lian-1B anticipates the high point for the Chinese Space Program this year, the launch of TG-1 TianGong-1 and SZ-8 Shenzhou-8. These two unmanned vehicles will attempt, for the first time in Chinese spaceflight history, to dock in orbit. This is an important step ahead of the launch of SZ-9 with its three person crew, which are scheduled to dock with TG-1.
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 predecessor, Tian Lian-1A, the Tian Lian-1B 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 platform can carry multiple telecommunications payloads for providing numerous services, such as fixed communication, international satellite communication, national and regional communication, wide-band data communication, mobile communication and direct broadcast; military communication, spacecraft tracking and data relay, etc.
The platform comprises six subsystems: control, power, propulsion, measurement and control, structure and thermal control subsystem. It’s configuration features a module subdivision, which includes communication module, propulsion module, service module and solar array.
The platform adopts a three-axis stabilized attitude control mode, with 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 satellite platform has been successfully applied in the 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 have been proved. Moreover, it has an expansion capacity and can be upgraded to some space exploration missions, such as meteorological satellite, lunar resource satellite services.
This was the seventh flight of the CZ-3C Chang Zheng-3C launch vehicle. 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. 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 (N204/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.
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. Down range Tracking and Control stations of the launch center are located in Xi Chang 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 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.
During 1993-1994 Xi Chang 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 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.