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Super heavy-lift launch vehicle

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Super heavy-lift launch vehicles, to scale
Class overview
NameSuper heavy-lift launch vehicle
Preceded byHeavy-lift launch vehicle
BuiltSince 1967
General characteristics
Capacity
    • US definition: >50,000 kg (110,000 lb)
    • Russian definition: >100,000 kg (220,000 lb)

A super heavy-lift launch vehicle is a rocket that can lift to low Earth orbit a "super heavy payload", which is defined as more than 50 metric tons (110,000 lb)[1][2] by the United States and as more than 100 metric tons (220,000 lb) by Russia.[3] It is the most capable launch vehicle classification by mass to orbit, exceeding that of the heavy-lift launch vehicle classification.

Only 14 such payloads were successfully launched before 2022: 12 as part of the Apollo program before 1972 and two Energia launches, in 1987 and 1988. Most planned crewed lunar and interplanetary missions depend on these launch vehicles.

Several super heavy-lift launch vehicle concepts were produced in the 1960s,[4] including the Sea Dragon. During the Space Race, the Saturn V and N1 were built by the United States and Soviet Union, respectively. After the Saturn V's successful Apollo program and the N1's failures, the Soviets' Energia launched twice in the 1980s, once bearing the Buran spaceplane. The next two decades saw multiple concepts drawn out once again, most notably Space Shuttle-derived vehicles and Rus-M, but none were built. In the 2010s, super heavy-lift launch vehicles received interest once again, leading to the launch of the Falcon Heavy, the Space Launch System, and Starship, and the beginning of development of the Long March and Yenisei rockets.

Flown vehicles

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Retired

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  • Saturn V was a NASA launch vehicle that made 13 orbital launches between 1967 and 1973, principally for the Apollo program through 1972. The Apollo lunar payload included a command module, service module, and Lunar Module, with a total mass of 45 t (99,000 lb).[5][6] When the third stage and Earth-orbit departure fuel was included, Saturn V placed approximately 140 t (310,000 lb) into low Earth orbit.[7] The final launch of Saturn V in 1973 placed Skylab, a 77-tonne (170,000 lb) payload, into LEO.
  • The Energia launcher was designed by the Soviet Union to launch up to 105 t (231,000 lb) to low Earth orbit.[8] Energia launched twice in 1987/88 before the program was cancelled by the Russian government, which succeeded the Soviet Union, but only the second flight payload reached orbit. On the first flight, launching the Polyus weapons platform (approximately 80 t (180,000 lb)), the vehicle failed to enter orbit due to a software error on the kick-stage.[8] The second flight successfully launched the Buran orbiter.[9] Buran was intended to be reusable, similar to the Space Shuttle Orbiter, but it relied entirely on the disposable launcher Energia to reach orbit.

Operational

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Under development

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  • Starship is a two-stage-to-orbit fully reusable launch vehicle being privately developed by SpaceX, consisting of the Super Heavy booster as the first stage and a second stage, also called Starship.[22][23] It is designed to be a long-duration cargo and passenger-carrying spacecraft.[24] After two failed flight tests,[25][26] Starship completed its first successful launch on its third flight on March 14, 2024,[27] and achieved soft landing of both stages on its fourth flight.[28]
  • The Long March 9 is a Chinese three-stage-to-orbit partially reusable launch vehicle currently being developed by the China Academy of Launch Vehicle Technology. The design has undergone numerous major changes over the years and with the most recent designs showing some resemblance to the SpaceX Starship. The Long March 9 is planned to be operational by the early 2030s.[29]
  • The Long March 10 is a Chinese three-stage-to-orbit partially reusable launch vehicle currently being developed by the China Academy of Launch Vehicle Technology with an initial launch targeting the 2025–2027 time range.

Unsuccessfully flown

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  • The N1 was a three-stage super heavy lift launch vehicle developed in the Soviet Union from 1965 to 1974. It was the Soviet counterpart to the Saturn V, however all four test flights of the vehicle ended in flight failure. For lunar missions, it would carry the L3 crewed lunar payload into Low Earth Orbit, which had an additional two stages, a Soyuz 7K-LOK as a mothership and an LK lunar lander that would be used for crewed lunar landings. Its Block A first stage held the record for the most thrust of any rocket stage built until it was superseded by the Super Heavy booster on its first flight.

Comparison

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Rocket Configuration Organization Nationality Human rated Max First Stage Thrust Mass to LEO Maiden successful orbital flight First >50 t payload Status Reusable Launches
(success / total) 		Launch cost Launch cost
(2020, US$ in millions) 		Cost / t
(2020, US$ in millions)
Saturn V Apollo/Skylab NASA  United States Yes 34,500 kN
(7,750,000 lbf) 		140 t (310,000 lb)A 1967 1967 Retired
(1973) 		No 12G / 13 US$1.23 billion (2019) US$1,245 $8.9
N1 OKB-1  Soviet Union Not achieved 45,400 kN
(10,200,000 lbf) 		95 t (209,000 lb) None None Cancelled (1974) No 0 / 4 3 billion RUB (1971) US$1,500[30] $16
Energia NPO Energia Not achieved 34,800 kN
(7,800,000 lbf) 		100 t (220,000 lb)B 1988B 1987 Retired
(1988) 		No 2 / 2 US$764 million (1985) US$1,838 $18
Falcon Heavy Recoverable Side Boosters SpaceX  United States No 22,800 kN
(5,100,000 lbf) 		57 t (126,000 lb)[10] 2022 Not yet Operational but mass untested PartiallyC 6 / 6F US$90 million (2018) US$92 $1.6
Expended No 63.8 t (141,000 lb)[31] 2023 Not yet Operational but mass untested No 2 / 2F US$150 million (2018) US$154 $2.4
SLS Block 1 NASA Yes 39,000 kN
(8,800,000 lbf) 		95 t (209,000 lb)[32]D 2022 2022 Operational No 1 / 1 US$2.2 billion (2021) US$2,100 $22.1
Block 1B Planned 105 t (231,000 lb)[33] Planned (2028) — Under development No — ? ? ?
Block 2 Planned 41,000 kN
(9,200,000 lbf) 		130 t (290,000 lb)[34] Planned (2031) — Under development No — ? ? ?
Starship Block 1 SpaceX No 73.5 MN (16,500,000 lbf)[35] 100 t (220,000 lb)[36]E 2024J None Retired
(2024) 		Partially (reuse untested)K 4 / 6 Projected US$<90 million (2024)[37]I US$<75 $<0.75
Block 2 Unknown 80.8 MN (18,200,000 lbf)[38] 150 t (330,000 lb)[36]E Planned (2025) — Under development Planned (fully) — Projected US$<10 million (2024)[37]I US$<8.4 $<0.056
Block 3 Planned 98 MN (22,000,000 lbf)[38] 200 t (440,000 lb)[39]E TBA — Under development Planned (fully) — Projected US$<6 million (2024)[39] US$<5 $<0.025
Long March 10 CALT  China Planned 26,250 kN
(5,900,000 lbf) 		70 t (150,000 lb)[40] Planned (2027) — Under development No — ? ? ?
Long March 9 Planned 60,000 kN
(13,490,000 lbf) 		150 t (330,000 lb)[41] Planned (2033) — Under development Planned (partially) — ? ? ?
Yenisei Yenisei Progress  Russia Planned 43,500 kN
(9,780,000 lbf) 		103 t (227,000 lb) TBA — Under development No — ? ? ?
Don Planned 130 t (290,000 lb) TBA — Under development No — ? ? ?

^A Includes mass of Apollo command and service modules, Apollo Lunar Module, Spacecraft/LM Adapter, Saturn V Instrument Unit, S-IVB stage, and propellant for translunar injection; payload mass to LEO is about 122.4 t (270,000 lb).[42]
^B Required upper stage or payload to perform final orbital insertion.
^C Side booster cores recoverable, center core intentionally expended. First re-use of the side boosters was demonstrated in 2019 when the ones used on the Arabsat-6A launch were reused on the STP-2 launch.
^D Includes mass of Orion spacecraft, European Service Module, Interim Cryogenic Propulsion Stage, and propellant for translunar injection.
^E Does not include dry mass of spaceship.
^F Falcon Heavy has launched 11 times since 2018, but first three times did not qualify as a "super heavy" because recovery of the center core was attempted.
^G Apollo 6 was a "partial failure": It reached orbit, but had problems with the second and third stages.
^I Estimate by third party.
^J Flight 6 entered a Transatmospheric Earth orbit, an orbit, though one that results in rapid decay and reentry.
^K Block 1 boosters were proven to be recoverable in a state permitting reuse on Starship flight test 5, but it was decided they would not be reused regardless.

Proposed designs

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Chinese proposals

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Long March 10 was first proposed in 2018 as a concept for the Chinese Lunar Exploration Program.[43] Long March 9, an over 150 t (330,000 lb) to LEO capable rocket was proposed in 2018[44] by China, with plans to launch the rocket by 2028. The length of the Long March-9 will exceed 114 meters, and the rocket would have a core stage with a diameter of 10 meters. Long March 9 is expected to carry a payload of over 150 tonnes into low-Earth orbit, with a capacity of over 50 tonnes for Earth-Moon transfer orbit.[45][46] Development was approved in 2021.[47]

Russian proposals

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Yenisei,[48] a super heavy-lift launch vehicle using existing components instead of pushing the less-powerful Angara A5V project, was proposed by Russia's RSC Energia in August 2016.[49]

A revival of the Energia booster was proposed in 2016, also to avoid pushing the Angara project.[50] If developed, this vehicle could allow Russia to launch missions towards establishing a permanent Moon base with simpler logistics, launching just one or two 80-to-160-tonne super-heavy rockets instead of four 40-tonne Angara A5Vs implying quick-sequence launches and multiple in-orbit rendezvous. In February 2018, the КРК СТК (space rocket complex of the super-heavy class) design was updated to lift at least 90 tonnes to LEO and 20 tonnes to lunar polar orbit, and to be launched from Vostochny Cosmodrome.[51] The first flight is scheduled for 2028, with Moon landings starting in 2030.[52] It looks like this proposal has been at least paused.[53]

US proposals

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Blue Origin has plans for a project following their New Glenn rocket, termed New Armstrong, which some media sources have speculated will be a larger launch vehicle.[54]

Cancelled designs

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Comparison of Saturn V, Sea Dragon and Interplanetary Transport System
Comparison of Space Shuttle, Ares I, Saturn V and Ares V

Numerous super-heavy-lift vehicles have been proposed and received various levels of development prior to their cancellation.

As part of the Soviet crewed lunar project to compete with Apollo/Saturn V, the N1 rocket was secretly designed with a payload capacity of 95 t (209,000 lb). Four test vehicles were launched from 1969 to 1972, but all failed shortly after lift-off.[55] The program was suspended in May 1974 and formally cancelled in March 1976.[56][57] The Soviet UR-700 rocket design concept competed against the N1, but was never developed. In the concept, it was to have had a payload capacity of up to 151 t (333,000 lb)[58] to low earth orbit.

During project Aelita (1969–1972), the Soviets were developing a way to beat the Americans to Mars. They designed the UR-700A, a nuclear powered variant of the UR-700, and UR-700M, a LOx/Kerosene variant to assemble the 1,400 t (3,100,000 lb) MK-700 spacecraft in earth orbit in two launches. The UR-700M would have a payload capacity of 750 t (1,650,000 lb).[59] The only Universal Rocket to make it past the design phase was the UR-500 while the N1 was selected to be the Soviets' HLV for lunar and Martian missions.[60]

The UR-900, proposed in 1969, would have had a payload capacity of 240 t (530,000 lb) to low earth orbit. It never left the drawing board.[61]

The General Dynamics Nexus was proposed in the 1960s as a fully reusable successor to the Saturn V rocket, having the capacity of transporting up to 450–910 t (990,000–2,000,000 lb) to orbit.[62][63]

The American Saturn MLV family of rockets was proposed in 1965 by NASA as successors to the Saturn V rocket.[64] It would have been able to carry up to 160,880 kg (354,680 lb) to low Earth orbit. The Nova designs were also studied by NASA before the agency chose the Saturn V in the early 1960s[65] Nova was cancelled in 1964 and had reusable variants.[66]

Based on the recommendations of the Stafford Synthesis report, First Lunar Outpost (FLO) would have relied on a massive Saturn-derived launch vehicle known as the Comet HLLV. The Comet would have been capable of injecting 230.8 t (508,800 lb) into low earth orbit and 88.5 t (195,200 lb) on a TLI making it one of the most capable vehicles ever designed.[67] FLO was cancelled during the design process along with the rest of the Space Exploration Initiative.[citation needed]

The U.S. Ares V for the Constellation program was intended to reuse many elements of the Space Shuttle program, both on the ground and flight hardware, to save costs. The Ares V was designed to carry 188 t (414,000 lb) and was cancelled in 2010.[68]

The Shuttle-Derived Heavy Lift Launch Vehicle ("HLV") was an alternate super heavy-lift launch vehicle proposal for the NASA Constellation program, proposed in 2009.[69]

A 1962 design proposal, Sea Dragon, called for an enormous 150 m (490 ft) tall, sea-launched rocket capable of lifting 550 t (1,210,000 lb) to low Earth orbit. Although preliminary engineering of the design was done by TRW, the project never moved forward due to the closing of NASA's Future Projects Branch.[70][71]

The Rus-M was a proposed Russian family of launchers whose development began in 2009. It would have had two super heavy variants: one able to lift 50–60 tons, and another able to lift 130–150 tons.[72]

SpaceX Interplanetary Transport System was a 12 m (39 ft) diameter launch vehicle concept unveiled in 2016. The payload capability was to be 550 t (1,210,000 lb) in an expendable configuration or 300 t (660,000 lb) in a reusable configuration.[73] In 2017, the 12 m evolved into a 9 m (30 ft) diameter concept Big Falcon Rocket, which became the SpaceX Starship.[74]

See also

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Notes

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  1. ^ A configuration in which all three cores are intended to be recoverable is classified as a heavy-lift launch vehicle since its maximum possible payload to LEO is under 50,000 kg.[12][11]

References

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