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China’s Rockets and Missiles
The Risk Report
Volume 11 Number 1 (January-February 2005)
The following are the most recent technical specifications of China’s
missiles and rockets.
Chinese Missiles
Dong Feng-3 or -3A (DF-3/3A) (US: CSS-2)
The CSS-2/DF-3 is a single-stage, liquid fueled missile fitted with a thermonuclear warhead. It has a range of 2,800 kilometers and was the first indigenously designed Chinese ballistic missile. Several CSS-2 missiles were exported to Saudi Arabia in 1988.
Technical Specifications
Range (km): 2800
Payload (kg): 2150
Diameter (m): 2.25
Weight (tons): 64
Length (m): 24
Stages: 1
Propellant: UDMH and nitrogen tetroxide
Mission: Nuclear-armed; mobile launcher
Status: First flight, December 1966; now deployed.
Dong Feng-4 (DF-4) (US: CSS-3)
The DF-4 is a two-stage, liquid fueled ballistic missile with a range of 4,750 kilometers. It can reach targets throughout European Russia, including Moscow.
Technical Specifications
Range (km): 4750
Payload (kg): 2200
Diameter (m): 2.25
Weight (tons): 80
Length (m): 28
Stages: 2
Propellant: UDMH
Mission: Nuclear-armed; ground-based
Status: First flight, September 1971; deployed.
Dong Feng-5 (DF-5, DF-5A) (US: CSS-4)
The DF-5 is China’s only true intercontinental ballistic missile, with a range of over 13,000 kilometers. It is a two-stage, liquid-fueled missile that is virtually identical to the Long March-2 rocket. According to a report by the U.S. Secretary of Defense, China is replacing its approximately twenty DF-5 missiles with the CSS-4 Mod 2, an upgraded version which has greater range.
Technical Specifications
Range (km): 13,000
Payload (kg): 3,200
Diameter (m): 3.35
Weight (tons): 183
Length (m): 32.6
Stages: 2
Propellant: UDMH and nitrogen tetroxide
Mission: Nuclear-armed; silo-based
Status: First flight September 1971; approximately 20 deployed.
Dong Feng-21 (DF-21) (US: CSS-5)
The DF-21 is the land-based version of the Julang-1 (JL-1) submarine launched missile (SLBM), with the same technical characteristics but deployed on a transporter-erector-launcher (TEL) vehicle. It can carry a 600 kilogram payload about 1800 kilometers.
Technical Specifications
Range (km): 1800 km
Payload (kg): 600 kg
Diameter (m): 1.4
Weight (tons): 14.7
Length (m): 10.7 m
Stages: 2
Propellant: Solid
Mission: Nuclear-capable; mobile launcher
Status: First flight, May 1985; deployed.
Dong Feng-15 (DF-15) (US: CSS-6 or M-9)
The DF-15 (M-9) is a short-range, mobile, solid-fueled missile, that can carry a 950 kilogram payload 600 kilometers. It is marketed abroad by the China Precision Machinery Import-Export Corporation (CPMIEC).
Technical Specifications
Range (km): 600
Payload (kg): 950
Diameter (m): 1
Weight (tons): 6.2
Length (m): 9.1
Stages: 1
Propellant: Solid
Mission: Short-range; mobile; nuclear-capable
Status: First flight, June 1989; widely deployed.
Dong Feng-11 (DF-11) (US: CSS-7 or M-11)
The DF-11 is a short-range ballistic missile that can carry a 800 kilogram payload 300 kilometers. The DF-11 is believed to be deployed largely in the Nanjing Military Region, opposite Taiwan. The M-11, an export version of the DF-11, has been exported to Pakistan. The DF-11A (DF-11 Mod 2), an improved version of the DF-11, reportedly was displayed at a military parade in 1999, and may now be in service.
Technical Specifications
Range (km): 300
Payload (kg): 800
Diameter (m):
Weight (tons):
Length (m):
Stages: 2
Propellant: Solid
Mission: Short-range; mobile; conventionally-armed; nuclear-capable
Status: First flight, mid-1990; widely deployed.
Dong Feng-31 (DF-31)
The DF-31 is a long-range, mobile, solid-fueled ballistic missile estimated to have a range of 8,000 kilometers. Deployment of the DF-31 is expected by the end of the decade. The DF-31A, a longer-range follow-on version of the DF-31, reportedly is also under development. The DF-31A is expected to have a range of approximately 12,000 kilometers.
Technical Specifications
Range (km): 8000
Payload (kg): 700
Diameter (m):
Weight (tons):
Length (m):
Stages: 3
Propellant: Solid
Mission: Nuclear-capable; mobile
Status: Under development
Submarine Launched Missiles (SLBMs)
Julang-1 (JL-1) (US: CSS-N-3)
The JL-1 is a single-warhead, two-stage submarine launched ballistic missile. It is the first Chinese missile to use only solid fuel and China’s only deployed SLBM.
Technical Specifications
Range (km): 1700
Payload (kg): 600
Diameter (m): 1.4
Weight (tons): 14.7
Length (m): 10.7
Stages: 2
Propellant: Solid
Mission: Submarine-launched; nuclear-capable
Status: First flight, October 1982; 12 deployed on Xia-class submarines.
Julang-2 (JL-2) (US: CSS-N-4)
The JL-2 is a three-stage, submarine-launched ballistic missile currently under development. It is based upon the DF-31, a land-based long-range ballistic missile also still being developed. The JL-2 is expected to have a range of approximately 8,000 kilometers, far greater than the 1,700 km range of the JL-1. The JL-2 would be deployed on the Project 094 SSBN, currently under construction.
Technical Specifications
Range (km): 8000
Payload (kg): 700
Diameter (m):
Weight (tons):
Length (m):
Stages: 3
Propellant: Solid
Mission: Submarine-launched; nuclear-capable
Status: Under development
Note: According to a report in July 2003 by the U.S. Secretary of Defense,
China has approximately twenty ICBMs capable of targeting the United
States. The report says that this number could increase to about 30 by
2005 and could reach 60 by 2010.
Chinese Launch Vehicles
Long March 2C/SD Launch Vehicle (LM-2C/SD or CZ-2C/SD)
The LM-2C/SD is a two-stage launch vehicle with a smart dispenser and a payload capacity of 2,500-2,800 kilograms. It is used to deploy recoverable satellites in low earth orbit (LEO). The original model, the LM-2, was renamed the LM-2C after a successful test flight in 1975. The LM-2C's design was derived directly from China's DF-5 (CSS-4) ballistic missile. It was renamed the LM-2C/SD in 1999, after being modified in preparation to launch Motorola's Iridium communications satellites. The modifications included upgrades to the first two stages and the addition of a smart dispenser (SD) as a third stage. The LM-2C/SD is capable of placing multiple satellites into different Low Earth Orbits (LEO).
Technical Specifications
1st Stage 2nd Stage Smart Dispenser
Diameter (m): 3.35 3.35 2.7
Mass of Propellant (t): 162.7 54.7 12.5/50
Propellant: Nitrogen tetroxide/UDMH HTPB
Engine Type: DaYF6-2 DaYF20-1 (Main) Solid motor
YF21-1 (Vernier)
Engine Thrust (kN): 2962 742 (Main) 157
11.8x4 (Vernier)
Lift-off Mass (t): 213
Overall Length (m): 40.4
Fairing Diameter (m): 3.35
Long March 2D Launch Vehicle (LM-2D or CZ-2D)
The LM-2D is a two-stage launch vehicle adapted from the first and second stages of the Long March 4. The LM-2D can deploy a payload of 3700 kilograms into low earth orbit (LEO). The LM-2D is launched from the Jiuquan Satellite Launch Center.
Technical Specifications
1st Stage 2nd Stage
Diameter (m): 3.35 3.35
Mass of Propellant (t): 182.07 35.408
Propellant: Nitrogen tetroxide/UDMH
Engine Type: DaYF-21B YF-22B (Main)
Engine Thrust (kN): 2250 742 (Main) 46.1 (Vernier)
Lift-off Mass (t): 232.7
Overall Length (m): 37.73
Fairing Diameter (m): 2.90/3.35
Long March 2E Launch Vehicle (LM-2E or CZ-2E)
The LM-2E is a two-stage launch vehicle using stages similar to those of the LM-2C. The LM-2E has four 15 meter strap-on boosters. It is used to deploy payloads up to 9,500 kilograms in low earth orbit (LEO). When equipped with a perigee kick motor (EPKM) as a third stage, the LM-2E can deploy a payload of 3,500 kilograms in geostationary transfer orbit (GTO). Kick motors for the LM-2E were originally supplied by foreign companies; however, China now has the ability to produce its own kick motors.
Technical Specifications
Boosters 1st Stage 2nd Stage 3rd Stage
Diameter (m): 2.25 3.35 3.35
Mass of Propellant (t): 148 (4 x 37) 181 37
Propellant: Nitrogen tetroxide/UDMH
Engine Type: 4 x YF-20 YF-21 YF-22 (Main)
YF-23 (Vernier)
Engine Thrust (kN): 4 x 740 2961 742 (Main)
47 (Vernier)
Lift-off Mass (t): 460
Overall Length (m): 49.7
Fairing Diameter (m): 4.20
Long March 2F Launch Vehicle (LM-2F or CZ-2F)
The LM-2F, China's largest launch vehicle, was developed on the basis
of the LM-2E. The LM-2F has four boosters, two stages, and an escape
tower. On October 15, 2003, an LM-2F launch vehicle carrying a Shenzhou
V spacecraft launched China's first astronaut into space.
Long March 3 Launch Vehicle (LM-3 or CZ-3)
The LM-3 is a three-stage launch vehicle with a cryogenic third stage. The liquid hydrogen and liquid oxygen third-stage engines were developed by the China Academy of Launch Vehicle Technology (CALT). The LM-3 can deploy satellites up to 1,500 kilograms into a geosynchronous transfer orbit (GTO). It was first launched in January 1984.
Technical Specifications
1st Stage 2nd Stage 3rd Stage
Diameter (m): 3.35 3.35 2.25
Mass of Propellant (t): 144 36 8.7
Propellant: Nitrogen tetroxide/UDMH LOX/LH
Engine Type: 4 x YF-20 YF-22 (Main) YF-73
(YF-21) YF-23 (Vernier)
Engine Thrust (kN): 2962 2911 (Main) 44.4
2834 (Vernier)
Lift-off Mass (t): 204
Overall Length (m): 44.56
Long March 3A Launch Vehicle (LM-3A CZ-3A)
Designed and developed using LM-3 technology, the LM-3A uses a more powerful cryogenic third stage engine, a more capable control system, and greater flexibility in the attitude control system. It can deploy a 2,600 kilogram payload into geosynchronous transfer orbit and can be used for low earth orbit and polar orbit missions as well. It was first launched in February 1994.
Technical Specifications
1st Stage 2nd Stage 3rd Stage
Diameter (m): 3.35 3.35 3.0
Mass of Propellant (t): 171.8 30.8 18.2
Propellant: Nitrogen tetroxide/UDMH LOX/LH2
Engine Type: DaYF6-2 DaYF20-1 (Main) YF-75
(4 x YF-20) DaYF21-1 (Vernier)
Engine Thrust (kN): 2962 742 (Main) 157
11.8x4 (Vernier)
Lift-off Mass (t): 241
Overall Length (m): 52.52
Fairing Diameter (m): 3.35
Long March 3B Launch Vehicle (LM-3B or CZ-3B)
The LM-3B launch vehicle was designed with a LM-3A vehicle as its core with four strap-on liquid propellent boosters. The core stage of the LM-3B is identical to the -3A except that the stage tanks have been extended and reinforced, the fairing has been enlarged, and the control and telemetry systems have been modified to accommodate the strap-on boosters. The LM-3B can deploy a payload of 5,200 kilograms into geosynchronous transfer orbit (GTO). The LM-3B can also perform payload attitude adjustments and dual or multiple launch requirements. The LM-3B is launched from Xichang Satellite Launch Center (XSLC) in Sichuan Province.
Technical Specifications
Boosters 1st Stage 2nd Stage 3rd Stage
Diameter (m): 2.25 3.35 3.35 3.00
Mass of Propellant (t): 171.8 49.6 18.2
Propellant: Nitrogen tetroxide/UDMH LOX/LH2
Engine Type: DaFY5-1 DaFY6-2 DaFY20-1 (Main) YF-75
DaFY21-1 (Vernier)
Engine Thrust (kN): 740.4x4 2961.6 742 (Main) 78.5x2
11.8x4 (Vernier)
Lift-off Mass (t): 426
Overall Length (m): 54.838
Fairing Diameter (m): 4.00
Long March 3C Launch Vehicle (LM-3C or CZ-3C)
The LM-3C is a three-stage launch vehicle. It differs from the LM-3B in its use of two strap-on boosters in its first stage rather than four. The LM-3C is launched from Xichang Satellite Launch Center (XSLC). The LM-3C can be used to deploy payloads into GTO.
Technical Specifications
Boosters 1st Stage 2st Stage 3rd Stage
Diameter (m): 2.25 3.35 3.35 3.00
Mass of Propellant (t):
Propellant: N2O4/UDMH N2O4/UDMH N2O4/UDMH LOX/LH2
Engine Type: DaFY5-1 DaFY6-2 DaFY20-1(main) YF-75
DaFY-21-1(Vernier)
Engine Thrust (kN): 740.4x2 2961.6 742 (Main) 78.5x2
11.8x4 (Vernier)
Lift-off Mass (t): 345
Overall Length (m): 54.838
Fairing Diameter (m) 4.00
Long March 4 Launch Vehicle (LM-4 or CZ-4)
The LM-4 is a three-stage launch vehicle. The first and second stages are adapted from the LM-3, with a liquid propellant third stage. The LM-4 can deploy a 2,790 kilogram payload into sun synchronous orbit (SSO), a 1,419 kilogram payload into geosynchronous transfer orbit (GTO), or a 4,595 kilogram payload into low earth orbit (LEO). The LM-4 is launched from Taiyuan Satellite Launch Center. It was first launched in September 1988.
Technical Specifications
1st Stage 2nd Stage 3rd Stage
Diameter (m): 3.35 3.35 2.90
Mass of Propellant (t): 182.07 35.408 14.3
Propellant: Nitrogen tetroxide/UDMH
Engine Type: DaYF-21B YF-22B (Main) YF-40A
YF-23 (Vermier)
Engine Thrust (kN): 2962 742 (Main) 100.8
46.1 (Vernier)
Lift-off Mass (t): 249.2
Overall Length (m): 45.8
Fairing Diameter (m): 2.90/3.35
Small Launch Vehicle J-1
Small Launch Vehicle J-1 is a small three-stage launch vehicle with an orbit-maneuver motor. It is used to launch small satellites into LEO or SSO. The Small Launch Vehicle conducted its first test flight in 1997.
Technical Specifications
1st Stage 2nd Stage 3rd Stage OM Motor
Diameter (m) 2.25 2.25 2.05
Mass of Propellant (t):
Propellant: N2O4/HNO3 N2O4/HNO3 HTPB HTPB
Engine Type: YF-2A YF-3 SPAB-14B OM-1
Engine Thrust (kN): 1101.29 320.19 161.5 7.93
Lift-off Mass (t): 85.42
Overall Length (m): 31.28