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SLS and Starship are not competing rockets for the same leg of a mission. NASA’s Space Launch System (SLS) launches Orion, astronauts and cargo from Earth toward the Moon. Starship Human Landing System (HLS) is being developed to take astronauts from lunar orbit to the surface and back for Artemis III and Artemis IV. SLS has published NASA payload figures; Starship’s relevant lunar and launch capabilities are still being demonstrated.
The short answer: complementary systems, not a replacement contest
The most important distinction is where each vehicle operates. SLS is the heavy-lift launcher for the Earth-to-Moon segment of NASA’s Artemis architecture. Orion rides on SLS, receives the crew at launch and carries them toward lunar orbit. Starship HLS is the planned lander for the next segment: it meets the crew in lunar orbit, descends to the Moon, supports surface operations and returns them to lunar orbit.
That division means a direct “which rocket wins?” comparison can be misleading. SLS has a NASA-published translunar-injection (TLI) capability. Starship HLS is being evaluated as a lunar landing system, and the cited NASA material does not provide a complete, current, like-for-like Starship payload figure for either launch or lunar-surface delivery. Treating an unverified Starship estimate as an operational specification would overstate what is known.
At a glance
| Comparison point | SLS | Starship HLS |
|---|---|---|
| Primary Artemis role | Launches Orion, crew and cargo from Earth toward the Moon | Transports astronauts between lunar orbit and the lunar surface |
| Payload figure published in the cited NASA material | More than 27 metric tons to the Moon for Block 1 crew configuration; approximately 38 t for Block 1B crew configuration; approximately 42 t for Block 1B cargo-only configuration | Not stated as a current, like-for-like lunar payload figure |
| Destination measured by those figures | Translunar injection, the trajectory that sends payload toward the Moon | Lunar surface delivery and ascent; operational capacity remains under development |
| Propulsion information available here | Four RS-25 liquid-hydrogen/liquid-oxygen engines plus two five-segment solid boosters; about 8.8 million pounds of liftoff thrust | NASA describes the HLS as a system under development; the cited material does not give a complete current propulsion specification |
| Reusability status | Designed as an expendable launch system for its stated Artemis role | Reusability and high-flight-rate economics are design goals being developed, not flight-proven lunar-service results |
| Crew-readiness status in the cited material | NASA publishes the vehicle’s crew-launch architecture and payload capabilities | NASA requires an uncrewed demonstration before crew use |
| Per-launch price | Not established by the cited cost figures | Not stated in the cited official material |
What SLS is built to do
Earth launch and direct lunar departure
SLS is the launch vehicle at the beginning of the Artemis crew mission. It lifts Orion from Earth and provides the energy needed to send the spacecraft onto a lunar trajectory. NASA describes SLS as capable of delivering crew and/or cargo directly to the Moon in a single launch across the 239,000-mile (384,633-kilometer) distance, at speeds up to 24,500 mph.
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“Directly to the Moon” in this context refers to the launch vehicle’s delivery of Orion or cargo onto a translunar path. It does not mean that SLS lands astronauts on the lunar surface. The lunar landing is assigned to a separate system after the crew reaches lunar orbit.
Block 1 capability
NASA lists more than 27 metric tons to the Moon for the initial crew configuration of SLS Block 1. A NASA Marshall Space Flight Center technical figure records this as 59,000 pounds (27 t) of initial crewed TLI capability, with the figure identified as a 2025 NASA value.
This is a TLI number, not a payload-to-the-lunar-surface number. Propellant, spacecraft hardware and mission trajectory all affect how much of that capability becomes useful equipment at the destination.
Block 1B capability
Block 1B is the more powerful successor to Block 1 and is described by NASA as the primary crew-transport rocket for later Artemis missions. NASA lists approximately 38 metric tons for the Block 1B crew configuration and approximately 42 metric tons for the cargo-only configuration.
The same NASA technical material records those values as more than 84,000 pounds (38 t) for Block 1B and 93,000 pounds (42 t) for Block 1B cargo-only TLI capability. These are 2025 NASA Marshall Space Flight Center figures. The cargo-only value is higher because it does not reserve the launch architecture for a crewed Orion mission.
| SLS configuration | Published lunar-delivery figure | What the number means |
|---|---|---|
| Block 1, crew configuration | More than 27 t (59,000 lb) | Initial crewed TLI capability; NASA Marshall Space Flight Center, 2025 |
| Block 1B, crew configuration | Approximately 38 t (more than 84,000 lb) | Crewed TLI capability; NASA Marshall Space Flight Center, 2025 |
| Block 1B, cargo-only configuration | Approximately 42 t (93,000 lb) | Cargo-only TLI capability; NASA Marshall Space Flight Center, 2025 |
How SLS produces its lift
Core stage and boosters
The initial SLS configuration combines four RS-25 engines that burn liquid hydrogen and liquid oxygen with two five-segment solid rocket boosters. Together they produce about 8.8 million pounds of liftoff thrust.
Block 1B retains the liquid-hydrogen/liquid-oxygen core stage and the five-segment solid boosters. Its greater lunar-delivery capability comes from the Block 1B configuration’s more powerful upper-stage architecture, while the core and boosters provide the same fundamental high-thrust launch arrangement described by NASA.
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- High liftoff thrust: The 8.8-million-pound figure shows the scale of force available at launch, when the vehicle must overcome Earth’s gravity and atmospheric drag.
- Cryogenic propellants: Liquid hydrogen and liquid oxygen provide high performance, but they require careful handling and ground operations because the propellants are stored at very low temperatures.
- Solid boosters: The five-segment boosters add substantial thrust during the first part of ascent and are not part of an on-orbit refueling or landing cycle.
- Mission-specific payload: A published TLI capability is tied to a particular SLS configuration and mission design. It should not be treated as a universal payload number for every trajectory.
What Starship HLS is being developed to do
Lunar orbit to surface and back
NASA’s Human Landing Systems program describes SpaceX’s Starship HLS as a lunar lander for Artemis III and Artemis IV. Its job is to carry astronauts from lunar orbit to the Moon’s surface and return them to lunar orbit. Orion remains the crew’s Earth-launched spacecraft in the cited Artemis architecture; Starship HLS supplies the descent-and-ascent segment.
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NASA describes the lander as about 165 feet (50 meters) tall. That dimension applies to the HLS vehicle described by NASA, not to a complete Earth-launch stack with every stage and support system.
Development status is part of the specification
Starship HLS is not presented by NASA as an operational lunar vehicle in the cited material. NASA says SpaceX must perform an uncrewed demonstration before crew use. The demonstration requirement is consequential: a vehicle can have an ambitious design target while its practical performance, turnaround process, docking operations, propellant management and surface systems are still being validated.
For that reason, a current official Starship payload-to-TLI figure, payload-to-lunar-surface figure or operational per-flight price should be treated as not stated here. Public estimates may differ in assumptions about tanker flights, mission duration, landing reserves and cargo configuration; they are not substitutes for a finalized NASA-qualified capability.
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Why the payload numbers cannot be compared directly
“Which can carry more to the Moon?” has no single answer unless “to the Moon” is defined precisely.
- SLS figures are TLI figures: They describe the mass SLS can send onto a lunar trajectory in a specified configuration.
- Starship HLS is a lander: Its relevant result would be useful mass delivered to the lunar surface and, for a crewed mission, the ability to return the crew to lunar orbit.
- The mission chains differ: SLS launches once with Orion and its assigned payload. A Starship HLS mission depends on the complete lunar-transport architecture, including whatever steps are required to place and prepare the lander for its crewed sortie.
- Mass is not the same as usable cargo: A payload figure can include spacecraft, adapters, propulsion reserves and other mission hardware rather than equipment that astronauts unload on the surface.
The defensible comparison is therefore: SLS has published NASA TLI values of more than 27 t for Block 1 crew missions, approximately 38 t for Block 1B crew missions and approximately 42 t for Block 1B cargo-only missions. The cited official material does not establish a corresponding current Starship HLS number.
Reusability and operational maturity
SLS: specified, expendable architecture
SLS is designed to perform its launch mission with the flight hardware expended rather than recovered for another launch. That approach prioritizes a defined heavy-lift capability for the Artemis architecture. It also means that vehicle production, refurbishment of supporting ground systems and mission integration are central to sustaining the program.
The important point for readers is not simply “reusable versus disposable.” Reusability can reduce recurring hardware consumption if recovery, inspection, refurbishment and logistics work at the required scale. An expendable design can offer a more tightly bounded mission architecture when its performance and interfaces are already specified. Those advantages involve different risks and costs rather than a universal winner.
Starship: reusability as a development objective
Starship’s attraction is its intended reusable architecture and the possibility of more frequent flights. However, the cited NASA material characterizes Starship HLS as under development and requires an uncrewed lunar demonstration before astronauts fly. Until those demonstrations establish repeatable missions, reusability and high-cadence economics should be described as design goals or development claims, not as proven lunar-service results.
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A reusable lunar system must demonstrate more than a successful launch. It must support the required orbital operations, rendezvous or docking sequence, lunar descent, surface stay, ascent and safe return. For a crewed mission, each phase also has to meet NASA’s human-rating and mission-assurance requirements.
Crew safety and integration
How the Artemis roles fit together
- SLS launches Orion, the crew vehicle, from Earth.
- Orion carries the astronauts toward lunar orbit on the mission trajectory supported by SLS.
- The crew transfers to a lunar landing system in lunar orbit under the Artemis architecture.
- Starship HLS is being developed to perform the landing-system portion for Artemis III and Artemis IV: descent to the surface, surface operations and ascent back to lunar orbit.
- The crew returns using the lunar-orbit and Earth-return elements of the Artemis architecture rather than using SLS as a lunar takeoff vehicle.
This integration explains why Starship HLS is not a direct replacement for SLS in the cited plan. Replacing SLS would require a different way to launch Orion and crew from Earth, not merely a different lunar lander.
Different certification questions
SLS must demonstrate the performance and reliability needed for the crewed Earth departure carried out by Orion. Starship HLS must demonstrate safe crew transfer, lunar landing, surface ascent and integration with the rest of the Artemis mission. Their safety cases overlap at the program level but are not identical because the vehicles operate in different environments and mission phases.
Launch cadence and schedule: what can be said now
The cited material supplies no reliable, like-for-like launch-cadence number for SLS and Starship HLS. SLS has a defined NASA architecture and published Block 1 and Block 1B performance values. Starship HLS remains a development program with an uncrewed demonstration required before crew use.
That difference affects schedule interpretation. A stated future mission date is not the same as an operational flight rate. For SLS, the relevant question is production and integration of the specified launcher, Orion and associated ground systems. For Starship HLS, the schedule depends on completing the required demonstrations and proving the complete lunar mission sequence, not only reaching orbit.
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What the GAO figures cover
The U.S. Government Accountability Office reported in its 2024 assessment that NASA established $9.6 billion in December 2023 development cost baselines for SLS Block 1B, Gateway initial capability and Human Landing System initial capability. Those are development baselines for multiple projects, not a price tag for one SLS launch or one Starship HLS flight.
GAO also reported that those projects plus Orion represented $19.2 billion, nearly 60 percent of NASA’s major-project portfolio development costs in that assessment. The figure describes a portfolio’s development burden and should not be converted into a per-mission operating cost.
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| Question | Evidence available in the cited material |
|---|---|
| How much does one SLS launch cost? | Not established by the cited development-baseline figures |
| How much does one Starship HLS launch cost? | Not stated in the cited official material |
| Which system has lower recurring cost? | Cannot be determined from the cited figures because the systems perform different mission segments and Starship HLS remains under development |
| What does $9.6 billion represent? | December 2023 development baselines for SLS Block 1B, Gateway initial capability and HLS initial capability, according to GAO’s 2024 assessment |
| What does $19.2 billion represent? | Development costs for those projects plus Orion, described by GAO as nearly 60% of the major-project portfolio in that assessment |
A meaningful economic comparison would need common accounting rules: development amortization, launch preparation, ground infrastructure, vehicle recovery or disposal, tanker or refueling requirements, crew-support systems and the number of missions over which fixed costs are spread. The cited numbers do not provide that complete model.
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Which rocket is “bigger”?
The answer depends on the measurement. SLS has a published liftoff-thrust figure of about 8.8 million pounds and published lunar-delivery capacities for Block 1 and Block 1B. NASA describes Starship HLS as about 165 feet (50 m) tall, but that is a lander dimension, not a complete comparison with the full SLS launch vehicle.
Because the available official figures do not provide matching height, mass, thrust and payload data for both complete systems, declaring one universally “bigger” would mix unlike measurements. For launch force and specified Earth-to-Moon delivery, SLS has the quantified NASA figures. For Starship HLS, the relevant lunar performance remains a development target until the required demonstrations produce operational data.
Which system matters for each Artemis question?
If the question is “How do astronauts leave Earth for the Moon?”
SLS is the vehicle assigned to launch Orion and crew in the cited architecture.
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If the question is “How do astronauts land on the Moon?”
Starship HLS is the system NASA is developing for the lunar-orbit-to-surface and surface-to-orbit portion of Artemis III and Artemis IV, subject to the required uncrewed demonstration before crew use.
If the question is “Which has the larger published lunar payload?”
SLS is the only one of the two for which the cited NASA material gives directly usable lunar-delivery figures: more than 27 t for Block 1 crew configuration, approximately 38 t for Block 1B crew configuration and approximately 42 t for Block 1B cargo-only configuration. A comparable Starship HLS number is not stated.
If the question is “Which is reusable?”
Starship HLS is being developed around reusability, but its lunar reusability and operating cadence are not yet flight-proven in the cited material. SLS is an expendable launch architecture.
If the question is “Is Starship replacing SLS?”
No—not in the Artemis III and IV architecture described by NASA. SLS launches Orion and crew from Earth; Starship HLS performs the lunar landing-system role after the crew reaches lunar orbit.
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What to watch as the comparison changes
- Completion of the uncrewed Starship HLS demonstration: NASA requires this milestone before crew use.
- Verified lunar performance: Look for official payload, propellant, landing, ascent and mission-duration data rather than estimates that omit parts of the mission chain.
- Block 1B readiness: The practical value of the approximately 38 t crew and 42 t cargo-only figures depends on the availability of the complete Block 1B vehicle and its integrated Artemis mission systems.
- Operational cadence: Reusability becomes an economic advantage only when recovery, inspection, refurbishment and relaunch are demonstrated at a useful rate.
- Comparable cost accounting: Future comparisons should separate one-time development costs from recurring launch and mission operations.
Bottom line
SLS is NASA’s currently specified Earth-to-Moon crew launcher, with published TLI capabilities ranging from more than 27 metric tons for the initial crew configuration to approximately 38 metric tons for Block 1B crew missions and approximately 42 metric tons for Block 1B cargo-only missions. Starship HLS is a different kind of vehicle: a lunar lander intended to carry astronauts from lunar orbit to the surface and back for Artemis III and IV. Its reusability and potential for higher flight rates are important design goals, but its relevant lunar capabilities remain under development and require an uncrewed demonstration before crew use.
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