space-28-tec-2020 strategic research cluster in-space...

H2020 Programme 2018-2020

SPACE-28-TEC-2020

Strategic Research Cluster – In-space electrical

propulsion and station keeping

Guidance document

Version 1.0

5 November 2019

Table of contents

1. INTRODUCTION ....................................................................................................... 2

2. OVERVIEW OF THE SRC ON IN-SPACE ELECTRICAL PROPULSION

AND STATION KEEPING ........................................................................................ 2

2.1. Objectives of the document ............................................................................... 3

2.2. The roadmap of the SRC ................................................................................... 3

2.2.1. SRC roadmap and evolution ................................................................ 4

2.2.2. Roadmap for incremental technologies ............................................... 5

2.2.3. Roadmap for disruptive technologies ................................................ 10

2.3. Conclusion ....................................................................................................... 10

A - INCREMENTAL LINE .............................................................................................. 12

A1 - Low Power (200 W-700 W) for LEO Applications & Constellations -

Telecommunications ........................................................................................ 18

A2 - Medium Power (> 3.0 kW for SK and > 5.0 kW for EOR) for all

Incremental Technologies (HET/GIE/HEMPT) Project activities .................. 21

A3 - High Power (> 20 kW) for all Incremental Technologies EPS activities

oriented to (HET/GIE/HEMPT) ...................................................................... 24

ACRONYMS & ABBREVIATIONS ............................................................................... 26

Note: The present guidelines complement the Space-28-TEC-2020 Call text with specific

expectations.

As a foreword, the following is clarified:

- The Commission now expects to fund projects according to three ranges of

power, a change from the funding by technology alone which applied to the

COMPET-3-2016-a Call. Reference to a Phase 2 in the Call text should be

understood as the period of implementation of the selected SPACE-28-TEC-2020

projects.

- Applicants may build on the results obtained from a bread board model developed

outside the COMPET-3-2016-a call as long as the technology has reached the

level of maturity expected in the COMPET-3-2016 Call.

2

1. INTRODUCTION

This paper presents specific guidelines for the applicants to topic SPACE-28-TEC-2020

(In-Space electrical propulsion and station keeping), to be implemented through a

Strategic Research Cluster (SRC).1

The distinct nature of these projects responds to the demand inserted in the Specific

Programme for Horizon 2020 (Council Decision 2013/743/EU) that [The implementation

will, where appropriate, be based on strategic research agendas developed in consultation

with the Member States and National Space Agencies, ESA, stakeholders from European

space industry (including SMEs), academia, technology institutes and the Space

Advisory Group].

SRCs are implemented through a system of grants connected among them and

consisting of:

1) “Programme Support Activity” (PSA): The main role of the PSA is to elaborate a

roadmap and implementation plan for the whole SRC (referred to hereafter as the

SRC roadmap) and provide advice on the calls for operational grants. In 2014

interested consortia were invited to apply for one PSA grant for each of the

identified SRCs: “In-space electrical propulsion and Station keeping” and “Space

Robotics Technologies”. The PSA is also expected to contribute to the assessment of

the evolution (and results) of operational grants.

2) Operational grants: In on going and future work programmes (2016, 2019 and

2020), and on the basis of the SRC roadmap and the PSA advice for the calls, the

Commission is expected to publish calls for “operational grants”. The work

programmes determine whether they are considered research and innovation grants

(100%) or innovation grants (70%). The operational grants address different

technological challenges identified in the roadmap. The objective of this system of

grants is that the expected results of each individual grant would, when taken

together, achieve the overall objective of the SRC.

Each individual grant within the SRC (either the PSA or operational grants) will follow

the general principles of Horizon 2020 in terms of proposals, evaluation, selection

process and legal obligations. However, to ensure the effectiveness of the SRC’s

operation overall, some specific provisions are necessary.

2. OVERVIEW OF THE SRC ON IN-SPACE ELECTRICAL PROPULSION AND STATION

KEEPING

EPIC stands for "Electric Propulsion Innovation & Competitiveness". EPIC is the PSA

for the SRC on “In-space electrical propulsion and station keeping”. EPIC is a

Coordination and Support action (grant number 640199) started in October 2014 which

will be extended with a new proposal of the PSA consortium to cover 2020-2024 time

frame.

1 The work programme contains a reference to a set of specific guidelines for applicants which are those

developed here. However, these guidelines are to be understood as guidance and do not supersede (or

derogate from) the legal obligations contained in the work programme and basic legal texts for H2020.

3

2.1. Objectives of the document

This document, prepared with the technical contents supplied by the Programme Support

Activity (PSA) EPIC, contains the high level description of work, in terms of goals and

achievements, for the purpose of guiding potential applicants and evaluation experts.

Requirements and guidelines for each activity are given in terms of numbers and

rationale, for each application and for each technology that shall be applicable to any

proposal which will be submitted in response of SPACE-28-TEC-2020.

2.2. The roadmap of the SRC

The SRC on in-space electrical propulsion (EP) and station keeping follows a roadmap

developed in EPIC and updated in 2019. The EPIC roadmap is based on a critical review

and gap analysis to match the identified requirements and the available perspectives

electric of propulsion systems (EPS) and EPS-related technologies. The EPIC roadmap

has been updated taking into account the Market analysis and results of the 2016 calls as

well as the conclusions of the different EPIC workshops.

Definition: An Electric Propulsion System is composed by four different building

blocks:

o The thruster components, which includes the thruster itself (discharge chamber,

anode, grids) and it(s) cathode(s) or neutraliser(s)

o The propellant components or fluidic management system, including the

propellant tanks, valves, filters, pipes, pressure regulators, mass flow controllers

o The power components, which includes the PPU, thruster switching unit and

other components such as electrical filter unit for an HET

o The pointing mechanisms (or thrust orientation mechanism), including the

alignment mechanism and electronics, as an option on the EPS.

A schematic is presented in Figure 1. For the EPIC Roadmap and the objectives of

SPACE-28-TEC-2020, the EPS does include neither the thrust orientation mechanisms

nor the tanks, and therefore is composed of the thruster, the PPU, the fluidic

management system, and other power components only.

Thruster components

Power Components

Pointing Mechanism (optional)

Fluidic management system and Propellant tanks

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Figure 1: Electric Propulsion System Main components

The main target of the EPIC roadmap is to increase the competitiveness of the EP

systems developed in Europe. The expected competitive position in the European and

non-European markets takes into consideration:

future missions,

valorisation of competencies/technologies already developed at European level in

other national, European and/or international projects,

performances gain achieved through disruptive technology advancement,

potential spin-off initiatives for cross-related fields,

integration capability within launch systems worldwide.

The SRC roadmap is structured along two lines of developments: incremental and

disruptive technologies. The SRC roadmap is developed taking into account two phases,

a first one starting with the 2016 Call, and a second one starting with the 2019

(disruptive) and 2020 (incremental) Calls.

2.2.1. SRC roadmap and evolution

The SRC roadmap prepared by EPIC for the incremental and disruptive technologies

for electric propulsion foresee two subsequent phases, one starting with the 2016 Call,

and the other one starting with the 2019 Call and 2020 Call:

• Phase 1 = Horizon 2020 Space Work Programme 2016 and the SRC Operational

Grants (OGs) funded through the COMPET-3-2016 call topic.

• Phase 2 = Horizon 2020 Space Work Programmes 2019 and 2020 and the SRC

Operational Grants (OGs) funded through the SPACE-13-TEC-2019

and SPACE-28-TEC-2020 call topics.

Figure 3 provides an overview of the high-level SRC Roadmap evolution. In Phase 1, the

basis was stated for achieving the final aim of the SRC “In-Space Electrical propulsion”:

European technical leadership and economic competitiveness on Electric Propulsion at

world level. To that extend, the most promising technologies are supported and enabled

to reach higher levels of maturity and TRLs, while proving their suitability for mid to

long term identified or new applications needs.

SRC 2016 Call was focused on the challenge of enabling major advances in Electric

Propulsion for in-space operations and transportation, in order to contribute to guarantee

the leadership through competitiveness and non-dependence of European capabilities in

electric propulsion at world level within the 2020-2030 timeframe, always in coherence

with the existing and planned developments at national, commercial and ESA level.

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Phase 2 with SRC 2019 Call and SRC 2020 Call foresees the continuation of the two

lines of developments (incremental and disruptive technologies). The objective for this

second phase is to support the more promising technologies developed in Phase 1

towards higher TRLs and taking into account the optimization of the recurring costs

during the design phase in order, at the end of the Phase 2, to achieve the SRC

expectations: first, to be ready to be chosen for a potential IOD/IOV, and secondly to

allow the developed EPS products to become competitive on the electric propulsion

market at world level within the 2020-2030 timeframe.

2.2.2. Roadmap for incremental technologies

The challenge is enabling incremental advances in technologies already under

development which require major advances in the development of the thruster itself and

its equipments (including power processing unit (PPU), feeding systems, etc.), in order to

increase substantially their TRL at product level to enable them in-orbit in a short-to-

medium timeframe to cope with the market demand.

The term "incremental" technologies refers to the most mature technologies, i.e. the ones

with high TRL and possibly with flight heritage, with the physical principles rather well

understood, and with established performances in all of the relevant parameters like

thrust, specific impulse (Isp), power/thrust ratio, total impulse, and lifetime. The analysis

performed focuses the incremental EPS in those based in three thruster types:

Hall Effect Thruster (HET),

Gridded Ion Engines (GIE), and

High Efficiency Multistage Plasma Thrusters (HEMPT).

The three incremental technologies which have been maturated during the incremental

part of the 2016 call have individual strengths and weaknesses, which make them more

competitive for certain applications and less competitive for others.

The advantage of having several mature technologies in the portfolio is a particular

strength of the European EP scene. This will allow a high flexibility to react to possible

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changes of the satellite market needs and unforeseen developments of the launcher

market, giving to the European stakeholders a strategic position.

The SRC roadmap developed by the EPIC consortium addresses all three technologies in

the incremental line. It has allowed the three types of thruster systems to be developed to

higher TRL levels on a first stage, SRC Call 2016 (2016-2020), while complying with

certain requirements to address the needs of a number of applications.

The general initial roadmap was characterized for phase 1 by a technology approach and

pursued in this phase 2 by an application oriented approach.

The Call SPACE-28-TEC-2020 for incremental EP is organized as a consequence with

an approach per application with for each, a selection process of the most promising

ones, in order to cope with the global available budget. This approach will allow to

comfort the development of products based on the retained incremental technologies, that

could be flown if needed in an IOV/IOD flight (opportunity which is being proposed by

EC) and that could be easily and rapidly adopted and further qualified by ongoing

commercial and institutional projects in order to arrive on time to market and be

worldwide competitive.

The main application/market linked with EPS power range domains targeted are:

Telecom/MEO (including Navigation)

LEO (including Constellations)

Space Transportation

Exploration/Interplanetary/Science

The technology line for the incremental line is characterized by the electric propulsion

system aspects and its power level range.

The retained application domains for the SRC Call 2020 are identified and classified into

3 power range classes of EPS products:

7

Low power (i.e. for Constellations and LEO applications) from 200 W to 700 W

Medium power dual mode (SK/EOR) i.e. for Telecom and Navigation

applications > 3.0 kW for SK and > 5.0 kW for EOR

High power (i.e. for Exploration and Space Transportation) > 20.0 kW

Each future EPS product (thruster-based system) shall address different gaps for the

adequate retained application. A schematic view of the roadmap is presented in Figure 2:

the layers represent the different applications where each EPS product (thruster-based

system) has to address.

Figure 2: The Roadmap logic for the Incremental EP systems

For the incremental developments the complete EP system needs to be brought to the

higher TRLs required for subsequent market introduction as EPS products.

The achieved TRL’s have to be consistent with the definitions and requirements from:

ECSS-E-AS-11C – Adoption Notice of ISO 16290, Space systems – Definition of the

Technology Readiness Levels (TRLs) and their criteria of assessment (1 October 2014).

And using for their implementation:

ECSS-E-HB-11 Technology readiness level (TRL) guidelines

Each EPS product, for the purpose of the SRC roadmap and SPACE-28-TEC-2020, shall

include the development of the thruster (including its Cathode/Neutralizer if needed)

with the following EPS sub-elements:

Power Processing Unit (PPU)

8

Fluidic Management System (FMS)

As part of the thruster, the cathodes/neutralisers are required for all three incremental

technologies. High current cathodes for thrusters with power performance beyond state-

of-the-art have been investigated. They need to be developed as part of the projects.

Experience has shown that the PPU is a technically challenging and expensive part of

each EP system (up to 50 % of the cost - indicative). Power performance beyond state-

of-the-art, which is one of the tasks to be fulfilled for Telecom applications (and even

more for Space Transportation), may indeed be more challenging on the PPU side than

for the thruster. This importance needs to be properly addressed in the effort and

development of the EPS. Also for Telecommunication applications dual mode EP

systems are sought, which can switch between a high thrust - lower Isp mode for Electric

Orbit Raising (EOR) and a high Isp – lower thrust mode for station keeping. The

challenge for a dual mode PPU is to handle both high power at low voltage and high

voltage. Also this requirement may make the dual mode PPU development more difficult

than the dual mode thruster development. PPU shall improve their competitiveness for all

applications in the development of the adequate power range, as an important part of the

roadmap for all incremental technologies.

The fluidic management system, which provides the EP thrusters with the right amount

of propellant, also needs to be improved. The aim is to simplify the fluidic architecture in

order to reduce cost and complexity and also mass on the platform. Additionally, some

fluidic systems presently produced together with European EP thrusters may contain

parts, which are subject to export restrictions, such as pressure regulators.

Some common aspects to all thruster-based systems are the following:

• Alternative/non-conventional propellants

• High Power testing facilities and EPS diagnostics and simulations

• EPS testing methods – Standardization of EP testing and simulations

First Call (2016). It was proposed through the past call to start the development of a

complete EP system, the thruster including cathodes, the PPU, and the FMS, up to TRL

levels dependant on the targeted applications. These developments results should foresee,

amongst others, a definition of the requirements of the EPS for the chosen application(s),

the impacts of this EPS on the system (platforms) and the achievable type of missions.

The common aspects mentioned above have been addressed together as part of the same

technology. The topics mentioned have been investigated in parallel with the EP system

development, as they are related to: alternative propellants, test facilities and common

standards for testing and simulation. The standardisation of testing methods and

simulation methods with reliable diagnostics tools and reference test cases are very

important to compare results obtained at different facilities, different simulation tools or

with different technologies comparable among each other. All projects have taken these

common topics into account and have proposed solutions.

Second Call (2020). The objective is to complete the development up to the qualification

of the complete EPS proposed products, the thruster including cathodes, the PPU and the

FMS, to achieve the targeted higher TRLs for the relevant applications and in the

retained perimeter, which has to be proposed by the applicant on the basis of its Market

analysis survey.

9

An assessment of the achievements in the first Call projects has been made for the

second Call, and the possible identified changes in the international competition, future

missions, or new market requirements have been taken into consideration for the second

call definition. Depending on the outcome of this analysis, the long-term goals have been

updated and the roadmap has been adjusted accordingly.

The target TRLs at the end of the incremental Call 2016 are supposed to be achieved by

each technology to be used by the EPS products in the relevant applications.

Different applications for electric satellite propulsion have been considered for the

incremental technologies developments with the objective to increase the TRL towards

the development of EPS products that will be the best adapted to the considered

applications.

The LEO Constellation market (Space X, OneWeb, etc.) is opening new opportunities to

EP systems which are capable to offer low cost and high performance solutions to the

propulsion requirements of such missions involving hundreds or thousands of spacecraft,

and therefore its commercial application for electric propulsion is considered to be of

high priority in the short term for the development of future EP systems.

The geostationary Telecommunication satellite market (using EOR and SK manoeuvres)

is still today one of the main commercial application for electric propulsion and remains

important for the development of future EP systems (dual mode for SK/EOR).

MEO, Space Transportation, Exploration and Science are the other applications

considered and their relative importance is ranked to decrease in the given order. The

three incremental EP technologies have focussed on different technical parameters to be

worked on and to be improved, such that EPS products based on each thruster technology

can become competitive on the commercial market within a timeframe compatible with

Horizon 2020.

The expected TRL at EPS level for these developments as well as the main activities in

each application field are detailed as well in further sections of this document.

- For Low Power Electric Propulsion Systems, the target TRL at the end of the

project should be at least 6/7.

- For Medium power dual mode, the target TRL at the end of the project should be

at least 6/7.

- For High power, the target TRL at the end of the project is 5/6

The EPS products shall meet technically the expected performances required by the

needs of applicative field, as well as reducing drastically the EPS products recurring

costs.

European Non-Dependence, competitiveness and the understanding of the interactions

between the EP system and the spacecraft are goals to be achieved as much as possible

across all application fields. Common goal for all three technologies in all application is

a significant reduction of the EPS recurrent costs (30% on the overall system), and

particularly for the PPUs.

10

It should be noted that due to the different type and physical principles of the three

technologies tackled under this incremental line, only the requirement on the power

range classes of EPS products (Low power: from 200 W to 700 W; Medium power dual

mode (SK/EOR): > 3.0 kW for SK and > 5.0 kW for EOR; High power > 20.0 kW) is

the same for the HET, GIE and HEMPT and dependant on the application targeted.

Therefore, all the other performance parameters are technology specific.

2.2.3. Roadmap for disruptive technologies

(Not applicable to the SRC 2020 call - Incremental Technology)

2.3. Conclusion

The advantage of having several mature technologies in the portfolio is a particular

strength of the European EP scene. The three Incremental Technologies have individual

strengths and weaknesses, which make them more competitive for certain applications

and less competitive for others.

The EPIC roadmap developed by the EPIC PSA addresses all three technologies in the

Incremental Technology line. The COMPET-3-2016-a Call allowed the three Electric

Propulsion Systems based on these technologies, to be developed to higher TRL levels

on a first stage (2016-2020), while complying with certain requirements and TRL

objectives to address the needs of a number of applications.

Regarding new markets and applications, as Constellations in the Low power range, and

dual mode features for Electric Orbit Raising (EOR) and Station Keeping (SK) in the

Medium power range, it is not possible to tell at the time being, which products based on

Incremental Technology and developed with a design to cost approach would be the best

suited for the market at the end of the SRC (2023/2024).This approach guarantees a high

flexibility to react to possible changes of the satellite market needs and unforeseen

developments of the launcher market, giving to the European stakeholders a strategic and

flexible position, clearly demanded by Satellite Operators and Large System Integrators.

For the SPACE-28-TEC-2020 Call, the retained application domains are identified for

the call into 3 power range classes: Low power (i.e. for Constellations and LEO

applications) from 200 W to 700 W; Medium power dual mode i.e. for Telecom and

Navigation applications > 3.0 kW for SK and > 5.0 kW for EOR; and High power (i.e.

for Exploration and Space Transportation) > 20.0 kW.

SPACE-28-TEC-2020 Call proposals should address further development and

qualification of the most promising products based on Incremental Technologies which

have a TRL not lower than the expected target from the COMPET-3-2016-a Call, up to

design, industrialization and qualification level of the overall Electric Propulsion System,

in order to guarantee the current leadership through competitiveness of European electric

propulsion.

Proposals based

on sub-line Application activities Expected TRL target

from the COMPET-3-

11

2016-a Call

HET

1. Telecommunications /

Navigation

2. LEO

3. Space Transportation /

Exploration /

Interplanetary

1. (5-6)

2. (5-6)

3. (4-5)

GIE


Navigation

2. LEO


Exploration /

Interplanetary

4. Science

1. (5-6)

2. (4-5)

3. (4-5)

4. (4-5)

HEMPT


Navigation

2. LEO


Exploration /

Interplanetary

4. Science

1. (5-6)

2. (4-5)

3. (4-5)

4. (4-5)

TRL expected target from the COMPET-3-2016-a Call

Proposals shall enable to achieve the incremental advances on the already mature

technologies for Electric Propulsion Systems, with the focus on product development for

the most promising applications and future expected markets in line with the market

studies: Telecom applications, Constellations, Navigation, LEO applications, Exploration

and Space Transportation.

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Technical Annex

A - INCREMENTAL LINE

This section provides additional information in order to clarify what is expected from the

proposals to be submitted in response to SPACE-28-TEC-2020: SRC – In-Space

electrical propulsion and station keeping a) Incremental Technologies.

The projects to be funded under SPACE-28-TEC-2020 Incremental Technologies are

meant to substantially advance the TRL of the EPS products based in either: HET

technology, GIE technology or HEMPT technology; for the retained application domains

identified by the 3 power range classes: Low power (i.e. for Constellations and LEO

applications) from 200 W to 700 W; Medium power dual mode i.e. for Telecom and

Navigation applications > 3.0 kW for SK and > 5.0 kW for EOR; and High power (i.e.

for Exploration and Space Transportation) > 20.0 kW.

The applicants have to define and propose their targeted perimeter range (in terms of

power range) for the optimisation, dimensioning and functional domain of their EPS

products within the most suited 3 power range classes (corresponding to the different

applications) and on the basis of a Market analysis justified in the proposal

It has to be noted that the complete power ranges given above and defining the

application domains are not to be fulfilled on the all range of power by each of the

proposed EPS products if not considered adequate to the Market needs.

It has also to be noted that a design to cost approach is recommended during the

development of the products to fully reach the objectives of the SRC roadmap.

This section is composed of several tables, which provide specifications for the activities

to be pursued within the 3 power range classes (Low power, Medium power dual mode

and High power).

The first table (Table 0) is applicable to and common to all the proposals focused on

Incremental Technologies (HET/GIE/HEMPT).

The remaining tables in this section (Tables 1.1 to 1.3, Table 2.1 and Table 3.1) identify

specific challenges and considerations for each of the 3 power range classes for each

thruster technology (HET/GIE/HEMPT).

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In summary, the proposals are invited to focus on the following activities:

Power Range

Application activities

the proposals

shall address

Incremental Technology

can choose to address Applicable Tables

All Power

Ranges All All (HET, GIE, HEMPT) Table 0

Low Power

(200 W-700 W)

LEO Aplications &

Constellations -

Telecommunications

HET

GIE

HEMPT

Table 1.1

Table 1.2

Table 1.3

Medium Power

(> 3.0 kW for

SK and > 5.0

kW for EOR)

GEO

Telecommunications

MEO Navigation

HET, or GIE, or HEMPT Table 2.1

High Power

(> 20 kW)

Exploration

Space Transportation HET, or GIE, or HEMPT Table 3.1

It is important to note that the thrust orientation mechanism(s), the tanks and the SC

power generation and distribution subsystem are not targeted by these activities.

Therefore the projects are meant to cover the following aspects of the EPS: thruster

(including cathode and neutraliser if needed), PPU and FMS.

The tables identify specific challenges for each power range classes/application. Each of

the three EPS Incremental technologies (HET/GIE/HEMPT) is based on different physics

phenomena and different concept architecture. The requirements set in these tables have

been selected in order to request equivalent efforts beyond the actual state of the art for

each technology.

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Table 0

All power ranges and incremental technologies activities

Description and

needed Action

The Electric Propulsion Systems (EPS) based on (HET/GIE/HEMPT) are

considered mature enough at the moment to allow for incremental steps through

this SRC aiming at enabling capabilities like operating at dual mode,

higher/lower power, Electric Orbit Raising (EOR)/Station Keeping (SK), etc.,

required by a number of applications and markets, which the current systems,

some of them qualified and others with flight heritage, are not able to provide.

The main action needed is to improve the current state of the art performances,

the current TRL, and reduce significantly the cost of the EPS, in order to satisfy

the medium and future needs of different markets.

Proposals should address further development and qualification of EPS products

based on the most promising Incremental Technologies starting from a TRL not

lower than the expected target from the COMPET-3-2016-a Call, up to design,

industrialization and generic qualification level of the overall Electric Propulsion

System, in order to guarantee the leadership through competitiveness of

European electric propulsion.

The projects shall cover the design, development, justification, validation

(including testing) and qualification (including testing performed in a relevant

environment) of the EPS and following the relevant ECSS Standards. Actions

should focus on design, industrialization and qualification in the required SRC

timeframe to foster flight readiness of the overall Electric Propulsion System, by

means of advanced Engineering Models (EM) (like Functional Engineering

Models, Structural mechanical and Thermal model (STM),…), to be followed

by a Qualification Model (QM) to achieve at the best TRL 7 depending on the

power range application. Proposals should seek to cover incremental

developments up to the specified TRL level.

Reference(s) Relevant ECSS Standards (www.ecss.nl) for the different elements of

the EPS i.e. but not limited to :

o for the relevant milestone documentation (ECSS-E-ST-10C),

o ECSS-E-ST-35C-Rev.1 – Propulsion general requirements,

o ECSS-E-ST-35-01C - Liquid and electric propulsion for

spacecraft,

o ECSS-E-ST-10-02C Rev.1 – Verification,

o ECSS-E-ST-10-03C – Testing

o ECSS-E-ST-10-04C – Space environment

o ECSS-E-ST-31C – Thermal control

o ECSS-E-ST-32C Rev.1 – Structural general requirements

o ECSS-Q-ST-30-11C Rev.1 – Derating – EEE components

o ECSS-U-AS-10C – Adoption Notice of ISO 24113: Space

systems – Space debris mitigation requirements

o And using for their implementation:

o ECSS-E-HB-11 Technology readiness level (TRL) guidelines

Proposers are invited to consult other EPIC public documentation

http://www.ecss.nl/

15

available under www.epic-src.eu (EPIC website)

Proposals

indicative

content

Proposals shall present an adequate approach addressing the relevant

applications and Power Range (targeted perimeter range for the

optimisation, dimensioning and functional domain of their EPS

products) to be covered in a balanced way including all aspects and

equipment of the EPS (thruster cathode/neutraliser-, PPU and FMS).

Proposals should provide for each EPS product the attainable

objectives in terms of performance (thrust, Isp, power), of costs

(recurring costs) and achieved TRL.

Proposals on Incremental Technologies should demonstrate the

readiness and interest to carry the developments further on for a

possible future in-orbit demonstration (IOD/IOV) and a business plan

on how to access the current or future expected markets.

Proposed developments shall include modelling/simulation and

testing of each equipment in the subsystem as well as for the complete

EPS product.

Proposals shall include an initial work package dedicated to the

requirements derivation based on the targeted application, as well as

an analysis of the different classes of missions and EP system impacts

on the satellite and the potential missions. The derivation of EPS

specific requirements from the targeted application needs shall be

included, taking into account the considerations described in the

tables for each power level/application and technology. System

impacts, thermal dissipation, plasma effects, electromagnetic

interaction or any other effects shall be taken into account including

considerations on integration of the EP system into the SC.

Proposals shall go beyond the present state of the art and, preferably,

the expected state of the art at the time of completion if alternative

technologies are being developed outside Europe, taking into account

the recurring costs optimisation and time to market opportunities.

Proposals should include detailed plans for design, industrialization

and qualification of the overall Electric Propulsion System by means

of advanced Engineering Models (EM) (like Functional Engineering

Models, Structural mechanical and Thermal model (STM),…) to be

followed by a Qualification Model (QM).

Proposals should identify and justify the relevant environment to be

considered during the development and qualification of the EPS

products, and that will be used for performance evaluation and for

tests based on the possible platform’s architecture considered

adequate to cope with the foreseen market targets.

To achieve TRL 5/6, proposal should include the foreseen necessary

tests of the critical functions in the relevant environment, using as

much as possible representative full scale model(s) in form, fit and

function.

http://www.epic-src.eu/

16

To achieve TRL 6/7, proposal should include the following tests in

the relevant environment at thruster level (EM and QM):

o Functional tests (electrical, fluidic, performance

characterization)

o Environment tests at cathode level (thermal vacuum test

including thermal cycling, sine and random vibration tests,

shock tests)

o Environmental tests at thruster level (thermal vacuum test

including thermal cycling, sine and random vibration tests,

shock tests)Part of lifetime tests (at least 1000 h; preferably

1500h if compatible with the available budget)

Note 1: Environmental tests at cathode and thruster level may also be

performed in a combined test e.g. at module level.

To achieve TRL 6/7 proposal should include the following tests in the

relevant environment at EPS level (EM and QM):Thruster Plume

characterization tests

o Thruster /PPU Coupled tests

o Electro Magnetic Compatibility (EMC) tests

Note 2: Those tests are conducted on a QM (or, depending on the

models philosophy, on EQM or PFM, see ECSS-E-HB-10-02 clause

5.2.5.2)

Note 3: TRL 7 is achieved if complete lifetime tests are performed

consistent with the mission objectives, operational environment and

the operational performance requirements established and agreed

upon by the stakeholders.

In order to reduce the cost of the full EPS system for increasing

competitiveness in the markets, proposals shall clarify the expected

cost (indicative) reduction for the whole EPS and the specific

subsystems together with a clear methodology.

Proposals shall seek synergies while avoiding duplications with

already existing or planned developments by other entities in Europe,

such as ESA, EU-FP, EU-H2020, National Space Programmes, and

commercial initiatives.

Proposals shall clearly declare any background IPR and non-European

component issue from the proposers used to perform the activities

described.

Expected

milestones

PDR (when relevant depending on the TRL objective) is considered achieved

before the end of Call 2016

At least the following reviews shall be achieved:

For TRL 6/7: Manufacturing Readiness Review (MRR), CDR, TRR and TRB

(for endurance tests), QR (which could be limited to cover partial life time test

duration if needed)

17

For TRL 5/6: PDR, CDR (if achievable)

Expected

Deliverables

At least the following Deliverables shall be produced:

System Studies Report,

Update of Business Plan including Market Analysis,

MRR, CDR, QR data packages including Technical Specification, System

Design, Detail Design Report including justifications (Design justification

file, thermal and mechanical analysis, FMECA, ICD (Interface Control

Document)), Design and Development Plan, Manufacturing Report, Test and

Verification Plans, Test and Verification Reports, Qualification Plan

including ROM Cost Assessment (recurrent and development), according to

the relevant ECSS Standards (ECSS-E-ST-10C)

Risk Assessment and Contingency Analysis report (yearly),

KPIs report (yearly),

Non-European components issues and contingency measures

Dissemination and educational public material: Activity and results

presentations, papers, conference papers, photos, posters, videos, professional

communication and educational movies; and

Project website.

18

A1 - Low Power (200 W-700 W) for LEO Applications & Constellations -

Telecommunications

Table 1.1

Low Power (200 W-700 W) for Hall Effect Thrusters (HET)

EPS activities oriented to LEO applications

Description and

needed Action

EP is one of the new revolutionary technologies at the moment in satellite

markets. There are many developments in LEO systems and applications, and EP

could play a significant role in this market.

Hall Effect Thrusters (HET) EPS have good prospects for use in LEO, due to

their power-to-thrust ratio allowing higher thrusts for the power-limited satellites

in LEO.

Recurring cost is one of the major drivers to take into account for the design and

development of the EPS to be attractive and on time to market opportunities.

Projects in this area shall aim at improving EPS performances and reducing the

recurrent indicative cost of the EPS.

All HET proposals shall cover this activity and the requirements specified

hereafter.

Requirements

Target TRL

at the end of

the SPACE-

28-TEC-

2020 project

6-7

Cycles TBD by

proposers

Due to the eclipses, a large number of cycles is needed for

operation in LEO. Thus, the design shall take into account

the impact that it has on performances and lifetime of the

EPS. This number of cycles shall be compliant with the

lifetime requirement of the platforms (currently around 5

years)

P/T < 20 W/mN Low P/T ratio is needed in order to obtain useful thrust when

little power is available.

Isp > 1500 s The EPS efficiency is important for the often mass-limited

LEO missions. The higher the Isp the better, but this

requirement is a trade-off of several performances.

Innovative

and cheaper

PPU

Low cost and compact PPU

EPS Cost < 200 k€ (indicative)

Remarks Compact, integrated and low mass system shall be considered.

19

Table 1.2

Low Power (200 W-700 W) for Gridded Ion Engine (GIE)


Description and

needed Action


markets. There are many developments in LEO systems and applications,

and EP could play a significant role in this market.

Gridded Ion Engines have good prospects for use in LEO, due to the mass

savings they can offer due to their high Isp. They have already demonstrated

good performances in some LEO applications, such as drag compensation.

Projects in this area shall aim at improving EPS performances and reducing

the recurrent cost of the EPS.

All GIE proposals shall cover this activity and the requirements specified

hereafter.

Requirements

Target TRL at

the end of the

SPACE-28-

TEC-2020

project

6-7

Cycles TBD by

proposers

Due to the eclipses, a large number of cycles are needed for





years).

P/T

~ 25 (W/mN) Low P/T ratios are needed in order to obtain useful Thrust

when little power is available.

Isp > 3500 (s) The EPS efficiency may be less important for the often

mass-limited LEO missions than a high Isp. The higher the

Isp the better, but this requirement is a trade-off of several

performance parameters.

Innovative and

cheaper PPU

Low complexity PPU


Remarks Compact and low mass integrated system

20

Table 1.3

Low Power (200 W-700 W) for Highly Efficient Multistage Plasma Thruster

(HEMPT)


Description and

needed Action


markets. There are many developments in LEO systems and applications,

and EP could play a significant role in this market.

HEMPT represents a promising technology for this market. Due to the

simplicity of the technology, it is expected that the new HEMPT-based

systems will combine cost effectiveness and reliability. This may result in an

advantage regarding the development of a low power system targeting the

LEO constellations market.

Projects in this area shall aim at improving EPS performances and reducing

the recurrent cost of the EPS.

All HEMPT proposals shall cover this activity and the requirements

specified hereafter.

Requirements

Target TRL at

the end of the

SPACE-28-

TEC-2020

project

6-7

Cycles TBD by the

proposers

Due to the eclipses, a large number of cycles are needed for





years)

P/T < 22 W/mN Low P/T ratios are needed in order to obtain useful thrust

when little power is available. The P/T ratio should be

decreased from the current state of the art.

Isp > 1600 s The EPS efficiency may be less important for the often

mass-limited LEO missions than high Isp. The higher the Isp

the better, but this requirement is a trade-off of several

performances.

Innovative and

cheaper PPU

Low cost and compact PPU


Remarks Compact and low mass integrated system

21

A2 - Medium Power (> 3.0 kW for SK and > 5.0 kW for EOR) for all

Incremental Technologies (HET/GIE/HEMPT) Project activities

Table 2.1

Medium Power (> 3.0 kW for SK and > 5.0 kW for EOR)

EPS activities oriented to GEO Telecommunications & MEO Navigation

applications

Description and

needed Action


markets. In the case of Telecommunications is still today one of the main

commercial applications for electric propulsion and remain important for the

development of future EP systems (dual mode for SK/EOR), with chemical

propulsion as main competitor, and a fierce international competition.

Hall Effect Thrusters (HET) EPS are the preferred option for this market at the

moment due to their flight heritage and the significant efficiency for Electric

Orbit Raising (EOR) time reduction.

Gridded Ion Engines (GIE), with their higher Isp, seem to be the thruster of

choice when propellant mass saving is the most important driver. GIE systems

are one of the best options for this market for Station keeping (SK) at the moment

due to their high Isp, which allows significant mass savings and lower launch

costs. New developments optimising the thrust-to-power ratio make these

systems attractive also for EOR.

Highly Efficient Multistage Plasma Thruster (HEMPT) EPS represent a

promising option for this market.

Activities in this area shall aim at improving or consolidating these EP

technologies position in the mid-term and as being one step ahead for the future

needs of the Telecom market, by substantially improving EPS performances for

the mode for which they are less efficient (SK for HET and EOR for GIE) and

reducing cost of the EPS.

All proposals shall cover this activity and the requirements specified hereafter.

Requirements

Target TRL

at the end of

the SPACE-

28-TEC-

2020 project

6-7

22

Dual mode TBD by

proposers

The EPS should be optimized to work in two different points

for two different types of functions: EOR mode with high

thrust to minimise the time to final orbit; and SK mode with

high efficiency to minimize the propellant used during the

in-orbit operations.

In the case of HET, it is expected that the effort for dual

mode will mainly aim to improve the Isp level for SK at an

adequate P/T ratio.

In the case of GIE, it is expected that the effort for dual

mode will mainly aim to improve the thrust level for EOR.

In the case of HEMPT, it is expected that the effort for dual

mode will mainly aim both to improve the Isp and the thrust

for both operating points (SK/EOR).

EPS Power > 5 kW for EOR

mode

> 3 kW for SK

mode

The EPS should demonstrate power performances beyond

the state of the art, justifying the specific power performance

selected with an analysis of the medium to long term market

needs.

P/T For HET

~ 14 W/mN for

EOR mode

~ 19 W/mN for

SK mode

For GIE

~ 21.5 W/mN for

EOR mode

~ 30 W/mN for

SK mode

For HEMPT

~ 18 W/mN for

EOR mode

~ 30 W/mN for

SK mode

The time to orbit is a critical requirement from satellite

operators and is fully dependent on the P/T ratio.

The P/T ratio should be reduced from the current state of the

art, in order to make the EPS more competitive for EOR

utilisations.

23

Isp For HET

1600-1900 s for

EOR mode

> 2000 s for SK

mode

For GIE

> 2500 s for EOR

mode

> 3000 s for SK

mode

For HEMPT

> 1500 s for EOR

mode

2500-3000 s for

SK mode]

The EPS efficiency in orbit operations is a critical

requirement from satellite operators to optimize the mass of

the propellant. The higher the Isp the better, but this

requirement is a trade-off of several performance

parameters.

The Isp should be increased from the current state of the art,

in order to make the EPS more competitive for SK

utilisations.

Innovative

and cheaper

PPU

The EPS should propose innovative and cheaper PPUs (addressing complexity

vs. indicative cost), covering: industrialisation (reduction of number of EEE

components, simplification of HV design, etc.), high power (high voltage (HV)

modules in parallel, thermal coupling, etc.), in-orbit reconfiguration and

modularity, etc. An asset would be a complementary study of alternative

simplified PPU concepts for general orbit transfer application using direct input

from spacecraft solar power systems.

Recurring

Cost

reduction

30% of the present EPS cost (indicative)

24

A3 - High Power (> 20 kW) for all Incremental Technologies EPS activities

oriented to (HET/GIE/HEMPT)

Table 3.1

- High Power (> 20 kW)

EPS activities oriented to Exploration/ Space Transportation applications

Description and

needed Action


markets. The specific characteristics enable new types of missions and

applications, in particular in Transportation, Exploration and Interplanetary

Missions.

Hall Effect Thrusters (HET) EPS are a good option for this market at the

moment due to their high thrust capabilities, though the Isp is not the best for

interplanetary missions.

Gridded Ion Engines have already been used for Interplanetary missions, due

to their good Isp and lifetime characteristics. In order to increase their

competitiveness within interplanetary missions, and as well to extend its use

for Space Transportation and Exploration missions, the performances of

existing systems must be improved.

In order to improve the competitiveness of HEMPT systems within

Interplanetary, Space Transportation and Exploration missions, the

performances of existing systems have to be improved.

Activities in this area shall aim at consolidating these positions in the mid-

term and at being one step ahead for the future needs of this market, by

substantially improving EPS performances and reducing cost.

All proposals shall cover this activity and the requirements specified

hereafter.

To cover this application, clusters of thrusters could be envisaged.

Requirements

Target TRL at

the end of the

SPACE-28-

TEC-2020

project

5 - 6

Lifetime (Total

Impulse)

TBD by

proposers

The required large total impulse implies a very long period

of thrust operation. Thus, the lifetime of the system must be

analysed and improved where necessary, in order to ensure

that the system can meet the mission needs.

EPS Power > 20 kW High Power thruster are required, since high thrust levels

will be required for these types of missions, and the systems

are expected to be able to provide higher power to the EPS.

P/T For HET

< 20 W/mN

For GIE

< 35 W/mN

High thrust levels will be required in order to enable the

missions with reasonable durations.

25

For HEMPT

< 26 W/mN

Isp For HET

>2500 s

For GIE

>3500 s

For HEMPT

>3000s

The EPS efficiency is a critical requirement to allow the use

of an EP technology in these types of missions, as they

usually require large delta-V, and there are severe mass

constraints.

PPU High power PPU able to provide 20 kW to the thruster

Remarks Clustering of lower power EPS and its PPU could be considered.

If clustering is foreseen, this activity should focus on the EPS system aspects

and not on the development of thrusters and components.

26

ACRONYMS & ABBREVIATIONS

CDR Critical Design Review

EC European Commission

ECR Electron Cyclotron Resonance

EEE Electrical, Electronic and Electromechanical

EOR Electric Orbit Raising

ECSS European Cooperation for Space Standardization

EP Electric Propulsion

EPIC Electric Propulsion Innovation and Competitiveness

EPS Electric Propulsion System

ESA European Space Agency

EU European Union

FMS Fluid Management Systems

FP Framework Programme

GIE Gridded Ion Engine

H2020 Horizon 2020

HEMPT Highly-Efficient Multistage Plasma Thruster

HET Hall-Effect Thruster

HPT Helicon Plasma Thruster

HV High voltage

IPR Intellectual Property Right

Isp Specific Impulse

KPI Key Performance Indicator

LEO Low Earth Orbit

MEO Medium Earth Orbit

MPD Magneto Plasma Dynamic

PDR Preliminary Design Review

PPT Pulsed Plasma Thruster

PPU Power Processing Unit

PSA Programme Support Activity

QR Qualification Review

REA Research European Agency

ROM Rough Order of Magnitude

RTD Research, Technology and Development

SC Spacecraft

SK Station Keeping

SRC Strategic Research Cluster

SRR System Requirement Review

TBD To Be Defined

TRL Technology Readiness Level

WP Work Package

space-28-tec-2020 strategic research cluster in-space...

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