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gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:assembly_location
|
gptkb:NASA_Michoud_Assembly_Facility
|
|
gptkbp:budget
|
estimated at $2 billion
|
|
gptkbp:challenges
|
high thrust-to-weight ratio
complex integration of systems
|
|
gptkbp:collaboration
|
international space agencies
involves multiple countries
|
|
gptkbp:community_engagement
|
community outreach programs
|
|
gptkbp:control_system
|
digital fly-by-wire
|
|
gptkbp:cooling_system
|
active cooling
|
|
gptkbp:crew_capacity
|
up to 4 astronauts
|
|
gptkbp:design
|
10 years
|
|
gptkbp:design_features
|
aerodynamic shape
|
|
gptkbp:designed_by
|
gptkb:NASA
|
|
gptkbp:development
|
gptkb:2011
|
|
gptkbp:diameter
|
8.4 meters
|
|
gptkbp:durability
|
not reusable
|
|
gptkbp:educational_programs
|
STEM initiatives related to space exploration
|
|
gptkbp:engine_type
|
gptkb:RS-25
|
|
gptkbp:environmental_impact
|
thermal vacuum tests
|
|
gptkbp:facilities
|
gptkb:NASA's_Stennis_Space_Center
|
|
gptkbp:first_flight
|
gptkb:Artemis_I
uncrewed
|
|
gptkbp:fuel_capacity
|
2.1 million liters
|
|
gptkbp:fuel_type
|
cryogenic
|
|
gptkbp:funding
|
funded by U. S. government
|
|
gptkbp:height
|
65 meters
|
|
gptkbp:historical_significance
|
gptkb:first_Artemis_mission
part of Artemis lunar missions
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
SLS core stage
|
|
gptkbp:infrastructure
|
mobile launcher
|
|
gptkbp:integrates_with
|
gptkb:stage_play
|
|
gptkbp:integration
|
several months
approximately 12 months
vertical assembly
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
static fire tests
|
|
gptkbp:launch_date
|
once every 2-3 years
annual launches expected
|
|
gptkbp:launch_mass
|
3 million pounds
|
|
gptkbp:launch_platform
|
gptkb:NASA_Launch_Services_Program
|
|
gptkbp:launch_site
|
gptkb:Kennedy_Space_Center
|
|
gptkbp:launch_window
|
varies by mission
multiple opportunities per year
|
|
gptkbp:launched
|
gptkb:Launch_Complex_39_B
|
|
gptkbp:lifespan
|
10 years
|
|
gptkbp:manufacturer
|
gptkb:Boeing
|
|
gptkbp:mission
|
deep space exploration
return humans to the Moon
Mars exploration planned
Mars exploration missions planned
|
|
gptkbp:mission_duration
|
up to 30 days
|
|
gptkbp:mission_type
|
deep space exploration
|
|
gptkbp:noise_level
|
passive damping
active damping system
|
|
gptkbp:number_of_engines
|
four
four RS-25 engines
|
|
gptkbp:objective
|
gptkb:Moon
|
|
gptkbp:operational_use
|
gptkb:NASA_Artemis_program
|
|
gptkbp:part_of
|
gptkb:Space_Launch_System
|
|
gptkbp:partnerships
|
gptkb:commercial_space_companies
|
|
gptkbp:payload_capacity
|
95 metric tons
up to 130 metric tons
|
|
gptkbp:payload_capacity_translunar_injection
|
27 metric tons
|
|
gptkbp:project
|
gptkb:NASA_Marshall_Space_Flight_Center
led by NASA Marshall Space Flight Center
|
|
gptkbp:propulsion
|
liquid hydrogen and liquid oxygen
1.6 million pounds
8.4 million pounds
each RS-25 engine produces 400,000 pounds
|
|
gptkbp:public_interest
|
high
high due to lunar exploration goals
|
|
gptkbp:safety_features
|
redundant systems
|
|
gptkbp:safety_measures
|
comprehensive risk assessments
|
|
gptkbp:supporting_structure
|
mobile launcher
|
|
gptkbp:supports
|
specialized transport vehicles
|
|
gptkbp:sustainability_efforts
|
focus on reducing waste
minimizing environmental impact
|
|
gptkbp:transportation
|
gptkb:boat
|
|
gptkbp:upgrades
|
planned for Block 1 B
Block 1 B configuration
|
|
gptkbp:used_for
|
launching crewed missions
|
|
gptkbp:weight
|
2.3 million pounds
|
|
gptkbp:year
|
gptkb:2021
|