Feasibility study for the development of a pyro starter
conference paper
Pyro starters can play a role as turbopump starter in liquid propellant propulsion systems by supplying pressurized gas to power turbines for engine start up. For such a purpose, the pyro starters supply a flow of combustion gases with a relatively low flame temperature to the turbines. A feasibility study on the design of a pyro starter for a Korean launch vehicle has been performed through the cooperation between APP, TNO and KARI. In the scope of the feasibility study, critical design parameters were identified from the analysis of the pyro starter requirements and a concept design has been accomplished. Although many design aspects still need further development, this feasibility study has shown a pyro starter performance according to the requirements.
Topics
Combustion gasConcept designsCritical design parametersEngine startFeasibility studiesFlame temperaturesFurther developmentLaunch vehiclePower turbinesPressurized gasPropulsion systemTurbo pumpsCombustionDecision makingDesignLaunch vehiclesLaunchingLiquid propellantsPlanningResource allocationSpacecraft propulsionTurbinesStarters
TNO Identifier
364450
ISBN
9781615679089
Source title
60th International Astronautical Congress 2009, IAC 2009, Daejeon, South Korea, 12-16 October 2009 (Conference code: 80592)
Pages
6752-6758
Files
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