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ORBITAL / STATUS UNVERIFIED

Electron

Rocket Lab · USA / New Zealand

Capacity: operator confirmation required

Explore technical data · Launch opportunities · Calculate my cargo
ElectronConfiguration record — no approved dimensional illustration

Technical overview

Electron uses two stages with electric-pump-fed Rutherford engines. Its optional Kick Stage supports maneuvers and deployment. Published performance does not confirm available capacity or integration geometry.

  • Electron

Technical specifications

Browse by category. Each value applies to the configuration described in its conditions; review date is not document date.

Source-supported parameter

9

A supported parameter does not qualify the whole vehicle or container.

Historical / reference data

0

Applies to a stated period or variant.

Engineering review required

0

Do not use as an approved design constraint.

Dimensions and mass

ParameterValue and applicabilityConfidence and source
Body diameter1.2 mSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document
Height18 mSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document
Wet mass13,000 kgSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document

Stages, propulsion and structure

ParameterValue and applicabilityConfidence and source
Engines9 sea-level Rutherford + 1 vacuum RutherfordSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document
First-stage thrust190 kN at liftoff; 224 kN peakSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document
PropellantsLOX / keroseneSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document
Second-stage thrust25.8 kN; vacuum RutherfordSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official Electron web page; revision date not stated

Open source document
Stages2 + Kick StageSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document
StructureCarbon compositeSource-supported parameter
Reviewed: 2026-10-13
Document and source

Official web page; document date not stated

Open source document

Payload performance

No approved performance set with complete orbital conditions. Published lift capability is not available capacity.

LEO

NOT PUBLICLY VERIFIED

SSO

NOT PUBLICLY VERIFIED

POLAR

NOT PUBLICLY VERIFIED

MEO

NOT PUBLICLY VERIFIED

GTO

NOT PUBLICLY VERIFIED

GEO

NOT PUBLICLY VERIFIED

HEO

NOT PUBLICLY VERIFIED

LUNAR TRANSFER

NOT PUBLICLY VERIFIED

DEEP SPACE

NOT PUBLICLY VERIFIED

Fairing & payload geometry

Electron — VARIANT_REQUIRES_CONFIRMATION

External diameter: NOT PUBLICLY VERIFIED

INSUFFICIENT_GEOMETRY_DATA · DOCUMENT_REVIEW_REQUIRED · NOT VERIFIED

Adapters: NOT PUBLICLY VERIFIED

Fairing diameter is not usable diameter. A digitized static profile does not confirm dynamic clearance or flight qualification.

Open existing geometry engine

Launch environment

Vibration, acoustics, quasi-static loads, shock, venting, thermal conditions and contamination require variant-specific profiles.

ENGINEERING VERIFICATION REQUIRED

Launch services

Dedicated service, rideshare, separation or orbital transfer requires operator and mission confirmation. HASTE is suborbital and is not an orbital launch offer.

Launch history

A complete verified history has not been imported. Reliability is not calculated from a partial catalog.

Historical launch cost & price intelligence

Electron · LEO / SSO

$30,000–$46,000 / kg

HISTORICAL · NOT_VERIFIED

NOT VERIFIED · USER_REFERENCE_ANALYSIS

An indicator is not a confirmed capacity offer. Historical indicators are not multiplied by customer mass.

PRICE ON REQUEST · Price and terms require renewed verification

ILS launch opportunities

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Full catalog and capacity confirmations

SLX BOX — REV 2.0

SLX BOX MICRO

SLX BOX MICRO

380 × 380 × 560 mm

Designed interior: 350 × 350 × 520 mm

ENGINEERING VERIFICATION REQUIRED

SLX BOX STANDARD

SLX BOX STANDARD

850 × 850 × 1240 mm

Designed interior: 810 × 810 × 1180 mm

ENGINEERING VERIFICATION REQUIRED

SLX BOX HEAVY

SLX BOX HEAVY

1840 × 1840 × 2700 mm

Designed interior: 1760 × 1760 × 2600 mm

ENGINEERING VERIFICATION REQUIRED

Tare mass, stacking, mounts and flight qualification remain unverified.

Preliminary calculator

INDIVIDUAL QUOTATION REQUIRED

Unknown hardware mass prevents a complete quote. Dimensions do not establish container qualification.

Continue — ISO, temperature, ESD and inquiry

PDF documentation

Download technical datasheet PDF

The technical datasheet is separate from the private cargo estimate generated after saving an inquiry.

REFERENCE / ENGINEERING REVIEW · 2026-11-10

Source documentation

Verification of one parameter does not verify the whole page. Space LogistiX does not claim operator partnership or qualification.