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BOEING / NASA · VEHICLE PROFILE · DATA AS OF 2026-07-28

Space Launch System (SLS)

Operational Expendable Super Heavy
4
Flights
Success / Partial / Failure
100.00%
Success Rate
4/4 flights
—
Fleet Leader
No booster telemetry
Jun 22, 2026
Cadence
Last completed flight

RELIABILITY & S/PF/F SPLIT

100.00%
Overall success rate · Wilson 95% LB 51.01%
4
Success
0
Partial Failure
0
Failure
0
Scrubbed
Days since last failureNo recorded failures
Current success streak4
Last completed flightJun 22, 2026
Methodology IP
S/PF/F split is non-negotiable methodology. Partial failures are NOT collapsed into failures. A partial (e.g. payload delivered to wrong orbit, booster lost on otherwise-successful flight) is treated as a distinct outcome for underwriting. See /methodology/.

SUBSYSTEM RELIABILITY

Per-system success rates aggregated across all flights with recorded subsystem outcomes. Systems without a row are "not tracked for this vehicle yet" — we never fabricate success.

Coolant System 0%
S 0 · PS 1 · F 0 · N 1

RECENT FLIGHTS

Date Mission Payload Outcome
Jun 22, 2026 NASA’s Nancy Grace Roman Space Telescope arrives in Florida — · 95,000 kg Success
Apr 01, 2026 Artemis II — · 95,000 kg Success
Apr 01, 2026 Orion CM003 — · 95,000 kg Success
Nov 16, 2022 Orion CM 002 — · 95,000 kg Success

View all flights in the main tracker →

TEST HISTORY

Engine hot-fires, hop flights, tank pressurizations, captive fires, and abort events recorded against this vehicle. Every row links to its reporting source.

Date Test Type Campaign / Article Facility Duration Outcome Source
Jun 22, 2026 Engine Test — — Success source →

View all tests in the test tracker →

PAYLOAD & ORBIT MIX

380.0K kg
Total mass lifted
—
Most-flown orbit
0% gov
Gov / commercial split
1
Crewed flights

OPERATOR CONTEXT

OperatorBoeing / NASA

Open operator financial profile →

REGISTRY DATA

First flight2022-11-16
Registry launches2 (as of 2026-04-01)
ClassSuper Heavy
Height98 m
ReusabilityExpendable
List price$2.20B
Payload capacity (kg)
LEO95,000 kg
TLI (translunar)27,000 kg

Source: space_launch_vehicle_registry.json · Operator page →

METHODOLOGY

Per-vehicle reliability is aggregated from the AstraVeris launch_events table with Wilson 95% lower-bound error estimates. Subsystem outcomes are extracted by a local Gemma model from primary-source articles — outcomes are never fabricated; absence of a row means "not tracked". Aspirational vehicles (not yet flown) carry registry-only metadata with explicit "Not yet flown" banners. Full specifications: /methodology/. Licensing terms: /data-licensing/.

Not investment advice. For insurance underwriting, verify against operator investigation reports.