Abstract In the framework of the next generation launcher activity at ESA, a top-down approach and a bottom-up approach have been performed for the identification of promising technologies and alternative conception of future European launch vehicles. The top-down approach consists in looking for system-driven design solutions and the bottom-up approach features design solutions leading to substantial advantages for the system. The main investigations have been focused on the future launch vehicle technologies. Preliminary specifications have been used in order to permit sub-system design to find the major benefit for the overall launch system. The development cost, non-recurring and recurring cost, industrialization and operational aspects have been considered as competitiveness factors for the identification and down-selection of the most interesting technologies. The recurring cost per unit payload mass has been evaluated. The TRL/IRL has been assessed and a preliminary development plan has been traced for the most promising technologies. The potentially applicable launch systems are Ariane and VEGA evolution. The main FLPP technologies aim at reducing overall structural mass, increasing structural margins for robustness, metallic and composite containment of cryogenic hydrogen and oxygen propellants, propellant management subsystems, elements significantly reducing fabrication and operational costs, avionics, pyrotechnics, etc. to derive performing upper and booster stages. Application of the system driven approach allows creating performing technology demonstrators in terms of need, demonstration objective, size and cost. This paper outlines the process of technology down selection using a system driven approach, the accomplishments already achieved in the various technology fields up to now, as well as the potential associated benefit in terms of competitiveness factors.
Highlights Technology and conception for launch system optimization. Demonstration activity to support technology maturation. Top-down/bottom-up approach for system loop and technology selection. Phasing with European launch vehicles development programs. Technology for cost reduction and system optimization.
System driven technology selection for future European launch systems
Acta Astronautica ; 107 ; 301-316
2014-10-27
16 pages
Article (Journal)
Electronic Resource
English
AFP , Automatic Fiber Placement , AoA , Angle of Attack , AVD , Anti-Vortex Device , CFRP , Carbon Fiber Reinforced Polymer , COTS , commercial off-the-shelf , CX , LOX/LCH4 1st stage , DEC , Double Engine Centaur , ELV , Expendable Launch Vehicle , EMA , Electro Mechanical Actuator , EMC , Electro Magnetic Compatibility , ETF , Engine Thrust Frame , FLPP , Future Launchers Preparatory Program , FSW , Friction Steer Welding , GNC , Guidance Navigation and Control , GNSS , Galileo Navigation System , GTO , Geostationary Transfer Orbit , HMS , Health Monitoring System , HH , Two LOX/LH2 stages launch vehicle , HX , LOX/LH2 1st stage , HY , LOX/LH2 upper stage , IRL , Integration Readiness Level , ISS , InterStage Structure , ITS , InterTank Structure , LEO , Low Earth Orbit , LV , launch vehicle , MEMS , Micro-Electro Mechanical System , MDHB , Modular Data Handling Block , NDI , Non Destructive Inspection , NRC , Non-Recurring Cost , OTS , On-The-Shelf , PDR , Preliminary Design Review , PL , Pay Load , PLC , Power Line Communication , PX , Solid propellant 1st stage , PI , Solid propellant 2nd stage , RC , recurring cost , RoM , Rough order of Magnitude , RT , Research and Technology , SEC , Single Engine Centaur , SRM , solid rocket motor , S/S , subsystem , SW , SoftWare , TDVP , Technology Development and Verification Plan , TIG , Transient Inert Gas , TPS , Thermal Protection System , TRL , Technology Readiness Level , TSP , Time and Space Partitioning , US , upper stage , VPPA , Variable Polarity Plasma Arc , WRT , with respect to
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