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OUR LAUNCH VEHICLE
TrueAscent Discriminators
- Fully reusable first stage (85% of cost) with the second stage designed for satellite specific customization.
- Common thrust chamber used across both stages to reduce cost, with optimized nozzle for first and upper-stage.
- Engines use a highly optimized Full-Flow Staged Combustion Cycle that is designed for high thrust-to-weight, efficiency (Isp), reliability and reusability.
- Our engines can use either liquid methane or liquid natural gas (LNG) as the fuel – both environmentally friendly. LNG allows for on-site production without hazmat or deep cryogenic issues.
| Vehicle Performance | ||||
|---|---|---|---|---|
| Payload (420 km at 51.6 deg from KSC) | 1,500 | Kg. | 3,307 | Lbm. |
| Liftoff Mass | 89,909 | Kg. | 198,519 | Lbm. |
| Diameter | 3.1 | M. | 10 | Ft. |
| Structure Reuses | 100 | |||
| Propulsion Reuses | 50 | |||
| Engine Properties | ||
|---|---|---|
| Thrust per Engine | 50,000 | Lbf. |
| Upper Stage Isp | 360 | Sec. |
| First Stage Isp (vac) | 310 | Sec. |
| Upper Stage Expansion Ratio | 150:1 | – |
| First Stage Expansion Ratio | 16:1 | – |
| Chamber Pressure | 1,000 | Psi. |
| Oxidizer/Fuel (O/F) Ratio | 3.57 | – |