Heavy-lift launch vehicle
Launch vehicle capable of lifting over 20,000 kg into low Earth orbit
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A heavy-lift launch vehicle (HLV) is an orbital launch vehicle capable of lifting payloads between 20,000 to 50,000 kg (44,000 to 110,000 lb) (by NASA classification) or between 20,000 to 100,000 kilograms (44,000 to 220,000 lb) (by Russian classification)[1] into low Earth orbit (LEO).[2] Heavy-lift launch vehicles often carry payloads into higher-energy orbits, such as geosynchronous transfer orbit (GTO) or heliocentric orbit (HCO).[3] An HLV is between a medium-lift launch vehicle and a super heavy-lift launch vehicle.
| Class overview | |
|---|---|
| Name | Heavy-lift launch vehicle |
| Preceded by | Medium-lift launch vehicle |
| Succeeded by | Super heavy-lift launch vehicle |
| Built | Since 1966 |
| General characteristics | |
| Capacity | 20,000 to 50,000 kg (44,000 to 110,000 lb) |
History and design

Government
The first heavy-lift launch vehicles in the 1960s included the US Saturn IB and the Soviet Proton. Saturn IB was designed to carry the Apollo spacecraft into orbit and had increased engine thrust and a redesigned second stage from its predecessor. Proton was originally designed to be a large intercontinental ballistic missile (ICBM).[4] Russia still operates variants of the Proton as of 2024[update], although it is expected to be phased out in favor of the Angara A5.
NASA introduced the Space Shuttle as the first partially reusable launch vehicle in 1981. The Space Shuttle carried up to eight crew members in addition to deploying heavy payloads to LEO, including space station modules and Department of Defense payloads. Higher-energy orbits for payloads were reached through the use of a kick stage such as the Inertial Upper Stage.
The United States Air Force (USAF) operated the Titan IV to supplement Space Shuttle launches. This was derived from the Titan family of ICBMs and launch vehicles, with upgrades including solid rocket boosters (SRBs), vehicle lengthening, and an optional third stage.[5] The USAF began the Evolved Expendable Launch Vehicle (EELV) program in 1994 to ensure access to space through contracted launch providers. This led to the development of the Delta IV, with the heavy variant using three first stage cores. United Launch Alliance (ULA) introduced Vulcan Centaur in 2024 as the successor to its Delta IV and Atlas V rockets, with Vulcan featuring a single, wider core and optional SRBs.
China's Long March 5 was introduced in 2016 as the most powerful version of the Long March family. It is notable as a Chinese launch vehicle using non-hypergolic liquid propellants.[6]
Commercial

The European Ariane 5 first flew in 1996 and launched many commercial payloads to GTO. It benefited in this role by launching from Guiana Space Center, a spaceport near the equator in French territory. Ariane 5 often carried multiple payloads per launch and set records for mass to GTO delivered for commercial payloads.
Falcon 9 was introduced by SpaceX in 2010, designed as a medium-lift launch vehicle with a reusable first stage.[a] Falcon 9 grew more capable through iterative design, with upgrades including improved Merlin engines and the lengthening of both stages. Since the introduction of Falcon 9 Full Thrust in 2015, the vehicle meets the capacity requirements of a heavy-lift vehicle when the first stage is expended. In 2021, Falcon 9 carried a record of 143 satellites into orbit on a single launch.[7] Falcon Heavy uses three first stage boosters similarly to Delta IV Heavy, but requires a strengthened center core. Falcon Heavy made its first flight in 2017 and was most capable operational launch vehicle until NASA's SLS launched in 2022.[8] Falcon Heavy is categorized as a heavy-lift launch vehicle when flown in configuration to recover the center core and both side boosters. When expending the center core or all boosters, its payload to LEO exceeds 50,000 kg, qualifying Falcon Heavy as a super heavy-lift launch vehicle.
Rated launch vehicles
| Rocket | Configuration | Organization | Nationality | Liftoff thrust | Mass to LEO | Maiden successful flight | Heaviest known launch | Status | Reusable | Launches (success / total) |
Cost per launch (adjusted for inflation) | ||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| ...to LEO or MEO | ...to GTO or GSO | ...to HEO and beyond | |||||||||||
| Saturn IB | NASA | 7,100 kN (1,600,000 lbf) | 21,000 kg (46,000 lb) | 1966 | 20,847 kg (45,960 lb) | N/a | N/a | Retired (1975) | No | 9 / 9 | US$413 million[9] | ||
| Proton | K | Khrunichev | 10,470 kN (2,350,000 lbf) | 19,760 kg (43,560 lb)[10][b] | 1967 | 22,776 kg (50,212 lb) | 4,723 kg (10,412 lb) | 6,220 kg (13,710 lb) | Retired (2017) | No | 275 / 310 | US$65 million[12] | |
| M | 10,532 kN (2,368,000 lbf) | 23,000 kg (51,000 lb)[13] | 2001 | 20,350 kg (44,860 lb) | 6,740 kg (14,860 lb) | 3,755 kg (8,278 lb) | Operational | No | 104 / 115 | US$65 million[12] | |||
| Space Shuttle | USA | 28,750 kN (6,460,000 lbf) | 27,500 kg (60,600 lb)[c][14] | 1981 | 22,753 kg (50,162 lb) | Classified[d][e] | 3,455 kg (7,617 lb) | Retired (2011) | Partially | 133 / 135 | US$601 million[15] | ||
| Titan IV | Lockheed Martin | 15,120 kN (3,400,000 lbf) | 21,380 kg (47,130 lb)[16] | 1989 | ≥ 19,600 kg (43,200 lb)[d][f] | Classified[d] | 5,712 kg (12,593 lb) | Retired (2005) | No | 35 / 39 | US$432 million | ||
| Ariane 5 | ECA/ES | Ariane Group | 15,175 kN (3,411,000 lbf) | 21,000 kg (46,000 lb)[18] | 1998 | 20,293 kg (44,738 lb)[19] | 11,210 kg (24,710 lb)[20] | 6,161.4 kg (13,584 lb)[21] | Retired (2023) | No | 90 / 92 | US$200 million[22] | |
| Delta IV Heavy | ULA | 9,420 kN (2,120,000 lbf) | 28,790 kg (63,470 lb)[23] | 2007 | 21,000 kg (46,000 lb)[24] | Classified[d] | 685 kg (1,510 lb) | Retired (2024) | No | 15 / 16 | US$350 million[25] | ||
| Angara A5 | Angara-A5 | Khrunichev, KBKhA | 9,600 kN (2,200,000 lbf) | 24,500 kg (54,000 lb)[26] | 2014 | N/a | 2,400 kg (5,300 lb)[27] | N/a | Operational | No | 4 / 5 | US$100 million (2021) [28] | |
| Angara-A5V | Khrunichev, Polyot | 38,000 kg (84,000 lb) | N/a | N/a | N/a | N/a | Under development | No | — | ? | |||
| Falcon 9 FT | Expended | SpaceX | 7,600 kN (1,700,000 lbf) | 22,800 kg (50,300 lb) | 2017 | 17,400 kg (38,400 lb)[29] | 7,076 kg (15,600 lb)[30] | 1,108 kg (2,443 lb) | Operational | No | 30 / 30 | US$69.7 million | |
| Long March 5/5B | CALT | 10,636 kN (2,391,000 lbf) | 25,000 kg (55,000 lb)[31] | 2016 | 23,200 kg (51,100 lb)[32] | 14,000 kg (31,000 lb)[33] | 8,350 kg (18,410 lb)[34] | Operational | No | 14 / 15 | US$160 million[35][36] | ||
| Falcon Heavy | Recoverable boosters and first stage | SpaceX | 22,800 kN (5,100,000 lbf) | >38,000 kg (84,000 lb)[37] | 2018 | 3,700 kg (8,200 lb) | 6,465 kg (14,253 lb)[38] | ~1,250 kg (2,760 lb) | Operational | Partially | 3 / 3 | US$95 million[39] | |
| Starship | Block 1 | SpaceX | 69,627 kN (15,653,000 lbf) | 15,000 kg (33,000 lb)[40] | 2024 | N/a | N/a | N/a | Retired (2024) | No | 4 / 6 | ? | |
| Block 2 | 69,627 kN (15,653,000 lbf) | 35,000 kg (77,000 lb)[40] | 2025 | N/a | N/a | N/a | Retired (2025) | Partially | 2 / 5 | ? | |||
| Vulcan Centaur | VC4 | ULA | 13,137 kN (2,953,000 lbf) | 21,400 kg (47,200 lb) | 2025 | N/a | 1,250 kg (2,760 lb) | N/a | Operational | Planned (partial) | 1 / 1 | US$110 million[41] | |
| VC6 | 17,259 kN (3,880,000 lbf) | 27,200 kg (60,000 lb)[42] | N/a | N/a | N/a | N/a | Under development | Planned (partial) | — | ||||
| New Glenn | Blue Origin | 17,100 kN (3,800,000 lbf) | 45,000 kg (99,000 lb)[43] | 2025 | Unknown | N/a | N/a | Operational | Partial | 2 / 2 | US$68-110 million[44][45] | ||
| Ariane 6 | A64 | Ariane Group | 15,370 kN (3,460,000 lbf) | 21,650 kg (47,730 lb)[46] | 2024 | 4,040 kg (8,910 lb)[47] | N/a | N/a | Operational | Planned (partially) | 4 / 4 | US$133 million[48] | |
| Zhuque-3E | LandSpace | 7,200 kN (1,600,000 lbf) | 25,600 kg (56,400 lb) | 2025 | N/a | N/a | N/a | Operational | Planned (partially) | 1 / 1 | ? | ||
| Gravity-2 | Orienspace | ? | 21,000 kg (46,000 lb) | N/a | N/a | N/a | N/a | Under development | Planned (partially) | — | ? | ||
| Terran R | Relativity Space | 15,480 kN (3,480,000 lbf) | 33,500 kg (73,900 lb) | N/a | N/a | N/a | N/a | Under development | Planned (partially) | — | ? | ||
| NGLV | NGLV | ISRO | ? | 23,000 kg (51,000 lb) | N/a | N/a | N/a | N/a | Under development | Planned (partially) | — | ? | |
| NGLV-H | ? | 31,700 kg (69,900 lb) | N/a | N/a | N/a | N/a | Under development | Planned (partially) | — | ? | |||
| Miura Next Heavy | Expended | PLD Space | 16,600 kN (3,700,000 lbf) | 36,000 kg (79,000 lb)[49] | N/a | N/a | N/a | N/a | Under development | Planned (partially) | — | ? | |
Notes
- The first successful landing of a Falcon 9 first stage occurred in 2015
- excluding orbiter mass
- Actual payloads flown are classified under the NRO launch program.
- The Space Shuttle deployed payloads with an attached Inertial Upper Stage to reach orbits beyond LEO
See also
- Comparison of orbital launch systems
- Comparison of orbital rocket engines
- Comparison of space station cargo vehicles
- List of orbital launch systems
- Sounding rocket, suborbital launch vehicle
- Small-lift launch vehicle, capable of lifting up to 2,000 kg (4,400 lb) to low Earth orbit
- Medium-lift launch vehicle, capable of lifting between 2,000 and 20,000 kg (4,400 and 44,100 lb) to low Earth orbit
- Super heavy-lift launch vehicle, capable of lifting more than 50,000 kg (110,000 lb) to Low Earth orbit