System driven technology selection for future European launch systems. (February 2015)

• Record Type: Journal Article
• Authors: Baiocco, P.; Ramusat, G.; Sirbi, A.; Bouilly, Th.; Lavelle, F.; Cardone, T.; Fischer, H.; Appel, S.
• Is Part Of: Acta astronautica. Volume 107(2015)
• Page Start: 301
• Page End: 316
• Publication Date: 2015-02
• Subjects: 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; FLPP -- ELV -- TRL -- IRL; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2014.10.037
• Languages: English
• ISSNs: 0094-5765

Abstract

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.