|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
suborbital flight
|
|
gptkbp:challenges
|
thermal and pressure management
|
|
gptkbp:check_in_time
|
approximately 90 seconds
|
|
gptkbp:collaborator
|
NASA and USAF
|
|
gptkbp:combustor_type
|
gas-generator cycle
|
|
gptkbp:control_system
|
manual and automated systems
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:cultural_impact
|
featured in documentaries and films
|
|
gptkbp:design
|
based on fluid dynamics and thermodynamics
|
|
gptkbp:designed_by
|
gptkb:North_American_Aviation
|
|
gptkbp:development
|
1955-1960
|
|
gptkbp:educational_use
|
case studies in engineering courses
|
|
gptkbp:engine
|
controlled shutdown
start sequence required
|
|
gptkbp:engine_configuration
|
detailed in technical manuals
single-chamber engine
|
|
gptkbp:engine_type
|
gptkb:XLR99-RM-1
|
|
gptkbp:environmental_impact
|
considered in design phase
|
|
gptkbp:exhaust_system
|
converging-diverging nozzle
|
|
gptkbp:first_flight
|
gptkb:1960
|
|
gptkbp:fuel_capacity
|
3 ft
12 ft
|
|
gptkbp:fuel_economy
|
optimized for performance
|
|
gptkbp:fuel_type
|
liquid oxygen and RP-1
cryogenic tank
|
|
gptkbp:future_prospects
|
inspired new technologies in propulsion.
|
|
gptkbp:has_limitations
|
limited to specific missions
|
|
gptkbp:historical_significance
|
pioneered rocket propulsion technology
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
XLR99 rocket engine
|
|
gptkbp:ignition_system
|
hypergolic ignition
|
|
gptkbp:impact
|
advanced propulsion research
|
|
gptkbp:influenced
|
future rocket engine designs
|
|
gptkbp:invention
|
multiple patents filed
|
|
gptkbp:involved_technology
|
aerodynamics and materials science
|
|
gptkbp:is_tested_for
|
gptkb:X-15_flight_tests
gptkb:Edwards_Air_Force_Base
Rocketdyne test facility
|
|
gptkbp:legacy
|
influential in space exploration
|
|
gptkbp:maintenance
|
requires specialized knowledge
|
|
gptkbp:material
|
high-strength alloys
|
|
gptkbp:number_of_rooms
|
1,000 psi
|
|
gptkbp:operational_use
|
research and testing
|
|
gptkbp:oxidizer_storage
|
cryogenic tank
|
|
gptkbp:performance
|
high altitude flight
|
|
gptkbp:production_status
|
retired
|
|
gptkbp:propulsion
|
no
60,000 lbf
|
|
gptkbp:publications
|
numerous scientific papers
|
|
gptkbp:retirement_year
|
gptkb:1970
|
|
gptkbp:safety_record
|
generally safe with precautions
|
|
gptkbp:successor
|
gptkb:XLR11_rocket_engine
|
|
gptkbp:successor_programs
|
gptkb:Space_Shuttle
|
|
gptkbp:type
|
gptkb:Team_Rocket
|
|
gptkbp:used_in
|
gptkb:X-15_rocket_plane
|
|
gptkbp:water_requirement
|
1,000 lb/min
1,500 lb/min
|
|
gptkbp:weight
|
1,500 lb
|
|
gptkbp:bfsParent
|
gptkb:X-15_Flight_11
gptkb:X-15_Flight_12
gptkb:X-15_Flight_15
gptkb:X-15_Flight_17
gptkb:X-15_Flight_22
gptkb:X-15_Flight_26
gptkb:X-15_Flight_4
gptkb:X-15_Flight_45
gptkb:X-15_Flight_46
gptkb:X-15_Flight_9
gptkb:Hercules_X-15
gptkb:XLR11_rocket_engine
gptkb:X-15
gptkb:X-15_A-2
gptkb:X-15_Flight_3-65-100
|
|
gptkbp:bfsLayer
|
5
|