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
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History of space scientific instruments at IEP-SAS
(http://space.saske.sk)
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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
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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.
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Magnetosphere
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Trapped particles
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Trapped particles
F = q(v x B)
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Space scientific instruments from IEP-SAS
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MEP – functional block diagram (Monitor of Energetic Particles)
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NUADU – functional block diagram (NeUtral Atom Detection Unit)
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SK-1 INTERKOZMOS - 17 (1977) (24.9.)
SPE-1 ACTIVE (1989)
SONG CORONAS-I (1994) CORONAS-F (2001)
AUOS-Z
Instruments and spacecraft
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PROGNOZ
DOK-T PROGNOZ-10
(1981)
DOK-1 INTERSHOCK (1985)
DOK-2 INTERBALL-T (1995) INTERBALL-A (1996)
Instruments and spacecraft
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MAGION
DOK-S (with FEI-TUKE)
MAGION-2, ACTIVE (1989)
MAGION-3, APEX (1991)
MAGION-4, INTERBALL-T (1995)
MAGION-5, INTERBALL-A (1996)
Instruments and spacecraft
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Orbital station MIR ( † 23. 03. 2001)
SPE-1M (1996)
DOSIMETRY Mission ŠTEFÁNIK
(1999)
Ivan BELLA © NASA – STS 12.06.1998
Instruments and spacecraft
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SLED-2 (1996)
MARS-96 (1996)
Instruments and spacecraft
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MARS-96
Instruments and spacecraft
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MARS-96 launch on 16. 11. 1996
Instruments and spacecraft
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Rosetta (2004-2016)
ESS
Instruments and spacecraft
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Double Star (2004)
NUADU
Instruments and spacecraft
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NUADU operations
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HotPay-2 (2008)
PEEL
Instruments and spacecraft
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Spectrum-RADIOASTRON (2011)
MEP-2
Instruments and spacecraft
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BepiColombo (MPO)
(2018 ?)
SERENA / PICAM
Instruments and spacecraft
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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
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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).
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ESS processor for ESA-Rosetta (Dual redundant)
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ESS processor for ESA-ROSETTA (Clean Room operations)
*2.3.2004 … † 27.7.2016
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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)
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Mechanical design and Stress Analysis (BepiColombo/PICAM)
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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)
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NUADU Vibration test (NSSC Beijing)
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Vibration test of Rosetta lander Philae
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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
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NUADU - impact test 600g
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Vibration tests HotPay-2 (PEEL)
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IR (~10um)
31.01.2008 / 19:14:00 UTC
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Experience is something you don't get until just after you need it.
Steven Wright
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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)
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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
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Thermal analysis
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PICAM – STM (Structural Thermal Model)
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NUADU – PD (thermal design)
thermal conduction bridge
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NUADU – electronics
thermal conduction bridge
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NUADU – mechanical design
thermal conduction bridge
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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)
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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
Temperature balance of the object in space
σ = 5.670367 × 10−8 Wm−2K−4 - Boltzman constant
Pabs
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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
Temperature balance of the object in space
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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
Temperature balance of the object in space
VIS (λ ~ 0.5 µm)
Pabs
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NUADU – OSR (Optical Solar Reflector)
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SERENA/PICAM
PICAM (Planetary Ion CAMera) ESA-BepiColombo, Mission to Mercury
OSR
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Thermal insulation of spacecraft (MLI = Multi Layer Insulation, typ. 5-25 layers)
Optionally perforated
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Onboard3
Double Star/TC-2 Instrument platform
before MLI installation
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Double Star/TC-2 installation of MLI (Multi-Layer Insulation)
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NUADU – MLI (Multi-Layer Insulation) installation
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NUADU TVAC Q-tests (IRF Kiruna)
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NUADU TVAC Q-tests (IRF Kiruna)
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NUADU TVAC Q-tests
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PEEL TVAC-test at IEP-SAS
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skCUBE TVAC-test at IEP-SAS
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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,...)
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NUADU/EM high voltage deflection system
sharp edges = electron emitters !
Al + Allodyne -> photoelectrons from solar UV !
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NUADU/FM high voltage deflection system (PEEK, black copper, gold, SS)
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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).
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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
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NUADU – DPU (rad-hard components, spot-shielding, thermal bridge)
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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)
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EMC - qualification tests