development and test of hpt-05 v2.0 print...

EPIC Workshop, Madrid. 25/10/2017.

Development and test of HPT-05

©SENER Ingeniería y Sistemas, S.A. –2017

Development and tests of HPT-05 25/10/2017

Table of contents

Background

SENER-UC3M collaboration

The Helicon Plasma Thruster

The HPT-05 experimental platform development

Performance models

The HPT system overview

The HPT-05 tests

Test facility and diagnostics

Brief summary of tests results

Conclusions and next steps for HPT evolution



Background: SENERSENER Ingeniería y Sistemas is a multidisciplinary engineeringcompany with more than 60 years of experience.

More than 50 years delivering equipment into Space:

More than 290 deliveries 0 failures recorded.

In-house AIT capabilities for Space products.

Production line for Defense and Aerospace mechatrons >100units/month.

Main EP related technology background (chronologically): In-orbit servicing OLEV spacecraft AOCS and propulsion modules

responsible, low thrust OTT and SK strategies.

LEOSWEEP FP7 Project Coordinators and System Designers, Ion Beam Shepherd (IBS) concept for debris removal.

“HPT for Space Missions” ESA-GSP working together with UC3Mfor the preliminary evaluation of the HPT.

Internal developments for the design and AIT of a first in-houseHPT prototype, in collaboration with UC3M.



Background: UC3M EP2

Research team is part of the AerospaceEngineering Dep. at Universidad Carlos III Madrid(UC3M)

1 Professor, 3 Assistant Professors, 7 doctoralstudents, 4 post-docs.

Extensive know-how in modelling and simulationof plasma thrusters and plasma physics

In-house EP testing laboratory since 2016. 25 year R&D experience 35 R&D projects: National R&D Plans, FP7, ESA,

US-AFOSR >150 papers, 1 patent 5 recent PhD theses and ~10 student prizes Extense background in teaching EP physics More on website: ep2.uc3m.es



Jan. 2015 Oct. 2015

Background: SENER-UC3M collaboration

May 2016 Dec. 2016 Mar. 2017

2008-2012:aaa

2013-2015:

2015-2017:

2016:

2017-2018:

2018-2019:

UC3M-EP2 started its work on Helicon Plasma Sources under the EC-FP7HPHcom Project.

SENER-UC3M joint effort in the “HPT for Space missions” ESA-GSP project.

Joint venture for the development of the HPT-05 experimental platform.

UC3M-EP2 EP Test Laboratory available.

New agreement for the development of a HPT system breadboard.

GSTP project awarded to increase the technology TRL.



A RF signal is generated, amplified and fed into the antenna RFGPU

The emitted RF wave propagates into the plasma where it is absorbed.

Within the chamber, the neutral gas is ionised and heated.

Along the MN, the plasma expands supersonically, increasing thrust capabilities.

The magnetic field is used for plasma confinement, guidance and RF-wave propagation.

Introduction to Helicon technology and its physical processes

Simple, compact, robust, long life time expected.

Flexible and throttlable.

Uses virtually any propellant.

Scalable to high powers (20kW +).

Still, existing prototypes show low efficiency.

Several aspects of HPT physics not fully understood yet.

Why the Helicon Plasma Thruster?

How does a Helicon Plasma Source work?



Models predict an efficiency ≃35%.

For such values, the utilisation factor 60%.

=80% and =75% are used based on DIMAGNO.

The thrust efficiency would be in the range =10%−30%.

The HPT-05 performance models

Preliminary estimation of performance

Based on UC3M-EP2 models:

Plasma-wave interaction code (HELWAVE)

Internal fluid dynamics, ionisation and losses (HELFLU)

External expansion in the magnetic nozzle (DIMAGNO)

Assumptions:

75% RF efficiency at the RFGPU

100% absorption efficiency

=5-7eV.

Main results

Teis the main driver forHPT performances.

Physical design for proof of concept



Rated at <1 kW @ 13.56 MHz

1.5mg/s Ar

B < 800 G, three coils arrangement, flexible in topology.

The HPT-05 system experimental platform

RF antenna

S1S2S3

electromagnets

Plasma plume



The UC3M-EP2 Electric Propulsion Laboratory

Installed by Leybold on December 2015, operativeon March 2016 (funded by Spanish Government)

1.5m inner diameter, 3.5m long.

Pumping speed >37000 l/s Xe

Ultimate pressure (dry) 1e-7 mbar

Operational pressure (20sccmXe) 2e-5 mbar

EP2 Laboratory Vacuum Chamber

Plasma diagnostics and thruster performances evaluation Characterisation of the plasma plume properties: , , , , , ion current, etc.

Intrusive probes: LP, RFCLP, FP, RPA.

Non-intrusive optical diagnostics.

Thruster performances

Thrust and thrust efficiency (requires a thrust balance, on-going project).

Plume divergence, IE on the beam wings.



Some results: Parametric analysis: , ,

Plasma density increases with and P.

threshold that separates low from highpropellant utilisation regimes. (Pointed out inAhedo & Navarro, PoP 20, 2013).

Propellant utilisation increases with P.



Some results: beam divergence and different antennae

No power coupling on the MN.

Independent of the amount of power.

MN helps to collimate the plasma beam.

Double peak, inductive mode, for thedouble loop antenna. The profiledepends on the antenna shape.

Single peak for the helical antenna,and higher current on the beam wings.

50 (for 95 % of )

There is a minimum B field on the MNto collimate better the beam. Beyondthat there is no gain.

MN OFFMN ON



Propulsive performances

Propellant utilisation: 20% Ar (900W), 50% Xe(extrapolated)

Thrust: 6.6mN (at 500 W)

Thrust efficiency,

: 2.9% (500W)

Propulsive performances are

still low

Construction of an evolved HPT-05 platform HPT-05M, performances improvement,focus on Te increase.

Tests of HPT-05M in two different facilities performances assessment.

Analysis and design activities aimed to improve performances gain knowledge,viability and competitiveness.

Development of a breadboard model (HPT-x) for the complete system increase TRL.

Conclusions and next steps for HPT evolution

Next steps for HPT evolution



Thanks for your attention

[email protected]

Mercedes Ruiz

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