document title / titre du document TRP W ORK PLAN ... - emits - ESA

TRP Work Plan 2005-2007
Description of Activities
TEC-SB/7935/dc
12/Feb/09
4.4 - Propulsion / Advanced Liquid Propulsion
TRP Reference:
Title:
MPC-846
Acquisition and Evaluation of Cryo-Solid Propulsion: Additional Testing
Conventional solid rocket propellants have specific impulses that are low compared to cryogenic liquids. Cryogenic Solid
Propellants (CSP), defined as frozen propellants that normally are liquids or gases, compare very favourably with conventional
ones. The objective of this activity is to establish a firm evaluation of CSP in terms of applicability, performance, operability
and cost. It is also necessary to establish the theoretical and experimental foundations of CSP-grain design, production,
integration, handling, ignition, combustion etc and rapidly provide the knowledge base of a prototype demonstrator version of
a CSP-motor. Experimental work carried out as part of this activity shall include investigations of strand burner and tests with
sub-scale motors. This CCN will continue the experimental work.
Deliverables:
Test data
Current TRL: TRL2 Target TRL: TRL2/3 Application Need/Date: TRL5 by 2020
Application/Mission: Future launchers Contract Duration: 18 months
SW Clause : - Dossier0 Ref.: T-7741
Consistency with Harmonisation
Roadmap and Conclusions:
TRP Reference:
Title:
T402-05MP
Scaling of Thermal Cavitation Effects on Cavitation-Induced Instabilities
Thermal cavitation effects, due to evaporation or condensation phenomena at the cavity interface, have long been known to
deeply affect the steady performance of cavitating turbopumps. The main objective of the activity consists in investigating
whether and to what extent established scaling laws developed for steady thermal cavitation effects are also applicable for
correlating dynamic cavitation phenomena, cavitation-induced instabilities, unsteady fluid forces and moments acting on
turbopump inducers. Thermal cavitation effects must be investigated by adjusting the liquid temperature as necessary for
adequately scaling the pump prototype operating at design conditions (flow coefficient and cavitation number) with the given
propellant. Instabilities must be characterized by both high-speed video movies and flow instrumentation (pressure and flow
transducers), so to measure the instantaneous unsteady fluid forces acting on the rotors. Finally, some of the unsteady
cavitation phenomena observed during the test campaign should be simulated and analysed with a 3D unsteady cavitation
code, taking into account the thermal effects.
Deliverables:
Database and test data for validation of SW tools.
Current TRL: N/A Target TRL: N/A Application Need/Date: TRL5 by 2007
Application/Mission: ArianeV and evolutions. Contract Duration: 18 months
SW Clause : - Dossier0 Ref.: T-604
Consistency with Harmonisation
Roadmap and Conclusions:
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