Function | Launch vehicle |
---|---|
Manufacturer | China Academy of Launch Vehicle Technology (CALT) |
Country of origin | China |
Cost per launch | US$50-70 million [1][2][3] |
Size | |
Height | |
Diameter | 3.35 m (11.0 ft) [4] |
Mass |
|
Stages | 3 / 4 |
Capacity | |
Payload to LEO | |
Mass | 11,500 kg (25,400 lb) [6][7] |
Payload to SSO | |
Mass | 7,100 kg (15,700 lb) [6][7] |
Payload to GTO | |
Mass | |
Payload to GEO | |
Mass | 2,000 kg (4,400 lb) [7] |
Payload to HCO | |
Mass | 3,300 kg (7,300 lb) [6][7] |
Associated rockets | |
Family | Long March |
Derivative work | Long March 3C |
Comparable | |
Launch history | |
Status |
|
Launch sites | Xichang LC-2, LC-3 |
Total launches |
|
Success(es) |
|
Failure(s) |
|
Partial failure(s) |
|
First flight |
|
Last flight |
|
Type of passengers/cargo | |
Boosters (3B) | |
No. boosters | 4 |
Height | 15.33 m (50.3 ft) |
Diameter | 2.25 m (7 ft 5 in) |
Propellant mass | 37,700 kg (83,100 lb) |
Powered by | 1 × YF-25 |
Maximum thrust | 740.4 kN (166,400 lbf) |
Specific impulse | 2,556.2 m/s (260.66 s) |
Burn time | 127 seconds |
Propellant | N2O4 / UDMH |
Boosters (3B/E) | |
No. boosters | 4 |
Height | 16.1 m (53 ft) |
Diameter | 2.25 m (7 ft 5 in) |
Propellant mass | 41,100 kg (90,600 lb) |
Powered by | 1 × YF-25 |
Maximum thrust | 740.4 kN (166,400 lbf) |
Specific impulse | 2,556.2 m/s (260.66 s) |
Burn time | 140 seconds |
Propellant | N2O4 / UDMH |
First stage (3B) | |
Height | 23.27 m (76.3 ft) |
Diameter | 3.35 m (11.0 ft) |
Propellant mass | 171,800 kg (378,800 lb) |
Powered by | 4 × YF-21C |
Maximum thrust | 2,961.6 kN (665,800 lbf) |
Specific impulse | 2,556.5 m/s (260.69 s) |
Burn time | 145 seconds |
Propellant | N2O4 / UDMH |
First stage (3B/E) | |
Height | 24.76 m (81.2 ft) |
Diameter | 3.35 m (11.0 ft) |
Propellant mass | 186,200 kg (410,500 lb) |
Powered by | 4 × YF-21C |
Maximum thrust | 2,961.6 kN (665,800 lbf) |
Specific impulse | 2,556.5 m/s (260.69 s) |
Burn time | 158 seconds |
Propellant | N2O4 / UDMH |
Second stage | |
Height | 12.92 m (42.4 ft) |
Diameter | 3.35 m (11.0 ft) |
Propellant mass | 49,400 kg (108,900 lb) |
Powered by | |
Maximum thrust |
|
Specific impulse |
|
Burn time | 185 seconds |
Propellant | N2O4 / UDMH |
Third stage | |
Height | 12.38 m (40.6 ft) |
Diameter | 3.0 m (9.8 ft) |
Propellant mass | 18,200 kg (40,100 lb) |
Powered by | 2 × YF-75 |
Maximum thrust | 167.17 kN (37,580 lbf) |
Specific impulse | 4,295 m/s (438.0 s) |
Burn time | 478 seconds |
Propellant | LH2 / LOX |
Fourth stage (optional) – YZ-1 | |
Powered by | 1 × YF-50D |
Maximum thrust | 6.5 kN (1,500 lbf) |
Specific impulse | 315.5 s (3.094 km/s) |
Propellant | N2O4 / UDMH |
The Long March 3B (Chinese: 长征三号乙; pinyin: Chángzhēng sānhàoyǐ), also known as the CZ-3B and LM-3B, is a Chinese orbital launch vehicle. Introduced in 1996, it is launched from Launch Area 2 and 3 at the Xichang Satellite Launch Center in Sichuan. A three-stage rocket with four strap-on liquid rocket boosters, it is the heaviest variant of the Long March 3 rocket family, and is mainly used to place communications satellites and navigation satellites into geosynchronous orbits.
An enhanced version, the Long March 3B/E or G2, was introduced in 2007 to increase the rocket's geostationary transfer orbit (GTO) cargo capacity and lift heavier geosynchronous orbit (GEO) communications satellites. The Long March 3B also served as the basis for the medium-capacity Long March 3C, which was first launched in 2008.
As of 10 October 2024[update], the Long March 3B, 3B/E and 3B/G5 have conducted 95 successful launches, plus 2 failures and 2 partial failures, accumulating a success rate of 96%.