|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
deep space missions
reusable launch vehicle
|
|
gptkbp:average_temperature
|
-250 to 600 degrees Celsius
|
|
gptkbp:benefits
|
cancelled project
|
|
gptkbp:challenges
|
thermal management
technical challenges
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:collaboration
|
space agencies
|
|
gptkbp:collaborative_projects
|
NASA engineers
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:community_outreach
|
STEM programs
|
|
gptkbp:control_system
|
computerized control system
digital control system
|
|
gptkbp:cooling_system
|
regenerative cooling
regenerative cooling system
|
|
gptkbp:debut
|
gptkb:1998
2025
|
|
gptkbp:design
|
gptkb:Marshall_Space_Flight_Center
|
|
gptkbp:design_purpose
|
high efficiency
|
|
gptkbp:designed_by
|
gptkb:NASA
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:engine
|
gptkb:advanced_technology
closed cycle
staged combustion cycle
|
|
gptkbp:engine_configuration
|
single engine
|
|
gptkbp:engine_power
|
high performance
high reliability
high thrust-to-weight ratio
|
|
gptkbp:engine_testing_phase
|
development phase
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
|
gptkbp:environment
|
vacuum and atmospheric
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
expandable nozzle
aerospike
|
|
gptkbp:facilities
|
gptkb:NASA_Marshall_Space_Flight_Center
gptkb:NASA_Stennis_Space_Center
|
|
gptkbp:fuel_capacity
|
5 feet
15 feet
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
liquid hydrogen
liquid oxygen and liquid hydrogen
|
|
gptkbp:funding
|
government grants
government funded
|
|
gptkbp:historical_significance
|
next generation propulsion
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
XRS-2200 rocket engine
|
|
gptkbp:ignition_system
|
pyrotechnic
|
|
gptkbp:impact
|
influenced future rocket designs
|
|
gptkbp:is_tested_for
|
gptkb:2001
ongoing
static fire test
|
|
gptkbp:key_people
|
lead engineers
|
|
gptkbp:launch_site
|
gptkb:Cape_Canaveral
gptkb:Kennedy_Space_Center
|
|
gptkbp:launch_vehicle
|
gptkb:Space_Launch_System_Block_1
gptkb:X-33
|
|
gptkbp:legacy
|
lessons learned for future projects
|
|
gptkbp:lifespan
|
10 years
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
gptkb:NASA
|
|
gptkbp:media_coverage
|
extensive
|
|
gptkbp:mission
|
develop advanced rocket engine technology
|
|
gptkbp:number_of_rooms
|
3000 psi
1000 psi
|
|
gptkbp:operational_use
|
future missions
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:partnerships
|
gptkb:commercial_space_companies
|
|
gptkbp:power_off_thrust
|
0 pounds
|
|
gptkbp:production_status
|
in development
cancelled
|
|
gptkbp:project
|
gptkb:Venture_Star
5 years
2020-2030
1996 to 2001
reusable space access
|
|
gptkbp:propulsion
|
22:1
220,000 pounds
cryogenic propellant
|
|
gptkbp:public_interest
|
high
|
|
gptkbp:regulatory_compliance
|
NASA standards
|
|
gptkbp:research_focus
|
advanced propulsion technologies
|
|
gptkbp:safety_features
|
redundant systems
|
|
gptkbp:specific_impulse
|
450 seconds
330 seconds
|
|
gptkbp:upgrades
|
planned enhancements
|
|
gptkbp:used_in
|
gptkb:X-33_vehicle
gptkb:Space_Launch_System
|
|
gptkbp:weight
|
10,000 pounds
1,500 pounds
|