EPIC Gap analysis and results PSA Consortium Workshop Stockholm 11/02/2015
EPIC Gap Analysis and results/ Content Content: Scope Process Missions Analysis (i.e GEO (OR + SK)) Gaps results Gap analysis is the comparison of actual performance with potential or desired performance
EPIC Gap Analysis and results/ Scope EP Technology & components to be addressed EP Thrusters Gridded Ion Engines (GIE) FEEP thrusters Hall Effect Thrusters (HET) High Efficiency Multistage Plasma Thrusters (HEMPT) Pulsed Plasma Thrusters (PPT) Arcjets Resistojets Magneto Plasma Dynamic thrusters (MPDs) Colloid thrusters Quad Confinement Thrusters (QCT) Electrodeless plasma thrusters: (like HPT (Helicon Plasma Thrusters), etc.) EP-related components Pointing Mechanisms Pressure Regulators and Flow Management elements Power Processing Units Power Generation and Distribution Test Facilities and Diagnostics Development tools Cathodes/Neutralisers New concepts and technologies
EPIC Gap Analysis and results/ Process EP technology and components: status, competitiveness, TRL and actual performances Missions (GEO, LEO, MEO, Space Transportation, Interplanetary), and type of EP functions/ maneuvers Mission requirements, specifications and new expected performances Market analysis, trends and competition Definition of criteria, guidance and parameters for the comparison and analysis
EPIC Gap Analysis and results/ Process EPS Technical parameters Mission Total Impulse Thrust level Specific Impulse Thruster input Power Maneuvering capability Thrust vector orientation capability Throttleability Power to Thrust Ratio
EPIC Gap Analysis and results/ Process CRITERIA Technical Characteristics Driver Performance Physical parameters Operative ranges Robustness and operational lifetime Costs Impact on the host -system recurring costs non recurring costs Expected saving on the host-system (weight, power etc.) Expected host-system delta performance Possible integration in European launch systems Feasibility Starting TRL and relevant justification Development Planning and Risks Analysis Level of dependence on Non European key technogies Level of dependence on Non European testing facilities, diagnostic capability Level of dependence on flight qualified technologies Critical components (PPU, FCU, etc.) Flexibility Versatility w.r.t. Different classes of missions (for each EP engine identify the possible classes of missions) Versatility w.r.t. Different applications (for each class of missions identify the possible applications) Versatility w.r.t. propellants (compatibility whith different propellant) Throttability, controllability ( i.e. fine thrust regulation, modularity ) Commonalities w.r.t. other EP building blocks Scalability Competitiveness Expected competitive position in the european and non european market (long term scenarios) Valorization of competiencies/technologies already developed at european level in other national and international project Performances gain due to disruprtive technology advacement Potential Spin off for cross related fields
EPIC Gap Analysis and results/ Missions The different types of missions and requirements addressed are: LEO & VLEO (e.g. Earth Observation, Earth Science, CubeSats, NanoSats) Space Science, Interplanetary, and Space exploration MEO (e.g. GNSS) Space Transportation (e.g. launcher kick stages, space tugs) GEO (e.g. telecommunications)
EPIC Gap Analysis and results/ Missions Mission operation domain and function Orbit raising: transfer from GTO to GEO Station keeping in GEO Interorbital transfer Interplanetary cruise Continuous LEO operations (air-drag control) Attitude control: extremely fine and/or agile
EPIC Gap Analysis and results/ Missions Thruster technology per mission operation domain Operation Telecom Earth Observation Scientific Satellites Orbit raising Ion Engines, HETs, Arcjets, HEMPT, HPT Ion Engines HETs, Arcjets, HEMPT Ion Engines HETs, Arcjets, HEMPT Exploration N/A Navigation Ion engines, HETs, Arcjets, HEMPT, QCT Interplanetary Primary Propulsion N/A N/A Ion Engines HET, MPD, HEMPT, HPT Ion Engines HET, MPD, Arcjets, HEMPT, HPT N/A Station Keeping Ion Engines HETs, HEMPT FEEP, HETs, Ion Engines, Arcjets, Resistojets, HEMPT, HPT, PPT FEEP, Ion Engines, HEMPT, HETs, PPT N/A HETs, Ion Engines, Arcjets, HEMPT, QCT Fine Attitude Control N/A FEEP, Ion Engines, colloids FEEP, Ion Engines, colloids N/A N/A De-orbiting Ion Engines HETs, HEMPT, PPT Ion Engines HETs, HEMPT, PPT Ion Engines HETs, HEMPT, PPT N/A HETs, Ion Engines, Arcjets, HEMPT, QCT
EPIC Gap Analysis and results/ Analysis GEO Mission / Orbit Raising vs Station Keeping Existing thruster technologies / ISP vs T/P region for orbit raising
EPIC Gap Analysis and results/ Analysis GEO Mission / Orbit Raising vs Station Keeping Existing thruster technologies / ISP vs T/P region for station keeping
EPIC Gap Analysis and results/ Gap results The generic needs and gaps to be fulfilled for the long term Reduction of cost per transponder Reduction of time to orbit/eor duration Satellite system compatibility Multi-launcher compatibility Sub-system cost reduction Improvement of operational constraints Decrease of xenon consumption Extension of the mission lifetime Cost reduction (main contributor being the PPU) Increase of reliability and autonomy Standardisation of PPU (multi-thruster compatibility) Non-dependence (e.g. avoiding non-european restrictions) Innovative power supply design: different voltages, direct drive, different modelling tools, etc. Breakthrough power supply technologies, optimization of mission strategy, and new propulsion technologies Alternative propellants to Xenon.
EPIC Gap Analysis and results/ Gap results Regarding the EPS Performances, these are high level requirements to be complied with by the different technologies in typical missions: VLEO station keeping, mission: 400kg-class spacecraft have shown that required thrust is around 20mN, Isp 1300s and power 300W. Small Satellites: Further development of new technologies; Availability of 500W-class thruster for medium satellites & constellations: 200-800W; thrust level 13-40mn with Isp>1,300s. NanoSats: Nanosats is a fast growing «market» and is prone to dissemination and outreach activities. The need for propulsion on such spacecraft is growing, and EP offers a very interesting technical solution; ( 2-5W power, thrust between 0.1-0.3mN and Isp within 500-1000s; Minimum Impulse Bit between 0.1-0.5mN.s, Subsystem mass below 1kg, Cost below 20k. Potential technologies include PPT, VAT, colloid/electrospray. MEO missions: Reliability >0.997; Thrust>250mN; 1,650<Isp<3,000s)
EPIC Gap Analysis and results/ Gap results GEO missions: low cost EP for GEO station keeping (1.5-2.5kW); low cost EP for GEO EOR (5kW-class). Dual-mode operation (0.3N @ 5kW ; Isp>2,500s for SK). GEO missions with HET : High power with different operating points : 4-10kW at 300-800V; >0.6N at 10kW and Isp >2500s at 800V with Itot>20MN.s GEO missions with GIE : 5-8kW, Isp>4,000s and Itot>15MNs; decrease of cost (both thruster and PPU), increase T. LEO missions: EP seems to be a promising technology for LEO satellites, with possible applications for EO, radar, and telecommunications. High Isp for countering air drag or formation flying; 4-50mN, 3,000-5,000s; thrust modulation between 5-100% (main propulsion); 500-1500µN, >1,000s, thrust modulation 0.1-100%, thrust resolution 0.5µN (µprop); Space Transportation (space tugs, kick-stages, multi-mission spacecraft): High-level requirements: >2N thrust, Isp>2,000s, 22kh lifetime, 20k cycles. High power (>20kW) thruster with flexible Isp and better efficiency (>60%), High power PPU, High efficiency SA, Direct drive, Alternative propellants.
EPIC Gap Analysis and results/ Gap results The main long term needs by technology combining gaps and objective performances are the following ones: Hall Effect Thruster SYSTEMS (future technology improvements) High voltage operation (high specific impulse) High power (10-20 kw) Throttleability Alternative propellants Clustered or multi-channel configurations Increased total impulse Direct drive Double operation points
EPIC Gap Analysis and results/ Gap results Hall Effect Thruster SYSTEMS Cont. (future technology improvements) The concept of a multi-mission EP platform has also been discussed, with a possible use as a satellite module, a launcher upper stage, an exploration module or a service module for active debris removal. Power Conditioning Units Cost reduction and Industrialization
EPIC Gap Analysis and results/ Gap results ION ENGINE SYSTEMS (Future technology improvements) High power ion engines with high specific impulse and low power to thrust ratio, double operation points and long lifetime. Low power ion engines for formation flying and drag compensation. High throttleability, high specific impulse, Ion engine with 3 or 4 grids to improve specific impulse and lifetime. New propellants utilisation. Cost reduction and Industrialization
EPIC Gap Analysis and results/ Gap results HEMPT (future technology improvements) The HEMP thruster reduces plasma-wall interactions, thus allowing longer lifetime. Besides, the ionization and acceleration zones are well separated, which makes dual mode operation possible. Higher power versions will be required in the future. Increase T and power. Increase TRL. Development of µn thrusters HEMPT for future science mission New propellants utilisation. Cost reduction and Industrialisation.
EPIC Gap Analysis and results/ Gap results NEW EP Concepts, Components, Test Facilities, Modelling, PCU New Concepts, Power Sources MICROPRULSION (FEEPs, PPTs, MEMS colloids, etc.) CATHODELESS PROPULSION: Helicon Antenna Thrusters (with high thrust to power ratio, long lifetimes, large throttleability, thrust vectoring capability, propellant friendly); ECR thruster, PEGASES, NEPTUNE, etc. QCT, Ponderomotive thruster, etc. Valves, pressure regulators, pressure transducers, filters, etc. Test facilities, diagnostics Modelling tools for thruster design and spacecraft thruster interaction Novel thrust vectoring solutions New PCU concepts (modularity, no potting, etc.) New Power systems, Solar arrays, direct drive, etc
Many Thanks for your attention Jorge LOPEZ REIG, CDTI (jorge.lopez@cdti.es) PSA Consortium Workshop Stockholm 11/02/2015