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

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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: Page 89 of 227
TRP Work Plan 2005-2007 Description of Activities TEC-SB/7935/dc 12/Feb/09 TRP Reference: T402-10MP Unsteady subscale force measurements within a launch vehicle base buffeting Title: environment Prediction of the unsteady forces on a full-scale, main stage, nozzle is normally obtained via wind tunnel testing. In such wind tunnel testing however, problems arise when the forces on the nozzle need to be evaluated. In the past this has been achieved using heavy instrumentation of the nozzle, to allow integration of unsteady pressure measurements and, thus, the derivation of the forces. This technique has, to date, been proven to be unreliable and the results are sometimes questionable, due to the drastic modification of the model of the nozzle required to accommodate the instrumentation. Based of the above, the proposed TRP activity is defined as follows: 1. In a first step, available literature should be examined and an evaluation of the potential for the separate techniques should be given.2. Secondly, a technical specification for a system, allowing the direct measurement of the unsteady forces on a scale nozzle in a representative environment, should be defined. 3. Finally, the performance of the new system should be: evaluated in testing; compared against the pressure integration techniques already developed; scaled for comparison against available flight data. Deliverables: Tech. Spec of Measurement methodology of unsteady forces on subsc. nozzle (representative of launch vehicle base flow environment). Final report (subsc. test results, comparison with avail. flight data, applicat. w.r.t. assoc. flow structure interations). Current TRL: TRL2 Target TRL: TRL3 Application Need/Date: TRL5 by 2011 Application/Mission: all launchers, future launchers Contract Duration: 24 months SW Clause : - Dossier0 Ref.: T-436 Consistency with Harmonisation Roadmap and Conclusions: Page 90 of 227
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