|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
3
|
|
gptkbp:bfsParent
|
gptkb:spacecraft
|
|
gptkbp:application
|
abort scenarios
|
|
gptkbp:challenges
|
high reliability requirements
|
|
gptkbp:check_in_time
|
approximately 5 seconds
|
|
gptkbp:collaborations
|
gptkb:NASA
|
|
gptkbp:community_engagement
|
high public interest
|
|
gptkbp:controls
|
digital control system
gimbal control
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:design
|
gptkb:rapid_response
Space X engineering team
|
|
gptkbp:developer
|
gptkb:NASA's_Commercial_Crew_Program
|
|
gptkbp:durability
|
designed for multiple uses
|
|
gptkbp:emergency_services
|
escape from launch pad
|
|
gptkbp:engine
|
8
staged combustion cycle
clustered configuration
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:facilities
|
Space X Rocket Development and Test Facility
|
|
gptkbp:first_flight
|
gptkb:2010
gptkb:2015
|
|
gptkbp:fuel_capacity
|
3.5 feet
high efficiency
1.5 feet
|
|
gptkbp:fuel_type
|
pressurized tanks
monomethylhydrazine (MMH)
|
|
gptkbp:future_plans
|
upgraded versions
|
|
gptkbp:historical_significance
|
first crewed spacecraft with abort engines
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Super Draco engines
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:inspiration
|
Apollo program escape systems
|
|
gptkbp:integrates_with
|
gptkb:Dragon_2_spacecraft
|
|
gptkbp:is_a_supporter_of
|
Demo-1 mission
|
|
gptkbp:is_designed_for
|
crew escape system
|
|
gptkbp:is_tested_for
|
developmental testing
|
|
gptkbp:launch_date
|
multiple launches per year
|
|
gptkbp:launch_site
|
gptkb:Crew_Dragon_launch_system
gptkb:Cape_Canaveral_Space_Force_Station
|
|
gptkbp:launch_vehicle
|
gptkb:Falcon_9
|
|
gptkbp:manufacturer
|
gptkb:Space_X
|
|
gptkbp:material
|
aluminum alloy
|
|
gptkbp:operational_area
|
crew transport missions
|
|
gptkbp:operational_status
|
active
|
|
gptkbp:part_of
|
Space X's safety protocols
|
|
gptkbp:performance
|
high thrust-to-weight ratio
|
|
gptkbp:project
|
next-generation crewed missions
|
|
gptkbp:propulsion
|
16,000 pounds
hypergolic propellant
267:1
|
|
gptkbp:regulatory_compliance
|
FAA approved
|
|
gptkbp:safety_features
|
crew safety
|
|
gptkbp:social_structure
|
nitrogen tetroxide (N2 O4)
|
|
gptkbp:storage
|
pressurized tanks
|
|
gptkbp:type
|
gptkb:rocket
|
|
gptkbp:used_in
|
gptkb:Dragon_spacecraft
|
|
gptkbp:weight
|
approximately 60 pounds
|