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The Long March 3A,also known as the Chang Zheng 3A,CZ-3A and LM-3A,is a Chinese orbital carrier rocket design. It is a 3-stage rocket,and is usually used to place communications satellites and Beidou navigation satellites into geosynchronous transfer orbits.
The Long March 1 (长征一号),also known as the Changzheng-1 (CZ-1),was the first member of China's Long March rocket family. Like the U.S.'s and the Soviet Union's first rockets,it was based on a class of ballistic missiles,namely the DF-4 class.
The Long March 2C (LM-2C),also known as the Chang Zheng 2C (CZ-2C),is a Chinese orbital launch vehicle,part of the Long March 2 rocket family. Developed and manufactured by the China Academy of Launch Vehicle Technology (CALT),the Long March 2C made its first launch on 9 September 1982. It is a two-stage launch vehicle with storable propellants,consisting of Nitrogen Tetroxide and Unsymmetrical Dimethylhydrazine. The launch vehicle was derived from the DF-5 ICBM.
The YF-100 is a Chinese liquid rocket engine burning LOX and kerosene in an oxidizer-rich staged combustion cycle.
The Long March 3C,also known as the Changzheng 3C,CZ-3C and LM-3C,is a Chinese orbital launch vehicle. It is launched from Launch Complex 2 and 3 at the Xichang Satellite Launch Center (XSLC). A three-stage rocket with two strapon liquid rocket boosters,it is a member of the Long March 3 rocket family,and was derived from the Long March 3B. It was designed to fill a gap in payload capacities between the Long March 3A and 3B.
The Long March 7,or Chang Zheng 7 in pinyin,abbreviated LM-7 for export or CZ-7 within China,originally Long March 2F/H or Chang Zheng 2F/H,nicknamed Bingjian,is a Chinese liquid-fuelled launch vehicle of the Long March family,developed by the China Aerospace Science and Technology Corporation (CAST). It made its inaugural flight on 25 June 2016.
The RD-120 is a liquid upper stage rocket engine burning RG-1 and LOX in an oxidizer rich staged combustion cycle with an O/F ratio of 2.6. It is used in the second stage of the Zenit family of launch vehicles. It has a single,fixed combustion chamber and thus on the Zenit it is paired with the RD-8 vernier engine. The engine was developed from 1976 to 1985 by NPO Energomash with V.P. Radovsky leading the development. It is manufactured by,among others,Yuzhmash in Ukraine.
The YF-115 is a Chinese liquid rocket engine burning LOX and kerosene in an oxidizer-rich staged combustion cycle. A high efficiency/high thrust environmental-friendly rocket engine was always an objective within Programme 863. Development began in the 2000s,along with its sibling,the bigger YF-100,which would power the LM-5,LM-6 and LM-7 boosters and first stages. Testing was directed by the China National Space Administration (CNSA) commencing in 2005. Development works are mainly carried out by the Xi'an Aerospace Propulsion Institute. It will be used as upper stage engine for China's next generation of medium and light environmental-friendly launch vehicles,namely the Long March 6 and the Long March 7. During early 2012,the engine system successfully passed vacuum testing. It is China's first upper stage rocket engine to adopt the staged-combustion cycle.
The YF-75D is a liquid cryogenic rocket engine burning liquid hydrogen and liquid oxygen in a closed expander cycle. It is China's third generation of upper stage cryogenic propellant engine,after the YF-73 and the YF-75. It is used in a dual engine mount in the H5-2 second stage of the Long March 5 launch vehicles. Within the mount,each engine can gimbal individually to enable thrust vectoring control. As its predecessor,the YF-75 it can adjust its mixture ratio to optimize propellant consumption. But as an additional improvement,it can do multiple restarts,against the single one of its predecessor.
The YF-40 is a Chinese liquid rocket engine burning N2O4 and UDMH in a gas generator cycle. It has dual gimbaling combustion chambers.
The YF-20 is a Chinese liquid-fuel rocket engine burning N2O4 and UDMH in a gas generator cycle. It is a basic engine which when mounted in a four engine module forms the YF-21. The high altitude variation is known as the YF-22 is normally paired with the YF-23 vernier to form the YF-24 propulsion module for second stages. New versions when used individually for booster applications are called YF-25.
The YF-23 is a liquid rocket vernier engine,burning N2O4 and UDMH. It is used in along the YF-22 to form the YF-24 and YF-25 propulsion modules.
The FG-46 is a Chinese spin stabilized solid rocket motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation for use in the Long March 2E on GTO missions. It first flew as a prototype SPTS-M14 on July 16,1990 on the Badr A mission. It had its first commercial mission orbiting the AsiaSat 2 on November 28,1995 and exactly one month later,on December 28 its second and last mission for EchoStar 1.
The CTS is an upper stage developed by the China Academy of Launch Vehicle Technology (CALT) to improve the performance of the Long March 2C to high LEO missions like SSO. The two stage LM-2 delivers the payload and stage to an elliptical orbit with the desired apogee and the CTS points the stack in the direction of the correct vector and activates the solid rocket motor (SRM) main engine to circularize it. It then dispenses the spacecraft and does a passivisation procedure.
The FG-47 is a Chinese solid rocket motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation for use in the Long March 2C SD/CTS/SMA third stage. It had its inaugural flight on the Iridium-MFS demonstration mission on September 1,1997.
Yuanzheng is a restartable upper stage developed by the China Academy of Launch Vehicle Technology (CALT) for the Long March rocket family.
The YF-1 was a Chinese liquid rocket engine burning N2O4 and UDMH in a gas generator cycle. It is a basic engine which when mounted in a four engine module forms the YF-2. It was used as the basis for developing a high altitude version known as the YF-3.
The FG-15 was a Chinese spin stabilized apogee kick motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation for use in the Dong Fang Hong 2 satellite bus for insertion into GSO orbit.
The FG-02 was a Chinese solid rocket motor burning Polysulfide. It was developed by China Hexi Chemical and Machinery Corporation for use in the Long March 1 third stage. It has a total nominal mass of 2,052 kg (4,524 lb),of which 1,806 kg (3,982 lb) is propellant load. It has an average thrust of 118 kN (27,000 lbf) with a specific impulse of 254 seconds burning for 38 seconds,with a total impulse of 4,500 kN (1,000,000 lbf). It used spin stabilization and a timing device to ignite in flight.
The FG-36 was a Chinese spin stabilized apogee kick motor burning HTPB. It was developed by China Hexi Chemical and Machinery Corporation for use in the Fengyun 2 satellite bus for insertion into GSO orbit.
References
- Data from Aerospace China magazine
- 1 2 Norbert Bgügge. "Chang Zheng CZ-1 & CZ-1D". B14643.DE. Retrieved 2015-07-25.
- ↑ "CZ-1D". Encyclopedia Astronautica. Archived from the original on 2013-12-30. Retrieved 2015-07-25.
- 1 2 "Chang Zheng-1". SinoDefence. Archived from the original on 2015-07-16. Retrieved 2015-07-25.
- ↑ Norbert Bgügge. "DF-4 & CZ-1 Design". B14643.DE. Retrieved 2015-07-25.
- 1 2 3 Norbert Bgügge. "Propulsion CZ-1 & CZ-1D". B14643.DE. Retrieved 2015-07-25.
- ↑ Norbert Bgügge. "The Chinese DF-3 missile". B14643.DE. Archived from the original on 2015-10-17. Retrieved 2015-07-25.
- ↑ "Dong Feng-3 (CSS-2)". SinoDefence. Archived from the original on 2015-11-23. Retrieved 2015-07-25.
- ↑ "Dong Feng-4 (CSS-3)". SinoDefence. Archived from the original on 2015-11-23. Retrieved 2015-07-25.
- ↑ "CZ-1". Encyclopedia Astronautica. Archived from the original on May 1, 2002. Retrieved 2015-07-25.
- ↑ "CZ-1". Encyclopedia Astronautica. Archived from the original on 2013-12-03. Retrieved 2015-07-25.
- ↑ Gunter Dirk Krebs. "CZ-1 (Chang Zheng-1)". Gunter's Space Page. Retrieved 2015-07-25.
