Biophotonic Detection , NASA, and Europa.pdf

Draft description of biophotonic detection of exoplanet life, NASA's single photon detection CMOS, and a possible Europa mission including fake positives and mitigations

1. Biophotonic Detection of Exoplanet Life +
NASA Single Photon Detector + Europa Testing
Concept Overview
Most living organisms—from plants to microbes—emit ultra‑weak photons (“biophotons”) as a
by‑product of metabolic and oxidative processes. On Earth this glow is vanishingly faint, but if
you could detect single photon emissions, a dense biosphere might be detectible.
Why the NASA SPSCMOS work matters for
biophotonic detection
NASA Reference: Advancing Single-Photon Sensing Image Sensors to Enable the Search for
Life Beyond Earth
•Single-photon sensitivity in an imaging array. Single Photon Sensing SPSCMOS can
count individual optical photons and even resolve photon-number histograms across
millions of pixels, enabling spatially resolved low-light maps instead of just single-point
counts. That’s huge for finding localized glowing patches (microbial mats, colonies,
“glow reefs”) or mapping emission patterns inside a dark chamber.
•Very low dark current / read noise at modest cooling. The RIT/CfD team report dark
current dropping to ~1 electron every 30 minutes at ~250 K and near-zero read noise —
this reduces false counts dramatically and lengthens integration times before thermal
noise dominates. For a lander dark chamber (where tight cryogenics are expensive), being
able to run at ~250 K or higher is a practical advantage.
•Radiation tolerance & readout modes. They’re explicitly developing readout schemes
and pipeline tools to mitigate cosmic-ray hits and cumulative radiation damage — critical
for outer-planet missions (Europa) where the radiation environment would otherwise
swamp weak biological signals.
•NIR extension & device simulation. They’re designing NIR variants (including HgCdTe
concepts) so the technique can be extended beyond visible wavelengths — important
because some hypothetical biopigments or chemiluminescent pathways might emit in the
NIR, and NIR suffers less scattering in some media.

2. •Large-format, practical imaging devices. SPSCMOS gives you megapixel arrays with
imaging capability (not just single detectors), making survey/scene characterization much
more efficient than single-pixel SNSPD point detectors
How this helps — concrete use cases
1.Europa / Mars lander dark-chamber imaging
◦Use SPSCMOS as the large-area imaging detector for an enclosed, optically
sealed dark chamber. It can produce maps of weak steady or pulsed emission
across samples (regolith, ice cores, microbial mats). Radiation-mitigating readout
modes are directly useful on Europ
2. Wide-field detection of planktonic/algal mats or colonies
•In water or ice pockets, SPSCMOS imaging can locate hotspots so a narrower, more
sensitive detector (e.g., SNSPD fiber or gated PMT) can be slewed in for photon-statistics
and spectral work.
3. Time-resolved photometry & photon-count histograms
•Photon-number resolving and ramp readout modes let you detect temporal patterns
(diurnal modulation, pulsing) and distinguish single-photon noise vs. real bursts — both
key for discriminating biological signals from noise or mineral phosphorescence.
4. Ground / balloon prototype tests
•The article describes ground telescope tests already performed; identical SPSCMOS
prototypes could be used in terrestrial analog tests (Antarctic, deep caves, Antarctic lakes)
or flown on balloons to validate instrument protocols before flight
Remaining gaps & realistic limits
•Absolute sensitivity floor: SPSCMOS is transformative for imaging, but the lowest
possible dark count of SNSPDs (≪1 count/s per detector) is still better for detecting a few
photons·cm⁻²·s⁻¹ over large backgrounds. So for the weakest UPE signals you may still
want SNSPDs for targeted point measurements. SPSCMOS + SNSPD hybrid
architectures are attractive.
•Spectral coverage & quantum yield uncertainty: The NASA team is pushing for NIR
SPSCMOS pixels (and simulations with HgCdTe). That helps, but full optical → mid-IR
coverage may still need different detector families. Which wavelengths an alien
biophoton system uses is unknown, so multispectral capability is desirable.
•Space vs. in-situ tradeoffs: SPSCMOS is being matured for large astrophysics missions
(e.g., HWO). For Europa landers you still must solve RAD-hardening, cryogenics (if you

3. push lower than 250 K), contamination control, and mechanical robustness. The NASA
work already targeting radiation testing and new readout modes directly addresses these
concerns.
Practical instrument concept (near-term, realistic)
•Primary imaging layer: SPSCMOS array cooled to ~220–250 K for low dark current —
used as the first pass to image samples, search for spatially localized photon excess, and
monitor temporal modulation. (NASA results show this is feasible and being space-
qualified.)
•Secondary high-sensitivity channel: One or more small SNSPD/PMT channels fed by
optical fibers (or a small telescope inside the chamber) for ultra-low dark-count follow-up
on candidate hot spots.
•Filtering & polarization: Narrowband optical filters and polarimetry stages to help
reject mineral luminescence and isolate biologically plausible spectral bands.
•Stimulus & control: Capability to apply mild chemical/thermal stimuli to samples while
monitoring photon response to detect metabolic activation signatures.
•On-board processing: Use the SPSCMOS ramp-readout and cosmic-ray mitigation
modes (as NASA is developing) to keep data quality high in radiation environments.
Recommended next steps (practical)
1.Lab experiments: Test current SPSCMOS prototypes imaging realistic analog samples
(drought-stressed plant canopies, algal mats, extremophile cultures) inside a dark
chamber to measure detection thresholds and optimal cooling/readout parameters.
2.Hybrid detector demonstrator: Build a breadboard combining SPSCMOS imaging +
SNSPD fiber feed to compare sensitivity vs. coverage tradeoffs.
3.Radiation tests for in-situ designs: Leverage the NASA team’s radiation-testing
approaches to validate detector behaviour in Europa-like fluxes (they’re already doing
similar tests for HWO)
4.Field-tests: Fly the imaging system on a high-altitude balloon or Antarctic field
campaign to validate noise models and background rejection before committing to a flight
mission.
Bottom line
NASA’s SPSCMOS maturation is an important, concrete step toward making practical, space-
qualified imaging of ultra-low light levels possible. For your biophotonic detection idea it

4. lowers the engineering bar for imaging searches (dark-chamber mapping, swarm/mat surveys,
plume particulate imaging) and supplies critical radiation-mitigation and NIR development work
— though for the very faintest UPE signals you’ll still want complementary ultra-low-dark-count
detectors (SNSPDs) and careful systems engineering. In short: the NASA article turns a
previously speculative instrument requirement into an achievable engineering path.
Europa Mission
Below is a concrete, mission-ready payload architecture for a Europa lander dark-chamber
biophoton detector that combines the new NASA SPSCMOS imaging approach (wide
coverage, imaging, radiation-mitigation) with an SNSPD-based follow-up channel (ultra-low
dark counts for the faintest signals). I include a component list, rough mass/power estimates, two
worked SNR examples, and a stepwise plan for development and testing.
1) High-level concept (what it does)
1.Scoop / drill → deliver sample (ice/regolith/plume particulate) into an optically sealed
dark chamber.
2.SPSCMOS imager performs wide-field, long-integration photon counting to map any
spatially localized emission and find candidate hotspots.
3.For each candidate hotspot, an SNSPD fiber-fed probe or small focusing optic is slewed
in (or fiber coupled) for ultra-sensitive follow-up (photon statistics, time-resolved bursts,
spectrum).
4.Optional stimulus module (mild warming, nutrient vapor, chemical trigger) probes for
metabolic activation and time-correlated photon response.
5.Onboard processing performs cosmic-ray rejection, image stacking, candidate detection,
and telemetry downlink summaries + selected raw event data.
(Notes: SPSCMOS maturity & radiation mitigations from the NASA article make large-format
single-photon imaging practical for an in-situ instrument.
2) Subsystem list
•Sample acquisition & transfer
◦Drill or scoop + sealed sample transfer arm
◦Sterile one-way sample carousel (multiple sample cups)
◦Contamination seals, heaters for sterilization/mating

5. •Dark chamber (science enclosure)
◦Optically black interior, low-reflectance baffles, diffuse calibrator
◦Internal optics bench: imaging lens, filter wheel, polarizer wheel, fiber pickoff
port
◦Ports for stimulus injectors (temperature, minimal nutrient vapor, mechanical
agitation)
•SPSCMOS imaging module (primary survey detector)
◦Mega-pixel photon-counting SPSCMOS sensor + readout electronics (ramp /
photon-count modes)
◦Cold-plate or small radiator to hold detector at ~220–250 K (per NASA work) to
reach very low dark current. Filter wheel (broadband, narrowband, polarizers)
•SNSPD follow-up channel (secondary high-sensitivity detector)
◦Small focusing optic/fiber feed from chamber to SNSPD cryostat
◦Compact cryocooler (mechanical ADR/cryocooler) to reach SNSPD operating
temperature (sub-Kelvin to a few K depending on detector)
◦SNSPD array or single pixel(s) with time-tagging electronics
•Spectroscopy branch (optional)
◦Compact grating spectrometer on fiber feed (for moderate spectral resolution)
•Electronics, processing, storage, comms
◦FPGA/CPU for real-time photon event handling, event filtering, cosmic-ray
rejection, and candidate selection.
•Thermal & radiation engineering
◦Radiation shielding where needed, radiation-tolerant readout FPGA
◦Active thermal control for cold stages (SNSPD cooler) and passive/active cooling
for SPSCMOS
•Calibration & witness sensors
◦Internal LED/laser calibrator (switchable wavelength), dark shutter, radiation /
particle counters, housekeeping sensors

6. 3) Key design numbers & assumptions (order-of-magnitude)
These are the baseline assumptions used for the SNR estimates and sizing below:
•SPSCMOS imaging optic: diameter D = 50 mm (5 cm), working distance d = 20 cm
inside chamber. Imaging throughput (optics + filter + QE) ≈ 50%.
•Sample sizes considered: a) large sample (100 cm²) with high emission (1,000
photons·cm⁻²·s⁻¹) — a “dense, stressed mat” scenario; b) faint sample: 1 cm² emitting 10
photons·cm⁻²·s⁻¹ — a weak UPE scenario.
•SNSPD follow-up: small optics (D ~ 10–20 mm) placed close (d ~ a few cm) via fiber
coupling; SNSPD dark counts ≲ 0.01 counts/s feasible for space-qualified SNSPDs.
•SPSCMOS dark current/readout noise: assumed negligible for the long integrations
thanks to the NASA SPSCMOS performance at ~220–250 K (dark current ~1 e per 30
min per pixel regime). 4) Worked sensitivity / SNR examples (real numbers)
4) Worked sensitivity / SNR examples (real numbers)
Calculation parameters
•Fraction of isotropic hemisphere collected by lens ≈ π (D/2)² / d² divided by 2π → for
D=5 cm, d=20 cm the collected fraction ≈ 0.0078125 (≈0.78%).
•Optical throughput (filters, optics, QE) = 0.5.
Case A — “Bright” patch (detect easily):
•Emission: 1,000 photons·cm⁻²·s⁻¹ over A = 100 cm² <z 100,000 photons/s emitted.
•Collected (after solid angle & throughput): ≈ 390 photons/s arriving at detector.
•Integrate 10 s → signal ≈ 3,900 counts → SNR ≈ √3,900 ≈ 62.
→ Conclusion: large, active mats or concentrated colonies emitting at Earth-high stress
levels would be clearly visible in short integrations with SPSCMOS imaging.
Case B — “Very faint” patch (challenging but possible with integration):
•Emission: 10 photons·cm⁻²·s⁻¹ over A = 1 cm² <z 10 photons/s emitted.
•Collected & throughput → detected ≈ 0.039 photons/s (SPSCMOS imaging geometry
above).

7. •Integrate 1,000 s (~17 minutes) → signal ≈ 39 counts (background from SNSPD dark ≪
signal; SPSCMOS dark negligible), SNR ≈ ~5.6.
→ Conclusion: with long integrations, SPSCMOS imaging can detect very weak UPE
from small samples if backgrounds are controlled.
SNSPD follow-up advantage
•For sub-cm² samples or extremely low fluxes, SNSPD with close coupling (larger solid
angle via proximity/focusing) and dark counts ≪0.01 cps enables detection with much
shorter times or higher SNR. SNSPD is therefore the natural follow-up for candidate
pixels identified in the SPSCMOS map.
5) Mass & power (rough, order-of-magnitude)
These are conservative, early-phase estimates for a payload module that could be accommodated
on a Europa lander concept.
•SPSCMOS imaging module + radiator & readout: mass ~4–6 kg, power ~10–20 W
(active readout + housekeeping).
•SNSPD cryostat + cryocooler + readout: mass ~8–12 kg, power ~30–80 W while
active (depends on cryocooler technology chosen; duty cycling helps).
•Sample handling (drill/scoop/carousel/arm): ~6–12 kg, power variable (~10–30 W
peak).
•Processing & electronics, filters, mechanical structure: ~4–6 kg, power ~10–20 W.
•Thermal/radiation shielding / harness: ~5 kg.
•Total payload: ~30–45 kg and ~60–150 W peak.
These numbers are first-cut estimates and should be refined with specific cryocooler and
mechanism selections. The SNSPD cooling is the dominant mass/power driver; a design
trade is to duty-cycle the SNSPD cooler and rely mostly on SPSCMOS for survey
operations.
6) Operational modes & timeline (on landing)
1.Standby / Calibration (hours): close chamber, run internal dark shutter, calibrate with
internal LEDs, measure background, cosmic-ray rate.
2.Survey mode (SPSCMOS): image multiple sample cups or the full chamber at long
integrations (10–600 s exposures) to produce spatial photon maps. Use stacking and
cosmic-ray rejection.

8. 3.Candidate selection: onboard algorithm picks pixels/regions above significance
threshold and produces thumbnails + time series.
4.SNSPD follow-up: position fiber/optic on candidate region, switch SNSPD on, take time-
tagged photon events, optionally run spectral branch.
5.Stimulus test: run mild thermal or chemical stimulus while monitoring photon response
for time-correlated increases consistent with metabolism.
6.Repeat & cross-validate: test sterile/dummy cups as controls, and repeat to rule out
artifacts.
7) Contamination & planetary protection
•Sterile sample path: single-use sample cups, hermetic seals, and pre-launch sterilization
protocols.
•Witness controls: multiple sterile control cups exposed only to chamber & handling to
detect false positives.
•Data policy: retain raw time-tagged events for high-value candidates for thorough Earth-
based reanalysis.
8) Key engineering risks and mitigations
•SNSPD cooling mass/power — mitigate by: duty cycling, using smaller SNSPD arrays,
hybrid architectures (SPSCMOS → SNSPD only for best candidates).
•Radiation noise — mitigate by radiation-hardened readouts, cosmic-ray rejection
algorithms, and the SPSCMOS readout modes NASA is developing for space.
•Mineral luminescence false positives — mitigate with spectral filters, polarization
discrimination (biological vs mineral luminescence can differ in polarization and time
profile), and sterile controls.
•Contamination — rigorous sterilization and single-use sample cups with chain-of-
custody logs.
9) Recommended development path (next 18–36 months)
1.Breadboard: Build a lab breadboard with an off-the-shelf SPSCMOS sensor and a single
SNSPD fiber-coupled detector. Include an internal dark chamber and sample transfer
mockup.
2.Analog testing: Measure real extremophile/analog samples (algal mats, stressed plant
tissues, psychrophiles) to quantify realistic UPE surface fluxes and response to stimuli.

9. 3.Radiation & thermal tests: Expose prototype electronics and sensors to radiation levels
approximating Europa environment; demonstrate SPSCMOS readout cosmic-ray
rejection routines.
4.Field demo: Fly on a high-altitude balloon or test in Antarctic dark environments to
verify background models and instrument stability.
5.Flight-qualified design: Trade SNSPD cooler designs (JR ADR, mechanical Stirling +
He loop etc.), finalize mass/power, and integrate into a candidate lander payload.
10) Short summary / takeaway
•SPSCMOS imaging + SNSPD follow-up is a practical, powerful combination for in-situ
detection of biophotonic signals in Europa-class environments. The SPSCMOS gives
wide coverage and practical operating temperatures; SNSPDs give the ultra-low dark
counts needed for the faintest signals. NASA’s SPSCMOS work materially lowers the
engineering barrier for the imaging layer; SNSPD cooling remains the primary systems
trade.

False Positives and Mitigations
Below is a concrete, mission-ready payload architecture for a Europa lander dark-chamber
biophoton detector that combines the new NASA SPSCMOS imaging approach (wide
coverage, imaging, radiation-mitigation) with an SNSPD-based follow-up channel (ultra-low
dark counts for the faintest signals). I include a component list, rough mass/power estimates, two
worked SNR examples, and a stepwise plan for development and testing.
1) High-level concept (what it does)
1.Scoop / drill → deliver sample (ice/regolith/plume particulate) into an optically sealed
dark chamber.
2.SPSCMOS imager performs wide-field, long-integration photon counting to map any
spatially localized emission and find candidate hotspots.
3.For each candidate hotspot, an SNSPD fiber-fed probe or small focusing optic is slewed
in (or fiber coupled) for ultra-sensitive follow-up (photon statistics, time-resolved bursts,
spectrum).
4.Optional stimulus module (mild warming, nutrient vapor, chemical trigger) probes for
metabolic activation and time-correlated photon response.

10. 5.Onboard processing performs cosmic-ray rejection, image stacking, candidate detection,
and telemetry downlink summaries + selected raw event data.
(Notes: SPSCMOS maturity & radiation mitigations from the NASA article make large-format
single-photon imaging practical for an in-situ instrument.
2) Subsystem list
•Sample acquisition & transfer
◦Drill or scoop + sealed sample transfer arm
◦Sterile one-way sample carousel (multiple sample cups)
◦Contamination seals, heaters for sterilization/mating
•Dark chamber (science enclosure)
◦Optically black interior, low-reflectance baffles, diffuse calibrator
◦Internal optics bench: imaging lens, filter wheel, polarizer wheel, fiber pickoff
port
◦Ports for stimulus injectors (temperature, minimal nutrient vapor, mechanical
agitation)
•SPSCMOS imaging module (primary survey detector)
◦Mega-pixel photon-counting SPSCMOS sensor + readout electronics (ramp /
photon-count modes)
◦Cold-plate or small radiator to hold detector at ~220–250 K (per NASA work) to
reach very low dark current. Filter wheel (broadband, narrowband, polarizers)
•SNSPD follow-up channel (secondary high-sensitivity detector)
◦Small focusing optic/fiber feed from chamber to SNSPD cryostat
◦Compact cryocooler (mechanical ADR/cryocooler) to reach SNSPD operating
temperature (sub-Kelvin to a few K depending on detector)
◦SNSPD array or single pixel(s) with time-tagging electronics
•Spectroscopy branch (optional)
◦Compact grating spectrometer on fiber feed (for moderate spectral resolution)

11. •Electronics, processing, storage, comms
◦FPGA/CPU for real-time photon event handling, event filtering, cosmic-ray
rejection, and candidate selection.
•Thermal & radiation engineering
◦Radiation shielding where needed, radiation-tolerant readout FPGA
◦Active thermal control for cold stages (SNSPD cooler) and passive/active cooling
for SPSCMOS
•Calibration & witness sensors
◦Internal LED/laser calibrator (switchable wavelength), dark shutter, radiation /
particle counters, housekeeping sensors
3) Key design numbers & assumptions (order-of-magnitude)
These are the baseline assumptions used for the SNR estimates and sizing below:
•SPSCMOS imaging optic: diameter D = 50 mm (5 cm), working distance d = 20 cm
inside chamber. Imaging throughput (optics + filter + QE) ≈ 50%.
•Sample sizes considered: a) large sample (100 cm²) with high emission (1,000
photons·cm⁻²·s⁻¹) — a “dense, stressed mat” scenario; b) faint sample: 1 cm² emitting 10
photons·cm⁻²·s⁻¹ — a weak UPE scenario.
•SNSPD follow-up: small optics (D ~ 10–20 mm) placed close (d ~ a few cm) via fiber
coupling; SNSPD dark counts ≲ 0.01 counts/s feasible for space-qualified SNSPDs.
•SPSCMOS dark current/readout noise: assumed negligible for the long integrations
thanks to the NASA SPSCMOS performance at ~220–250 K (dark current ~1 e per 30
min per pixel regime). 4) Worked sensitivity / SNR examples (real numbers)
4) Worked sensitivity / SNR examples (real numbers)
Calculation parameters
•Fraction of isotropic hemisphere collected by lens ≈ π (D/2)² / d² divided by 2π → for
D=5 cm, d=20 cm the collected fraction ≈ 0.0078125 (≈0.78%).
•Optical throughput (filters, optics, QE) = 0.5.
Case A — “Bright” patch (detect easily):
•Emission: 1,000 photons·cm⁻²·s⁻¹ over A = 100 cm² <z 100,000 photons/s emitted.

12. •Collected (after solid angle & throughput): ≈ 390 photons/s arriving at detector.
•Integrate 10 s → signal ≈ 3,900 counts → SNR ≈ √3,900 ≈ 62.
→ Conclusion: large, active mats or concentrated colonies emitting at Earth-high stress
levels would be clearly visible in short integrations with SPSCMOS imaging.
Case B — “Very faint” patch (challenging but possible with integration):
•Emission: 10 photons·cm⁻²·s⁻¹ over A = 1 cm² <z 10 photons/s emitted.
•Collected & throughput → detected ≈ 0.039 photons/s (SPSCMOS imaging geometry
above).
•Integrate 1,000 s (~17 minutes) → signal ≈ 39 counts (background from SNSPD dark ≪
signal; SPSCMOS dark negligible), SNR ≈ ~5.6.
→ Conclusion: with long integrations, SPSCMOS imaging can detect very weak UPE
from small samples if backgrounds are controlled.
SNSPD follow-up advantage
•For sub-cm² samples or extremely low fluxes, SNSPD with close coupling (larger solid
angle via proximity/focusing) and dark counts ≪0.01 cps enables detection with much
shorter times or higher SNR. SNSPD is therefore the natural follow-up for candidate
pixels identified in the SPSCMOS map.
5) Mass & power (rough, order-of-magnitude)
These are conservative, early-phase estimates for a payload module that could be accommodated
on a Europa lander concept.
•SPSCMOS imaging module + radiator & readout: mass ~4–6 kg, power ~10–20 W
(active readout + housekeeping).
•SNSPD cryostat + cryocooler + readout: mass ~8–12 kg, power ~30–80 W while
active (depends on cryocooler technology chosen; duty cycling helps).
•Sample handling (drill/scoop/carousel/arm): ~6–12 kg, power variable (~10–30 W
peak).
•Processing & electronics, filters, mechanical structure: ~4–6 kg, power ~10–20 W.
•Thermal/radiation shielding / harness: ~5 kg.
•Total payload: ~30–45 kg and ~60–150 W peak.
These numbers are first-cut estimates and should be refined with specific cryocooler and
mechanism selections. The SNSPD cooling is the dominant mass/power driver; a design

13. trade is to duty-cycle the SNSPD cooler and rely mostly on SPSCMOS for survey
operations.
6) Operational modes & timeline (on landing)
1.Standby / Calibration (hours): close chamber, run internal dark shutter, calibrate with
internal LEDs, measure background, cosmic-ray rate.
2.Survey mode (SPSCMOS): image multiple sample cups or the full chamber at long
integrations (10–600 s exposures) to produce spatial photon maps. Use stacking and
cosmic-ray rejection.
3.Candidate selection: onboard algorithm picks pixels/regions above significance
threshold and produces thumbnails + time series.
4.SNSPD follow-up: position fiber/optic on candidate region, switch SNSPD on, take time-
tagged photon events, optionally run spectral branch.
5.Stimulus test: run mild thermal or chemical stimulus while monitoring photon response
for time-correlated increases consistent with metabolism.
6.Repeat & cross-validate: test sterile/dummy cups as controls, and repeat to rule out
artifacts.
7) Contamination & planetary protection
•Sterile sample path: single-use sample cups, hermetic seals, and pre-launch sterilization
protocols.
•Witness controls: multiple sterile control cups exposed only to chamber & handling to
detect false positives.
•Data policy: retain raw time-tagged events for high-value candidates for thorough Earth-
based reanalysis.
8) Key engineering risks and mitigations
•SNSPD cooling mass/power — mitigate by: duty cycling, using smaller SNSPD arrays,
hybrid architectures (SPSCMOS → SNSPD only for best candidates).
•Radiation noise — mitigate by radiation-hardened readouts, cosmic-ray rejection
algorithms, and the SPSCMOS readout modes NASA is developing for space.
•Mineral luminescence false positives — mitigate with spectral filters, polarization
discrimination (biological vs mineral luminescence can differ in polarization and time
profile), and sterile controls.

14. •Contamination — rigorous sterilization and single-use sample cups with chain-of-
custody logs.
9) Recommended development path (next 18–36 months)
1.Breadboard: Build a lab breadboard with an off-the-shelf SPSCMOS sensor and a single
SNSPD fiber-coupled detector. Include an internal dark chamber and sample transfer
mockup.
2.Analog testing: Measure real extremophile/analog samples (algal mats, stressed plant
tissues, psychrophiles) to quantify realistic UPE surface fluxes and response to stimuli.
3.Radiation & thermal tests: Expose prototype electronics and sensors to radiation levels
approximating Europa environment; demonstrate SPSCMOS readout cosmic-ray
rejection routines.
4.Field demo: Fly on a high-altitude balloon or test in Antarctic dark environments to
verify background models and instrument stability.
5.Flight-qualified design: Trade SNSPD cooler designs (JR ADR, mechanical Stirling +
He loop etc.), finalize mass/power, and integrate into a candidate lander payload.
10) Short summary / takeaway
•SPSCMOS imaging + SNSPD follow-up is a practical, powerful combination for in-situ
detection of biophotonic signals in Europa-class environments. The SPSCMOS gives
wide coverage and practical operating temperatures; SNSPDs give the ultra-low dark
counts needed for the faintest signals. NASA’s SPSCMOS work materially lowers the
engineering barrier for the imaging layer; SNSPD cooling remains the primary systems
trade.