Relativity Space · In Development · us · Launch Vehicle
Terran R
Reusable medium-heavy lift rocket targeting first launch late 2026 from Cape Canaveral.
Verified 2026-09-24
Systems cutaway
13 Aeon R engines on the first stage and 1 Aeon V vacuum engine on the second; LOX/methane, gas-generator cycle; 3,497,000 lbf (15,555 kN) total liftoff thrust.
86.6 m height; 5.4 m diameter and payload fairing; high-strength aluminum alloys.
First stage designed for propulsive landing with 4 landing legs, 4 grid fins, base heat shield, engine relight capability.
Specs & Metrics
- Payload to LEO ↑ better
- 23,500 kg
- reusable/downrange landing config; 33,500 kg expendable
- Maximum payload mass deliverable to low Earth orbit (~200–400 km circular), in the vehicle's stated reference configuration.
- Liftoff Thrust ↑ better
- 15555 kN
- 15,555,431 N total liftoff thrust
- Total first-stage thrust at liftoff (sea-level), in kilonewtons, summing all active engines and solid strap-ons.
- Vehicle Height ↓ better
- 86.6 m
- Full stack height at liftoff, in metres, including fairing or spacecraft.
Subsystems
13 Aeon R engines on the first stage and 1 Aeon V vacuum engine on the second; LOX/methane, gas-generator cycle; 3,497,000 lbf (15,555 kN) total liftoff thrust.
86.6 m height; 5.4 m diameter and payload fairing; high-strength aluminum alloys.
First stage designed for propulsive landing with 4 landing legs, 4 grid fins, base heat shield, engine relight capability.
Program roadmap
- achieved
Vehicle-level critical design review and flight production started
2025-03↗ - achieved
All circumferential friction stir welds done on the first-flight first-stage tank; 1,602 parts released toward first flight
2025-11↗ - planned
First orbital launch from Launch Complex 16, Cape Canaveral (Relativity: starting late 2026)
2026↗