Statements (56)
| Predicate | Object |
|---|---|
| gptkbp:instance_of |
gptkb:rocket
|
| gptkbp:application |
gptkb:Super_Heavy
gptkb:starship |
| gptkbp:cooling_system |
regenerative cooling
|
| gptkbp:designed_by |
gptkb:Space_X
|
| gptkbp:developer |
gptkb:2012
estimated at $1 billion |
| gptkbp:diameter |
1.2 m
|
| gptkbp:durability |
designed for reuse
|
| gptkbp:elevation |
250 seconds
|
| gptkbp:engine |
twin-chamber
|
| gptkbp:engine_type |
gptkb:rocket
|
| gptkbp:facilities |
gptkb:Space_X_Mc_Gregor
gptkb:Space_X_Boca_Chica |
| gptkbp:first_flight |
gptkb:2020
|
| gptkbp:fuel_type |
full-flow staged combustion
methane-oxygen |
| https://www.w3.org/2000/01/rdf-schema#label |
Raptor engine family
|
| gptkbp:ignition_system |
spark ignition
|
| gptkbp:investment |
300 bar
|
| gptkbp:launch_vehicle |
gptkb:starship
|
| gptkbp:length |
3.5 m
|
| gptkbp:manufacturer |
gptkb:Space_X
|
| gptkbp:notable_features |
high performance
modular design advanced materials high reliability high efficiency advanced control systems reusable design high thrust-to-weight ratio full-flow staged combustion cycle environmentally friendly fuel designed for Mars missions designed for lunar missions capable of in-orbit refueling capable of landing on Mars capable of landing on the Moon capable of multiple ignitions designed for rapid turnaround high thrust vector control suitable for deep space missions |
| gptkbp:number_of_rooms |
2
|
| gptkbp:produced_by |
in production
|
| gptkbp:propulsion |
methane
liquid oxygen 330 seconds 2300 k N |
| gptkbp:rate_of_fire |
gptkb:2019
|
| gptkbp:sparked |
gptkb:theorem
|
| gptkbp:successor |
gptkb:Raptor_2
|
| gptkbp:uses |
methane
liquid oxygen |
| gptkbp:weight |
approximately 1,500 kg
|
| gptkbp:bfsParent |
gptkb:Raptor_Vacuum_engine
|
| gptkbp:bfsLayer |
5
|