Fundamentals of space scientific instruments - stuba.sk · Fundamentals of space scientific...

Fundamentals of space scientific instruments 1 Space for Education, Education for Space

Space for Education, Education for Space ESA Contract No. 4000117400/16NL/NDe

Specialized lectures

Fundamentals of space scientific instruments

Jan Balaz

Institute of Experimental Physics

Slovak Academy of Sciences


History of space scientific instruments at IEP-SAS

(http://space.saske.sk)


Department of Space Physics - Mission

Physical processes in the space

Solar energetic particles

Galactic cosmic rays

Earth’s magnetosphere

Solar surface

Space weather

Heliosphere

Interplanetary environment

Planets


Magnetosphere

Region where Earth’s magnetic field dominates over interplanetary (solar) magnetic field. The magnetosphere shape and dynamics is formed by interaction of solar wind and Earth’s magnetic field.


Magnetosphere


Trapped particles


Trapped particles

F = q(v x B)


Space scientific instruments from IEP-SAS


MEP – functional block diagram (Monitor of Energetic Particles)


NUADU – functional block diagram (NeUtral Atom Detection Unit)


SK-1 INTERKOZMOS - 17 (1977) (24.9.)

SPE-1 ACTIVE (1989)

SONG CORONAS-I (1994) CORONAS-F (2001)

AUOS-Z

Instruments and spacecraft


PROGNOZ

DOK-T PROGNOZ-10

(1981)

DOK-1 INTERSHOCK (1985)

DOK-2 INTERBALL-T (1995) INTERBALL-A (1996)



MAGION

DOK-S (with FEI-TUKE)

MAGION-2, ACTIVE (1989)

MAGION-3, APEX (1991)

MAGION-4, INTERBALL-T (1995)

MAGION-5, INTERBALL-A (1996)



Orbital station MIR ( † 23. 03. 2001)

SPE-1M (1996)

DOSIMETRY Mission ŠTEFÁNIK

(1999)

Ivan BELLA © NASA – STS 12.06.1998



SLED-2 (1996)

MARS-96 (1996)



MARS-96



MARS-96 launch on 16. 11. 1996



Rosetta (2004-2016)

ESS



Double Star (2004)

NUADU



NUADU operations


HotPay-2 (2008)

PEEL



Spectrum-RADIOASTRON (2011)

MEP-2



BepiColombo (MPO)

(2018 ?)

SERENA / PICAM



Extreme high reliability (no service available in space or briefly before launch)

No failure propagation to other equipment

Mechanical ruggedness (vibrations, impacts, accelerations, accoustic pressure on launch)

Temperature regime in space

Ultra-high-vacuum regime in space

Tolerance to space radiation

Electromagnetic compatibility

Basic requirements for space instruments


Reliability Application of space qualified components (technology, selection,

screening, burn-in, testing by manufacturer or specialized lab) selection from „Qualified Part List“ (ESA-QPL, NASA-QPL) – with good references for space. ESA-ECSS (European Cooperation for Space Standards)

Qualified technology procedures, qualified/certified personnel, top-level quality-management, clean room operations, detailed technical and technological documentation, operations logs, photo documentation, traceability for all components and operations.

Qualification tests to exclude (minimize) unreliability: thermal simulations, cycling, thermal-vacuum cycling, mech. simulations, stress analysis, vibrations, accelerations, impacts, optim. burn-in.

Redundancy (from backup of particular subsystems to complete full redundancy).


ESS processor for ESA-Rosetta (Dual redundant)


ESS processor for ESA-ROSETTA (Clean Room operations)

*2.3.2004 … † 27.7.2016


Mechanical ruggedness Vibrations / accelerations are dangerous for instrument integrity particularly during space launch and spacecraft initial operations. “A golden standard” requires compact design, sufficient number and distribution of supporting points, reinforcing structures (ribs) CAD simulations (FEA) shows endangered areas and dangerous resonances. Low resonance frequencies are dangerous. For electronic boards, component fixation with qualified structural glues and resins is necessary (e.g. ScotchWeld 2116) also for thermal issues.

Materials for mechanical structures (tradeoff for strength, mass, easy processing, outgassing, commercial availability, etc.)

AlMg - alloys 6061 – aluminium alloy AlBe (Albemet) – highest ratio strenght/specific mass (expensive, toxic) Titanium Stainless Stel (high specif. mass, doubtful magnetic cleanliess) Carbonfibre-composites, fiberglass composites Advanced plastics (PEEK, VESPEL, KAPTON, DELRIN) Ceramics (Al2O3, MACOR)


Mechanical design and Stress Analysis (BepiColombo/PICAM)


Qualification mechanical tests

Computer simulations (Stress analysis, FEA)

Search for resonances (10 Hz – 3000 Hz, 1g)

Sinusoidal load (10 Hz – 3000 Hz, 20g)

Random spectrum (10 Hz – 3000 Hz, 20g rms)

Impact (shock) test (up to 1000g)

Linear acceleration (20-30g, Centrifuge)

(1g = 9,81 ms-2, normal gravitation acceleration)


NUADU Vibration test (NSSC Beijing)


Vibration test of Rosetta lander Philae


IEP-SAS vibration test equipment (Brüel & Kjær / LDS)

Vibration test of skCube in launch container

Shaker V780 (5100 N) Power amplifier HPAK 5kW (D-class) Control system Laser-USB Control software LAS-200 Acceleration sensors IEPE 100mV/g


NUADU - impact test 600g


Vibration tests HotPay-2 (PEEL)


IR (~10um)

31.01.2008 / 19:14:00 UTC


Experience is something you don't get until just after you need it.

Steven Wright


Temperature in space Thermal exchange in space devices:

Thermal conduction – heat transfer within solid materials - direct thermal contact between the device components and the spacecraft instrument platform. The thermal drain from the high-dissipation components must be efficiently provided with thermal bridges (Cu, Al, heatpipes)

Thermal radiation (vacuum!) heat transfer via elmg. waves – black surfaces for improved radiation coupling inside the device and inside the spacecraft, special surface materials outside

Thermal convection – heat transfer via flowing medium (heatpipe, gas/fluid in hermetic compartment, etc…)

Thermal ablation - heat transfer (removal) by burning of the material away (heat shields, rocket nozzles)


Thermal qualification

Thermal analysis (math. modelling, computer modelling)

STM (Structural Thermal Model – experimental)

EQM (Engineering Qualification Model) – full extent TVAC (thermal vacuum) tests

FM (Flight Model – limited extent TVAC tests


Thermal analysis


PICAM – STM (Structural Thermal Model)


NUADU – PD (thermal design)

thermal conduction bridge


NUADU – electronics



NUADU – mechanical design



Temperature balance of the object in space

Thermal income (absorbed by black body) from the Sun (Solar constant SC)

0.39 AU (Mercury orbit) SC = 9130 W/m2

1.0 AU (Earth orbit) SC = 1367 W/m2

1.52 AU (Mars orbit) SC = 589 W /m2

9.54 AU (Saturn orbit) SC = 15 W/ m2

Pabs = s.A.SC (Sun is practically a point source, only the projection area is considered)


Thermal outcome (isotropic radiation of black body to space background, T = 2.7 K)

Stefan-Boltzman law:

Elementary example (1AU, black body ball, s= H =1 )

Pabs = Prad

T = 278K = +5,5 °C

4... TAP Hrad

422 .).4()..( TrSCr


σ = 5.670367 × 10−8 Wm−2K−4 - Boltzman constant

Pabs


Surface radiation constants

s= absorptivity (Solar, 0 – 1) (0 = perfect reflector, 1 = perfect absorper = black body).

Absorptivity is related to solar spectrum, i.e. black body at T = 5776 K.

H = emissivity (Hemispherical, 0 – 1) (0 = no radiation, 1 = perfect radiator = black body)

Emissivity is related to IR radiation of black body at T = 300 K



Material s H s / H T [°C]

OSR 0.09 0.82 0.11 -113

ElectroDag501 0.94 0.81 1.16 +16

VD Au 0.23 0.025 9.2 +212

ITO

SiO2

VD AL

IR (λ ~ 12 µm)

Optical Solar Reflector

(SSM=Second Surface Mirror)

4

422

4

.).4()..(

SCT

TrSCr

H

S

HS


VIS (λ ~ 0.5 µm)

Pabs


OSR


NUADU – OSR (Optical Solar Reflector)


SERENA/PICAM

PICAM (Planetary Ion CAMera) ESA-BepiColombo, Mission to Mercury

OSR


Thermal insulation of spacecraft (MLI = Multi Layer Insulation, typ. 5-25 layers)

Optionally perforated


Onboard3

Double Star/TC-2 Instrument platform

before MLI installation


Double Star/TC-2 installation of MLI (Multi-Layer Insulation)


NUADU – MLI (Multi-Layer Insulation) installation


NUADU TVAC Q-tests (IRF Kiruna)


NUADU TVAC Q-tests


PEEL TVAC-test at IEP-SAS


skCUBE TVAC-test at IEP-SAS


High vacuum in space

Space ultra-high vacuum: 10-12 to 10-17 bar

No conductive thermal transfer

Only high-vacuum qualified componnts

Only non-volatile materials (HV systems risk, optical sys., etc.)

„Fast outgassing design“ (no cavities, perforated MLI, etc.)

HV design: no sharp edges – electron emitters, surfaces -photoemissions, etc…

Only dry lubricants (space tribology: MoS2, but not graphite !)

Metals and ceramics o.k.(no Cd, Zn, Sn, sublim., whiskers !)

Plastics: PEEK, VESPEL, KAPTON, TEFLON, Dialylphtalate,...)


NUADU/EM high voltage deflection system

sharp edges = electron emitters !

Al + Allodyne -> photoelectrons from solar UV !


NUADU/FM high voltage deflection system (PEEK, black copper, gold, SS)


Space radiation environment Solar wind: low energies in quiet periods but higher energies and

densities at strong eruptions

Energetic particles of inner radiation belt (protons) and outer radiation belt („killer electrons“)

Galactic cosmic rays (protons) 108-109 eV, rarely > 1020eV (UHCR), but low density

„SEU-damage“ Single event upset – only lost of information (memory, SW), O.K. after reboot

Permannt damage (dislocations, breakdowns in semiconductors, lost of instrument, lost of spacecraft)

Degradation of surface materials exposed by solar radiation and solar wind (decay of plastics, lost of transparency of optical materials, changes in s/H, oxygen ions implantation).


Qualified semiconductor components (but >100 krad are under US-ITAR, export restrictions)

Design (LCL, Latch protection)

General and spot-shielding (Ta, Pb, Cu)

Qualification tests:

Usually by model – simulation for specific orbit and expected lifetime (NASA – AMES)

Irradiation by radioisotopes (60Co etc.)

Irradiation on particle accelerators.

Space radiation tolerant design


NUADU – DPU (rad-hard components, spot-shielding, thermal bridge)


EMC - Electromagnetic compatibility Conducted emissions

Radiated emissions

Conducted susceptibility

Radiated susceptibility

-----

Magneto-static cleanliness (stabil mag. moments, feromagnetic materials...

Electrostatic cleanliness – shielding of own fields (HV systems), surface charging: surface conductivity (ITO), active spacecraft potential control (ASPOC)


EMC - qualification tests


Thanks for your

attention !

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