L1 Launch Vehicle
Two-stage methalox orbital launch vehicle designed for delivering small to medium payloads to low Earth orbit and Sun-synchronous orbit.
Overview
The L1 is a two-stage expendable launch vehicle developed by Tomorrow for delivering small to medium payloads to low Earth orbit and Sun-synchronous orbit. It uses liquid methane (LCH₄) and liquid oxygen (LOX) propellants throughout both stages.
The first stage is powered by a cluster of G1 engines in a sea-level configuration, providing the thrust required to lift the vehicle through the atmosphere. The second stage uses a single G1 vacuum variant with an extended nozzle optimised for in-space performance.
Both stages utilise common-bulkhead tank construction to minimise structural mass. Propellant tanks are pressurised using helium stored in composite overwrapped pressure vessels (COPVs).
Stage 1
The first stage carries the majority of the vehicle's propellant mass and provides the initial acceleration through the lower atmosphere. Multiple G1 sea-level engines are arranged to provide engine-out capability during ascent.
The stage separates at supersonic velocity following first-stage burnout. The engine cluster configuration ensures mission success even in the event of a single engine failure during flight.
Stage 2
The second stage completes orbital insertion using a single G1 vacuum engine. The extended nozzle provides higher specific impulse in the vacuum environment.
The stage includes a full avionics suite for guidance, navigation, and control throughout the mission, enabling precise payload deployment to the target orbit.
Payload Fairing
The payload fairing protects the spacecraft during atmospheric ascent and is jettisoned once the vehicle exits the dense atmosphere. The fairing is sized to accommodate a range of satellite configurations.
A clamshell separation mechanism ensures clean and reliable fairing deployment, minimising risk of contact with the payload during the jettison event.
L1
| General | |
|---|---|
| Manufacturer | Tomorrow |
| Function | Orbital launch vehicle |
| Status | In development |
| Size | |
| Height | ~27 m |
| Diameter | 2.0 m |
| Stages | 2 |
| Capacity | |
| Payload to LEO | ~1,000 kg |
| Payload to SSO | ~700 kg |
| Propellant | |
| Fuel | Liquid methane (LCH₄) |
| Oxidiser | Liquid oxygen (LOX) |
| Stage 1 | |
| Engines | 9× G1 (sea level) |
| Thrust | ~580 kN (SL) |
| Stage 2 | |
| Engines | 1× G1 (vacuum) |
| Thrust | ~80 kN (vac) |