From Smart-1 to Galileo G2, Snecma is designing, developing and operating optimized HET propulsion architectures G.TURIN gilles.turin@sncema.fr A.LORAND anthony.lorand@snecma.fr
INTRODUCTION For more than 30 years, Snecma develops and produces Hall Effect Thrusters Thruster family from 300W to 20kW Thrust from 15mN to 1N ISP up to 2500s Moreover, Snecma studies, develops and produces complete and adapted Electric Propulsion Systems For probe applications For commercial applications For new applications Galileo G2 (EGEP) TUG ADR 1 / FLP 14-340 System EPIC - Nov 2014
SYSTEM BACKGROUND : SMART-1 PROGRAM Complete Electric Propulsion System developed and managed by Snecma Design, assembly and test including PPU, and Xenon management Cumulated operating time: 5 000 hrs (world record for HET) Launch in September 2003 From Earth GTO to Moon LMO transfer by Electric Propulsion Moon orbit capture November 2004 In-flight demonstration of PPS 1350 large throttling range 460 to 1200 W Input Power Earth to Moon with 75kg of Xe Image ESA 2 / FLP 14-340 System EPIC - Nov 2014
SYSTEM BACKGROUND : THRUSTER MODULES TMA developed by Snecma for Eurostar3000 2 TMAs per satellite for Control of orbit inclination (NSSK) and eccentricity Dumping momentum wheels Includes 2 HET Thruster units (nominal / redundant) on Thruster Orientation Mechanism + Filter Unit 17 TMAs already produced to date 14 currently on orbit 90 years and 25,000 hrs cumulated on-orbit (since 2004) EPTA developed by Snecma for SGEO 2 EPTA branches (nominal / redundant) per satellite for all in-orbit maneuvers (NSSK, EWSK, AOCS) 4 HET thruster units per branch PPU + FU + tubing & harness External Thruster Selection Unit for 1:4 switching ETSU PPU INMARSAT-4 AIRBUS DS courtesy STM SGEO ESA courtesy 3 / FLP 14-340 System EPIC - Nov 2014
CURRENT STUDIES : GALILEO G2 EGEP PROJECT Snecma has proposed an advanced Electric Propulsion System for Next Generation of Galileo (EGEP - ESA Contract) Increase launcher flexibility by using Electric Propulsion transfer (LEO / GTO) Reduce launch cost by using Electric Propulsion transfer High Level Requirements Transfer duration from LEO or GTO injection < 1 year High total impulse to allow several inclinaison Single failure tolerance High competitiveness (ceiling price) Industrial capability Demonstrate a TRL 5 in 2015 4 / FLP 14-340 System EPIC - Nov 2014
CURRENT STUDIES : GALILEO G2 EGEP PROJECT Snecma EPS proposal based on PPS 1350-E evolution to reach EGEP requirements PPS 1350-E C2G Implementation of a new ceramic able to increased by 50% the total impulse of the PPS 1350-E 5 MN.s per thruster (2,5kW / 140mN / 1800s) 2 thrusters firing simultaneously Should avoid thruster mechanism (throttling) Design of an ETSU and the associated electrical architecture in order to limit PPU number while achieving tolerance to any equipment single failure TRL 5 reached by mid-2015 PPU, FU and Thruster coupled test 2000h endurance test beginning of 2015 5 / FLP 14-340 System EPIC - Nov 2014
CURRENT STUDIES : EASE & ADR Snecma studies (CNES Contract) an advanced Electric Propulsion System for multi-mission stage (EASE) EPS architecture From tank to thruster From solar panel to PPS Thermal management Equipments draft Alternate propellant Cryogenic tank Direct Drive Unit Module layout and budget Preliminary mission trajectory Snecma studies (Primes Contracts) an advanced Electric Propulsion System for Active Debris Removal (ADR) Thruster blowing concept (one thruster to propel debris chaser and one thruster to push debris) EPS architecture Courtesy CNES Courtesy CNES 6 / FLP 14-340 System EPIC - Nov 2014
TECHNOLOGICAL CHALLENGES TOWARD THE FUTURE To optimize HET propulsion architecture and cost, Snecma is preparing the technological challenges toward the future To limit Xenon cost impact, study and firing test with alternative propellant (Kr TRL 4 / Ar TRL 2 ) Firing campaign at 1.5kW, 5kW and 20kW done in 2013 For orbit transfer mission with several on-board Xe metric tons (TUG, ADR, ), cost savings is quantifiable in Millions euros To reduce High Power electronics cost and thermal dissipation constraints, studies of Direct Drive Unit (coupled with Organic High Voltage solar panel >250V) in replacement of current PPU High Power electronics cost savings should be quantifiable in M Breadboard design carried out TRL 2 OHV solar panel - Courtesy DISASOLAR To simplify EPS architecture and thruster layout, analysis of cluster architecture and simultaneous firing test Firing test in 2012 TRL 4 7 / FLP 14-340 System EPIC - Nov 2014
CONCLUSION Snecma is preparing the technological innovative solutions allowing to optimize EP system (cost and mission performance) High total impulse thruster (Ceramic improvement, magnetic topology ) Alternate propellants Simplified electrical architecture (DDU) Cluster and simultaneous firing Snecma, through its competences in thruster, the key factor of an EP system, address the main space propulsion system challenges from exploration to telecommunication applications. Space TUG propulsion system ADR chaser propulsion system EGEP (Galileo G2) propulsion system THANK YOU for your attention 8 / FLP 14-340 System EPIC - Nov 2014