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Neutron is Rocket Lab’s two-stage, carbon-composite medium-lift orbital rocket, still in development as of October 18, 2026. Its first stage and captive payload fairing are designed to return and fly again, while the carbon-composite second stage is expended on each mission. Nine methane-and-liquid-oxygen Archimedes engines power the booster and one vacuum-optimized Archimedes powers the upper stage. Rocket Lab currently expects the first launch in 2027, but that is a company target dependent on qualification tests and manufacturing progress, not a guaranteed date.
What Neutron is designed to do
Neutron occupies the medium-lift segment between small launchers and the largest heavy-lift vehicles. Rocket Lab is designing it for commercial constellation deployment, national-security missions and civil spacecraft, with later concepts covering lunar and Mars missions, cargo delivery and potentially human spaceflight.
The vehicle uses carbon-composite structures in both stages. Carbon composites can provide high strength at relatively low mass, but they also require specialized manufacturing and inspection, particularly for tanks exposed to cryogenic propellants and for hardware that must survive repeated atmospheric entry.
Neutron is not an operational launcher yet. Its architecture, engines, recovery systems and launch site are progressing through qualification and construction activities, but no orbital flight has occurred.
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Which parts are reusable?
Neutron’s reusability is concentrated in Stage 1. Rocket Lab’s design returns the booster as one integrated assembly that includes the extended interstage and a captive payload fairing. The fairing does not separate into pieces and fall away as on many conventional launchers; it remains attached to the first stage during descent so the complete assembly can be recovered.
The second stage is carbon composite but is currently planned for disposal after delivering its payload to orbit. Therefore, “reusable Neutron” means a reusable first stage and fairing, not a fully reusable two-stage vehicle.
Why a captive fairing matters
A conventional expendable fairing must be separated, tracked and either discarded or recovered independently. Keeping Neutron’s fairing attached removes a separation event and lets the stage return with the aerodynamic shell already integrated. The trade-off is that the returning stage must carry the fairing’s mass through ascent, entry and landing, which is one reason the recovery profile and payload target are tightly linked.
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- Forward canards: aerodynamic control surfaces used during atmospheric descent.
- Tapered lifting-body shape: generates lift and control authority rather than behaving like a purely ballistic cylinder.
- Landing legs: deploy for a propulsive touchdown.
- Low ballistic coefficient: helps the stage lose speed and reduce aerodynamic loads during entry.
- Reusable thermal protection: protection on the thrust structure is intended to withstand re-entry heating on repeated flights.
How Neutron returns to Earth
After Stage 2 separates, the first stage can follow one of two recovery profiles. The choice affects the amount of payload the rocket can place in orbit.
Return To Launch Site (RTLS)
In an RTLS mission, the booster performs the maneuvers needed to fly back toward Virginia and land at Launch Complex 3 (LC-3) at the Mid-Atlantic Regional Spaceport on Wallops Island. Returning to the launch area requires propellant for the course reversal and landing, leaving less mass available for the customer’s payload than a down-range landing.
Down Range Landing (DRL)
For a DRL mission, the booster continues downrange and lands propulsively on a marine platform rather than spending as much energy flying back to Virginia. The reduced return distance can improve payload performance, although recovery then depends on a sea-based platform, weather and marine operations.
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Rocket Lab calls the planned platform “Return On Investment.” It is a modified 400-foot (122-meter) barge equipped with autonomous ground-support equipment to capture and secure the landed stage, blast shielding and station-keeping thrusters for precise positioning.
Both profiles use powered landing rather than a parachute recovery. The canards and lifting-body geometry guide the stage through entry; landing legs and an engine burn handle the final touchdown.
Where Neutron will launch and land
LC-3 at the Mid-Atlantic Regional Spaceport on Wallops Island, Virginia, is Rocket Lab’s dedicated Neutron test, launch and landing complex. The company describes it as supporting return-to-Earth missions and providing the largest orbital-launch capacity in the spaceport’s history.
An RTLS flight would return the booster to LC-3. A DRL flight would use the offshore platform and then bring the recovered stage back for inspection, refurbishment and preparation for a later mission. The exact operational sequence, turnaround time and number of flights per stage have not been established publicly because the rocket has not yet flown.
What engines does Neutron use?
Neutron uses Rocket Lab’s Archimedes engine, which burns liquid methane and liquid oxygen (methalox) in an oxidizer-rich staged-combustion cycle. Rocket Lab describes the engine as reusable and partly 3D printed, with a design intended to reduce operating stress and support repeated firings.
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The booster has nine sea-level Archimedes engines. The Payload User Guide lists up to 165,000 pounds-force (733 kilonewtons) per engine and 1,450,000 pounds-force total for the nine-engine first stage. The same guide gives total sea-level thrust as 6,600 kilonewtons; the figures are presented as separate rated values in the guide and should not be treated as interchangeable measurements.
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Stage 2 propulsion
The upper stage uses one vacuum-optimized Archimedes engine. Its listed vacuum thrust is 900 kilonewtons. A vacuum-optimized nozzle is better suited to the thin atmosphere at altitude and in space, where a larger expansion ratio can improve efficiency.
Throttle and restart capability
The Payload User Guide lists a minimum throttle capability of 65% and restart capability for the engines on both stages. Throttling helps manage acceleration and structural loads during ascent and provides control authority during landing burns. Restart capability gives the mission designers additional options for staging, orbit insertion and recovery maneuvers.
Why methane instead of RP-1 or hydrogen?
Rocket Lab says methane offers higher specific impulse than RP-1 kerosene without the very large tanks and vehicle-size penalty associated with liquid hydrogen. Liquid methane also fits the company’s goal of a reusable engine that can be manufactured and operated repeatedly, although the practical benefits will depend on Neutron’s final flight data and refurbishment process.
Neutron’s published size and performance
The following values come from Rocket Lab’s Payload User Guide version 1.0, published in January 2025, unless otherwise noted. Dimensions refer to the stages rather than a complete stacked vehicle.
| Item | Published value | Qualification |
|---|---|---|
| First-stage height | 42.8 m | Rocket Lab Payload User Guide v1.0, January 2025 |
| First-stage diameter | 7 m | Rocket Lab Payload User Guide v1.0, January 2025 |
| Second-stage height | 11.5 m | Rocket Lab Payload User Guide v1.0, January 2025 |
| Second-stage diameter | 4.9 m | Rocket Lab Payload User Guide v1.0, January 2025 |
| Stage 1 engines | 9 sea-level Archimedes | Configuration listed by Rocket Lab |
| Stage 2 engine | 1 vacuum-optimized Archimedes | Configuration listed by Rocket Lab |
| Stage 1 total thrust | 6,600 kN at sea level | Guide value; thrust varies with operating conditions |
| Stage 2 thrust | 900 kN in vacuum | Guide value |
| Reusable-configuration LEO payload | Approximately 13,000 kg | Rocket Lab’s current product information and a 2026 SEC filing; an approximate figure, not a demonstrated flight result |
| Minimum throttle | 65% | Guide lists this capability for both stage engines |
| Engine restart | Yes | Guide lists restart capability for both stage engines |
The approximately 13,000-kilogram low-Earth-orbit figure applies to the reusable configuration identified by Rocket Lab. Actual payload depends on orbit altitude and inclination, launch azimuth, recovery mode, weather, vehicle mass and mission reserves. A down-range landing generally preserves more performance than RTLS because the booster does not need to reverse course to Virginia.
What happens during a typical Neutron mission?
- Lift-off: Nine sea-level Archimedes engines accelerate the vehicle from LC-3.
- Ascent and staging: The first stage burns through the atmospheric portion of flight, then separates with its extended interstage and captive fairing still together.
- Stage 2 insertion: The single vacuum Archimedes engine continues accelerating the payload toward its target orbit and can use its restart capability if the mission requires it.
- Stage 1 entry: The booster uses its lifting-body shape, canards and guidance system to control the descent while reusable thermal protection manages re-entry heating.
- Landing: Depending on the mission plan, the stage either returns to LC-3 or lands on the Return On Investment platform using a propulsive terminal burn.
- Refurbishment: The recovered assembly would be inspected, serviced and prepared for another flight. Rocket Lab has not published a fixed turnaround interval or a guaranteed reuse count.
Why recovery mode changes payload capacity
Rocket performance is a mass and energy budget. Every kilogram reserved for landing propellant, thermal protection, landing legs, guidance hardware and recovery structure is unavailable for the payload. RTLS requires additional velocity change to return to the launch area, so it normally imposes a larger performance penalty. DRL avoids much of that reversal and can therefore support heavier payloads, but it adds marine logistics and exposure to sea conditions.
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Customers selecting a mission profile would need to match the recovery mode to the spacecraft’s mass, orbit and schedule. A lighter constellation batch might fit an RTLS mission, while a heavier payload could require down-range recovery. Until Neutron completes flight testing, these are architectural capabilities rather than demonstrated performance guarantees.
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When will Neutron launch?
Rocket Lab’s latest public update, dated October 14, 2026, says the inaugural launch is expected in 2027. That supersedes older company announcements that targeted 2025 or 2026.
A June 30, 2026 regulatory filing reported several activities still in progress: qualification testing, continued Archimedes engine testing, advancement of the second stage and reusable fairing, and first-stage tank production aligned with delivery to the pad in the fourth quarter of 2026. The filing also cautioned that the exact launch timing depends on first-stage qualification and other critical tests.
The 2027 date should therefore be read as a company expectation, not a firm flight appointment. A first launch can move if engine qualification, tank production, stage integration, ground testing, range approval or other safety-critical work takes longer than planned.
What Neutron’s design means for launch customers
Potential advantages
- Reusable booster and fairing: recovering the major first-stage assembly could reduce recurring hardware consumption after the system becomes operational.
- Medium-lift capacity: an approximately 13,000-kilogram reusable-configuration LEO capability is intended to serve large constellation batches and substantial civil or government spacecraft.
- Two recovery choices: RTLS prioritizes land-based return at Virginia; DRL trades marine recovery for additional payload performance.
- Methalox propulsion: methane and oxygen support the Archimedes engine’s reusable operating concept.
- Restart and throttling: the published 65% minimum throttle and restart capability give mission planners more control during ascent and landing.
Open questions
- The rocket has not yet demonstrated an orbital launch, landing or turnaround.
- Published payload numbers are design targets and approximate values, not flight-proven results.
- Rocket Lab has not publicly established operational cadence, refurbishment duration, reuse count or standard launch pricing.
- The first-launch schedule remains dependent on qualification and manufacturing milestones.
How to evaluate Neutron against another launcher
A meaningful comparison should use the same orbit and mission assumptions rather than headline payload numbers alone. Check these dimensions:
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- Reusable elements: determine whether the competitor reuses a first stage, fairing, upper stage or complete vehicle.
- Payload to the same orbit: compare mass to the same altitude and inclination, and identify whether recovery is RTLS, downrange or expendable.
- Propellant and engine cycle: methane, kerosene or hydrogen each impose different tank, handling and performance requirements; engine cycle affects pressure, efficiency and reuse goals.
- Landing infrastructure: include pads, barges, range access, weather limits and transportation of recovered hardware.
- Operational maturity: separate published plans from flight-proven launches, landings and turnaround data.
- Schedule confidence: distinguish a stated target year from a confirmed launch date and look for evidence of completed qualification milestones.
The essential takeaway
Neutron is a planned medium-lift orbital system built around a reusable nine-engine first stage, a captive fairing and a single-use vacuum upper stage. Its lifting-body booster can return to Virginia or land downrange on a barge, while methane-fueled Archimedes engines provide throttling and restart capability. Rocket Lab’s current target for the first launch is 2027, but the vehicle remains in development and its payload, recovery and turnaround claims have yet to be validated by an orbital flight.
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