Path: Propulsion/Rocket
% Artemis Launch Analysis This script analyzes the SLS launch vehicle. It designs an all-liquid booster, using the same RS-25 engines, and compares the performance. It includes launch simulations. The following gives reference information used in the script. *System* https://www.nasa.gov/exploration/systems/sls/factsheets.html http://www.braeunig.us/space/specs/sls.htm The SLS core stage and its two solid rocket boosters (SRBs) generated a total of 8.8 million pounds of thrust *Solid Rocket Booster Details (5 segment)* Length: 177 feet (53.9 meters) Diameter: 3.71 meters Total mass: 731,885 kg each Propellant mass: 631,495 kg Propellant: polybutadiene acrylonitrile (PBAN) Thrust: 16,000 kN each Specific impulse: 242 s (sea level), 268 s (vacuum) Operational time: 127 seconds *Core Stage Details* Length: Approximately 212 feet (64.6 meters) Diameter: 27.6 feet (8.4 meters) Dry mass: Approximately 188,000 lbs (85,275 kg) Burnout mass: 112,000 kg Usable propellant mass: 979,452 kg Capacities: Liquid Hydrogen (LH2) 537,000 gallons (2 million liters) (317,000 pounds) | Liquid Oxygen (LOX)196,000 gallons (741,941 liters) (1.86 million pounds) *RS-25D Details:* Thrust: 416,300 lbs. (~1860 kN) (sea level), 512,300 lbs. (2280 kN) (vacuum) Specific impulse: 363 s (sea level), 453 s (vacuum) Dry Mass: 3,525 kg See also: RocketModel, RocketMass, TimeHistory, LatexExp, DisplayLatexTable, AtmDens2, StdAtm, SLSLaunchAnalysis>RHS, SLSLaunchAnalysis>SRBThrustInterp, SLSLaunchAnalysis>DVParallel, SLSLaunchAnalysis>DVFromMassAndIsp ------------------------------------------------------------------------
AerospaceUtils: AeroData/AtmData AerospaceUtils: AtmosphericCalculations/AtmDens2 Propulsion: Rocket/RocketMass Propulsion: Rocket/RocketModel Common: Atmosphere/StdAtm Common: General/DisplayLatexTable Common: General/LatexExp Common: Graphics/TimeHistory Math: Integration/RK4 Math: Linear/Mag
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