ESA Presentation | Iain McKenzie | Trieste | 20/02/2015 | TEC-MME ESA ESTEC | Slide 1 ESA U

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Qualifying Photonics for the Space Environment

Iain McKenzie Trieste 20/02/2015

ESA Presentation | Iain McKenzie | Trieste | 20/02/2015 | TEC-MME ESA ESTEC | Slide 2 ESA U

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Qualifying Microphotonic Devices for Space

Vacuum • Outgassing • Contamination • Packaging

Mechanical • vibration • Pyro-shock

Space radiation • Displacement damage • TID • Charging due to interaction

with charged particles

Thermal • Large temperature

variations

15 years service life • No maintenance • Guarantee of end of life performance

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NASA vs. Telcordia Test Requirements

Due to the usage of MIL-STD-883 in Telcordia specifications, the random

vibration environmental parameters and duration are of greater intensity

than is required for space flight launch vehicles.

Reliability of Optical Fiber Modulators for Space Flight Environments, M. Ott, et al, NASA Parts and Packaging Program Report,

Electronic Parts Project, IPPAQ Task Report, October 2002.

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Radiation Effects on Fibre Optic Sensor Hardware

Induced attenuation in optical fibres

Refractive index change in glass (FBG shift)

Impact on fibre optic coating (FBG shift)

Displacement damage semiconductor laser (increased laser threshold,

decreased slope efficiency)

Displacement damage in detector (increased dark current, reduced

efficiency)

SEE – laser driver sensitivity

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Other Parameters that Effect Darkening

Stress in the fibre

Photo bleaching

Photobleaching test for two Standard Telecom fiber samples (97 m)

on the same spool with low and high optical power coupled in the fibers

0

1

2

3

4

5

6

7

0 200 400 600 800 1000 1200

Accumulated dose [Gy]

Rad

iati

on

in

du

ced

att

en

uati

on

[d

B]

Low Power (1 uW)

High Power (~10 mW)

Average dose rate = 449 Gy/h

Total dose = 1000 Gy

Wavelength = 980 nm

Fibres outside

irradiation setup

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Radiation Darkening of Optical Fibers

Radiation-induced attenuation in some COTS fiber samples (100 metres)

Average dose rate = 157 Gy/h, Total dose = 1000 Gy

0

1

2

3

4

5

6

7

8

9

10

11

12

0 200 400 600 800 1000 1200

Accumulated dose [Gy]

Ra

dia

tio

n-i

nd

uc

ed

att

en

ua

tio

n [

dB

]

Draka MaxCap 300 Radhard optimized

Draka MaxCap 300 Standard

Draka MaxCap 300 Radhard

INO 712A1

Telecom Standard

Telecom Radhard

fiber is not

irradiated in this

area,

time of recovery

= 60 minutes

Radiation-induced attenuation at 850 nm

performed at an average temperature of -17 °C

0

5

10

15

20

25

30

35

40

45

50

0 200 400 600 800 1000 1200

Accumulated dose [Gy]

Ra

dia

tio

n-i

nd

uc

ed

att

en

ua

tio

n [

dB

]

Draka MaxCap 300 Radhard Optimized

Telecom Standard

Draka MaxCap 300 Radhard Optimized(21 C)

Average dose rate = 429 Gy/h

Wavelength = 850 nm

Average dose rate = 429 Gy/h

Wavelength = 850 nm

Radiation-induced attenuation fits and extrapolations at 850 nm

of the Draka MaxCap 300 Radhard Optimized fiber

exposed to gamma radiations

0

1

2

3

4

5

6

7

8

9

0 100 200 300 400 500 600 700 800 900 1000

Accumulated dose [Gy]

Rad

iati

on

-in

du

ced

att

en

uati

on

[d

B]

452 Gy/h

157 Gy/h

452 Gy/h Fit

157 Gy/h Fit

20.4 Gy/h extrapolation

0.06 Gy/h extrapolation

Courtesy of INO And SpaceFibre Project

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FBG Wavelength Shift Due to Radiation

Applications include laser wavelength stabilisation, filtering, and sensing

FBGs show a shift in peak wavelength with radiation due partly to change in n

Changes for 1Mrad are on the order of some 10s pm

Radiation hardness improves with good selection of fibre, FBG writing approach, annealing process (thermal and UV), even coating type.

Femto second laser writing approaches so better radiation hardness

CH 10

-0.005

0.000

0.005

0.010

0.015

0.020

0.025

0.030

0.035

0.040

0.045

0 50 100 150 200

Time, h

Pea

k S

hif

t, n

m .

T10-1 T10-2 T10-3

Results courtesy of SCK-CEN ESA contract.

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Radiation Testing of SOI Devices

• Co-60 TID testing of SOI ring resonator devices

• Total dose 300kRad • 0.39 pm/kRad shift of

resonance peaks • Important to note that

~100pm/K is expected due to thermally induced refractive index changes.

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Vacuum

Material Selection – Outgassing

Contamination (hermetic sealing)

Packaging and Mounting

Hermetic Sealing required for active optoelectronic components (lasers

and detectors) – problems with moisture in package.

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SMOS Qualification Program

SMOS Mission (Soil Moisture and Ocean

Salinity) Payload Module:

Microwave Imaging Radiometer with

Aperture Synthesis (MIRAS)

COTS components used:

Modulight AlGaInAs 1300nm FP laser diodes,

Hamamatsu InGaAs PIN photodiodes,

Gooch and Housego Fiber Splitters

Gore FO Cable

Diamond AVIM connectors

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Qualification Approach

Highest quality level for commercial off-the-shelf opto-

electronic components is according to Telcordia standard or

similar.

Subsea is a good starting point – very high reliability

requirements – 20 year life expectancy

Space qualified components usually not existing

A full qualification exercise as per ESCC specification not

feasible due to

- time and cost constraints

- industry is too fast moving

What to do?

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Qualification Approach

Partial evaluation of 2 alternatives

Full qualification of 1 FL plus samples

• + costs are moderate (only one qualification)

• + risk of qualification failure low

• – impact on overall schedule is high as procurement has to be

performed for the samples and after successful evaluation for

the FL again

In order to reduce risk:

Evaluation phase with two possible COTS candidates for each

component (subjected to most critical tests, constructional

analysis, manufacturer assessment)

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Evaluation Process

Procurement from two different suppliers

Detailed constructional analysis

Critical selection and performance tests – Standard evaluation tests

should be designed to stress components and reveal failure

mechanisms. Depending on schedule and budget this may not be

possible.

Visit and make assessment of supplier’s manufacturing procedures

Based on final assessment procure flight lot

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Flight Lot Acceptance Testing (LAT)

Selection testing (Evaluation phase):

1. - vibration, shock

2. - thermal vacuum cycling

3. - radiation (gamma & proton)

4. - constructional analysis & manufacturer assessment

Flight lot screening / qualification

1. - extended burn-in

2. - acceptance thermal cycling

3. - measurement at high and low temperature

Flight lot acceptance testing

1. - thermal cycling, vibration, shock and radiation

2. - life test

3. - bending, fibre pull, mating, DPA

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Lessons Learnt from SMOS Qual.

Most manufacturers are not willing to customise their process

for a small volume order.

Be fast, products change fast – telecom market.

Smaller manufacturers show greater interest and higher

flexibility to customise their manufacturing and/or disclose the

exact processing

Be very accurate in manufacturer assessment (which activities

are outsourced, how is the visibility)

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Evaluation and Qualification of AVIM FO Connector

Project Scope:

Evaluate and qualify connector set AVIM

Document and write specifications for connector sets and assemblies

Qualify a patchcord patchcord=fiber+cable+connectors-set+assembly-

process

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Evaluation Test Plan (ETP)

Purpose of an ETP is to test resistance limits to understand safety

factors and define Qualification values

Scope: Break things and doing FA look why and when Find the

extreme temperature and define Tmin and Tmax for the long term

tests and cycles.

Evaluate limit in vibration and shock

Evaluate survivability to special condition (dust, salt mist,..)

Configuration Tested:

PM fiber Fujikura SM.15-P-8/125-UV/UV-400 1550nm, acrylate

coating

Loose tube OD=1mm PEEK Victrex 450G

Pigtails configuration (two connectors assembled when tested)

.

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Evaluation Test Plan

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Temperature Step Stress

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Random Vibration Step Stress

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Shock Step Stress

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Mating – Demating Test

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Qualification Values

Temperature cycles 100 cycles

• AVIM -55°C to +125°C

• Mini-AVIM -55°C to +85°C

Vibration 35gRMS, 20..2000Hz

Shock 500g

Endurance 1000h at Tmax

Mating durability 100 mating-

demating

Torsion 3N

Static side load 0.2 N

Cable retention 5N

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Qualification Test Plan

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Rocked Defect Investigation

Strange failure mode on ISS fibers observed in 1999

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Night lights from space

Thank you for your attention.