|
gptkbp:instanceOf
|
rocket engine
|
|
gptkbp:chemicalFormula
|
liquid oxygen
|
|
gptkbp:controls
|
digital control system
|
|
gptkbp:coolingSystem
|
regenerative cooling
|
|
gptkbp:designedBy
|
gptkb:ISRO
|
|
gptkbp:developer
|
approximately $50 million
|
|
gptkbp:documentType
|
converging-diverging nozzle
|
|
gptkbp:engineConfiguration
|
single engine
|
|
gptkbp:environmentalImpact
|
low emissions
|
|
gptkbp:fireDepartment
|
60 bar
|
|
gptkbp:firstFlight
|
1990
|
|
gptkbp:firstMatch
|
1988
|
|
gptkbp:fuelCapacity
|
kerosene
|
|
gptkbp:fuelType
|
liquid propellant
hypergolic ignition
|
|
gptkbp:futurePlans
|
Vikas 3
|
|
gptkbp:hasArea
|
gptkb:Vikram_Sarabhai_Space_Centre
gptkb:Satish_Dhawan_Space_Centre
|
|
gptkbp:hasContent
|
300 seconds
|
|
gptkbp:hasDepartment
|
150 seconds
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Vikas engine
|
|
gptkbp:internationalCooperation
|
none
|
|
gptkbp:launchDate
|
over 30 launches
|
|
gptkbp:manufacturer
|
gptkb:ISRO_Propulsion_Complex
|
|
gptkbp:notableEvent
|
successful lunar mission
successful satellite deployment
successful_Mars_mission
|
|
gptkbp:numberOfEpisodes
|
1
|
|
gptkbp:operationalArea
|
satellite launches
interplanetary missions
|
|
gptkbp:operationalStatus
|
active
|
|
gptkbp:productionCompany
|
1980s
|
|
gptkbp:propulsion
|
6.67
800 kN
|
|
gptkbp:related_engine
|
staged combustion
|
|
gptkbp:relatedPatent
|
gptkb:GSLV_Mk_III
gptkb:GSLV_Mk_II
GSLV_Mk_I
|
|
gptkbp:reliability
|
high
|
|
gptkbp:successor
|
Vikas 2
|
|
gptkbp:usedIn
|
gptkb:GSLV
gptkb:PSLV
|
|
gptkbp:uses
|
Chandrayaan-2
Chandrayaan-1
GSAT series
INSAT series
Mars Orbiter Mission
|
|
gptkbp:weight
|
1,200 kg
|