Function | Heavy-lift launch vehicle |
---|---|
Manufacturer | CALT |
Country of origin | China |
Cost per launch | ~US$70 million [1] |
Size | |
Height | 56.97 m (186.9 ft) (standard) 63.2 m (207 ft) (extended fairing) |
Diameter | 5 m (16 ft) |
Mass | 851,800 kg (1,877,900 lb) |
Stages | 2 |
Payload to LEO | |
Altitude | 200 km × 400 km (120 mi × 250 mi) |
Mass | 25,000 kg (55,000 lb) [2][3] |
Payload to GTO | |
Mass | 14,000 kg (31,000 lb) [2][3] |
Payload to TLI | |
Mass | 8,800–9,400 kg (19,400–20,700 lb) |
Payload to GEO | |
Mass | 5,100 kg (11,200 lb) |
Payload to SSO | |
Altitude | 700 km (430 mi) |
Mass | 15,000 kg (33,000 lb) |
Payload to SSO | |
Altitude | 2,000 km (1,200 mi) |
Mass | 6,700 kg (14,800 lb) |
Payload to MEO | |
Mass | 13,000 kg (29,000 lb) |
Payload to TMI | |
Mass | 6,000 kg (13,000 lb) |
Associated rockets | |
Family | Long March |
Comparable | |
Launch history | |
Status | Active |
Launch sites | Wenchang, LC-1 |
Total launches | 12
|
Success(es) | 11
|
Failure(s) | 1 (CZ-5)
|
First flight | |
Last flight |
|
Type of passengers/cargo | Mengzhou, Chang'e 5, Tianwen 1, Tianhe, Wentian, Mengtian, Chang'e 6 |
Boosters – CZ-5-300[6] | |
No. boosters | 4 |
Height | 27.6 m (91 ft) |
Diameter | 3.35 m (11.0 ft) |
Empty mass | 13,800 kg (30,400 lb) |
Gross mass | 156,600 kg (345,200 lb) |
Powered by | 2 YF-100 |
Maximum thrust | Sea level: 2,400 kN (540,000 lbf) Vacuum: 2,680 kN (600,000 lbf) |
Total thrust | 9,600 kN (2,200,000 lbf) |
Specific impulse | Sea level: 300 s (2.9 km/s) Vacuum: 335.1 s (3.286 km/s) |
Burn time | 173 seconds |
Propellant | RP-1 / LOX |
First stage – CZ-5-500[6] | |
Height | 33.16 m (108.8 ft) |
Diameter | 5 m (16 ft) |
Gross mass | 186,900 kg (412,000 lb) |
Propellant mass | 165,300 kg (364,400 lb) |
Powered by | 2 YF-77 |
Maximum thrust | Sea level: 1,036 kN (233,000 lbf) Vacuum: 1,400 kN (310,000 lbf) |
Specific impulse | Sea level: 316.7 s (3.106 km/s) Vacuum: 428 s (4.20 km/s) |
Burn time | 492 seconds |
Propellant | LH2 / LOX |
Second stage (CZ-5) – CZ-5-HO[6] | |
Height | 11.54 m (37.9 ft) |
Diameter | 5 m (16 ft) |
Empty mass | 5,100 kg (11,200 lb) |
Gross mass | 36,000 kg (79,000 lb) |
Propellant mass | 29,100 kg (64,200 lb) |
Powered by | 2 YF-75D |
Maximum thrust | 176.72 kN (39,730 lbf) |
Specific impulse | 442.6 s (4.340 km/s) |
Burn time | 700 seconds |
Propellant | LH2 / LOX |
Third stage – YZ-2 (Optional) | |
Diameter | 3.8 m (12 ft) |
Powered by | 2 YF-50D |
Maximum thrust | 13 kN (2,900 lbf) |
Specific impulse | 316 s (3.10 km/s) |
Burn time | 1105 seconds |
Propellant | N2O4 / UDMH |
Long March 5 (LM-5; Chinese: 长征五号; pinyin: Chángzhēng wǔ hào), or Changzheng 5 (CZ-5), and also by its nickname "Pang-Wu" (胖五, "Fat-Five"),[7] is a Chinese heavy-lift launch vehicle developed by the China Academy of Launch Vehicle Technology (CALT). It is the first Chinese launch vehicle designed to use exclusively non-hypergolic liquid propellants.[8] It is the fifth iteration of the Long March rocket family.
There are currently two CZ-5 variants: CZ-5 and CZ-5B. The maximum payload capacities are approximately 25,000 kg (55,000 lb) to low Earth orbit[9] (for CZ-5B) and approximately 14,000 kg (31,000 lb) to geostationary transfer orbit (for CZ-5).[10][11]
The Long March 5 roughly matches the capabilities of American NSSL heavy-lift launch vehicles such as the Delta IV Heavy. It is currently the most powerful member of the Long March rocket family and the world's third most powerful orbital launch vehicle currently in operation, trailing the United States' Falcon Heavy and Space Launch System.[12]
The first CZ-5 launched from Wenchang Space Launch Site on 3 November 2016 and placed its payload in a suboptimal but workable initial orbit. The second CZ-5 rocket, launched on 2 July 2017, failed due to an engine problem in the first stage.[13]
After an interval of almost two and a half years, the Long March 5 successfully returned to flight with its third launch on 27 December 2019, which placed the experimental Shijian-20 communications satellite into geostationary transfer orbit, thereby paving the way for the ultimately successful launch of the Tianwen 1 Mars mission, the lunar Chang'e 5 sample-return mission, and the modular space station,[5] all of which required the lift capacity of a heavy lift launch vehicle.
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