EPIC Gap analysis and resultsepic-src.eu/.../2015/02/Sacristan-Results-of-the-Critical-review-and-Gap-analysis.pdfEPIC Gap Analysis and results/ Gap results . The main long term needs

This project has received funding from the European Union’s Horizon 2020 research and innovation programme under grant agreement No 640199 This presentation reflects only the Consortium’s view. The EC/REA are not responsible for any use that may be made of the information it contains.

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 Driver

PerformancePhysical parametersOperative rangesRobustness and operational lifetime

recurring costsnon recurring costs

Expected saving on the host-system (weight, power etc.)Expected host-System delta performancePossible integration in European launch systems

Starting TRL and relevant justificationDevelopment Planning and Risks AnalysisLevel of dependence on Non European key technogiesLevel of dependence on Non European testing facilities, diagnostic capabilityLevel of dependence on flight qualified technologiesCritical components (PPU, FCU, etc.)

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

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 projectPerformances gain due to disruprtive technology advacementPotential Spin off for cross related fields

Competitiveness

Feasibility

Flexibility

Impact on the host -system

Technical Characteristics

Costs


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)

MEO (e.g. GNSS)

GEO (e.g. telecommunications)

Space Transportation (e.g. launcher kick stages, space tugs)

Space Science, Interplanetary, and Space exploration



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



Thruster technology per mission operation domain Operation

Telecom Earth Observation Scientific Satellites

Exploration Navigation

Orbit raising Ion Engines, HETs, Arcjets, HEMPT, HPT

Ion Engines HETs, Arcjets, HEMPT

Ion Engines HETs, Arcjets, HEMPT

N/A 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.



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)



• 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.



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



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



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



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.



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 ([email protected]) PSA Consortium Workshop Stockholm – 11/02/2015

Documents

EPIC Gap analysis and resultsepic-src.eu/.../2015/02/Sacristan-Results-of-the-Critical-review-and-Gap-analysis.pdfEPIC Gap Analysis and results/ Gap results . The main long term needs