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PICASSO

Fussen D., Anciaux M., Bonnewijn S., Cardoen P., Dekemper E., De Keyser J., Demoulin Ph.,, Pieroux D.,

Ranvier S., Vanhellemont F.

contact: [email protected]

PICo-satellite for Atmospheric and Space Science Observations

A scientific CubeSat mission

PICASSO, 9-Oct-2015 beSPACE @ VUB

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ALTIUS: still in phase B1 (after 10 years !)

PICASSO, the future of remote sensing ? Affordable, fast development, evolutive… and slightly risky !!!


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Strategic objectives

At BISA, we believe that pico- and nano-satellites could very well play an important role in the Earth observation in a near future:

They are “cheap” and thus can be deployed as a fleet and be spread all around the Earth, improving the spatio-temporal coverage of the measurements

Due to the fleet innate redundancy, individual failures are not catastrophic

They can be used to test new instrument concepts at a much cheaper cost

They are accessible to “small” countries, and even to institutions

So, why not to demonstrate their potential through a genuine scientific mission?

Objective: to demonstrate Science in a CubeSat mission

VISION, a visible and near-infrared hyper-spectral imager: vertical profiles retrieval

of the ozone density and of the T° via Sun occultations

SLP, a Sweeping multi-needle Langmuir Probe: electronic density and T° of the plasma


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PICASSO, the project

CubeSat mission, embarking 2 scientific experiments for Earth observation: VISION, to retrieve vertical profiles of ozone and t°, via Sun occultation SLP, to study the ionosphere (e-, ions and t°)


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The project set-up

2009: initiated by the Belgian Institute for Space Aeronomy

accepted as ESA In-Orbit Demonstrator kick-off on 21 October 2014

Belgian Institute for Space Aeronomy (BEL), prime: management mission definition & scientific aspects (incl. data analysis) whole development of SLP & software of VISION

VTT (FIN): manufacturing of the VISION hardware

Clyde-Space (UK): platform development & payload items integration tests, ground-station & operations

Centre Spatial de Liège (BEL): system engineering and PA/QA

Launch: mid-2016 ?

Mission duration: min. 2 years

Status : PDR successfully completed on 10 July 2015


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The platform: Clyde-Space Ltd, UK

Triple unit CubeSat (one unit left for the payload) o rigid structure, specifically designed for PICASSO o very light: 332 g

Four deployable 2-unit long solar panels


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The platform: Clyde-Space Ltd, UK

Attitude control: o inertial flight, one face towards the Sun o pointing accuracy: ~1° (knowledge: 0.2°) o 3 reaction wheels + magneto-torquers o star tracker o fine Sun sensor o GPS

Total mass estimated at 3.7 kg

Power budget: 10 W generated, 7.5 W needed

Telecom: o uplink: VHF; downlink: UHF + S-Band o data volume estimated at 52 MB/day


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Solar occultation

Observation of sunsets and sunrises through the Earth’s atmosphere

Occultation technique is self-calibrating (dividing by out-of-atmosphere signal)

Vertical distribution retrieved by onion peeling method


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Ozone retrieval

Absorption increases when looking deeper in the atmosphere (smaller tangent heights)

Ozone retrieved from the Chappuis band (~600 nm)

Measurement at 3 (or more)

Target: 5 % accuracy, 1 km vertical resolution, over the stratosphere

O3

VISION scientific goal 1: polar and mid-latitude stratospheric ozone vertical profiles


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VISION scientific goal 2: mesosphere and stratosphere temperature profiles

Courtesy of NASA

Temperature retrieval

Method 1: shape of the Sun (refractive flattening)

[refractive index depends on t°]

NASA


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VISION scientific goal 2: mesosphere and stratosphere temperature profiles

Courtesy of NASA

Temperature retrieval

Method 2 - Sun light dilution

ARID method [Fussen et al., AMTD., 8, 3571-3603, doi:10.5194/amtd-8-3571-2015, 2015]

2 K accuracy below 72 km


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VISION instrument, VTT (Finland)

Filter module

Collimating optics module

FPI module

Focusing optics module

Electronicsmodule

Heater

Image sensor module

Main housing

FPI control

Heater control

Main electronics

Spectral imager similar to the Aalto-1 Spectral Imager (AaSI) (Fabry-Perot interferometer + CMOS array sensor)

Field of view: 2.5°

Dimensions 97x97x50 mm, mass 500 g

Power < 3 W

VISION stands for “Visible Spectral Imager for Occultation and Nightglow”


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Fabry-Perot interferometer principle

Fabry-Perot Mirrors

Air gap

Incoming light

Transmitted light

400 500 600 700 800 900 10000

0.2

0.4

0.6

0.8

Wavelength/[nm]

Sp

ectr

al tr

an

smis

sion

Fabry-Perot + spectral filters: up to 3 modes Tuneable air gap: piezo actuator Range: ~400-800 nm, FWHM: < 10 nm Detector: commercial CMOS 2048x2048 RGB


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Retrieving 3 wavelengths from RGB


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Courtesy of NASA

Data downlink

S-band for data transmission

downlink capacity (52 MB/day) (SLP+VISION)

10 snapshots/s, 31 occultations/day > 8 GB/day

O3 & t°ARID : only total intensity (px)

Sun shape: 5 image moments

[upon request, rows & col. 880 values]

other benefits of imager: o ensure Sun entirely in the FOV o assess ADCS pointing accuracy o possible coupling with ADCS


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SLP stands for “Sweeping Langmuir Probe”

SLP scientific objectives are the in-situ study of: 1. the ionosphere-plasmasphere coupling 2. the sub-auroral ionosphere and

corresponding magnetospheric features 3. the aurora structure

SLP scientific objectives

ESA-ATG Medialab


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SLP instrument (built by BISA) Principle

4 cylindrical Langmuir probes (at the edge of solar panels)

electrical potential periodically swept with respect to the plasma potential

from electric current collected by each probe, retrieval of: local electron density and t° local ion density spacecraft potential

up to 50 sweeps/sec high spatial resolution (150 m)

power consumption: 1.7 W mass: 150 g envelope electronic boards: 91x95x35 mm boom + probe: 80 mm outside solar panel


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Orbit

high inclination

polar regions (SLP)

occultations @ all latitudes (VISION)

altitude ~550 km

duration 2 years at least

life time < 25 years (debris mitigation)

period ~94 min.

31 occultations/day (SS & SR)


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Consortium

Partners and sponsors

(STCE)

BIS

A


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Spare slides

Parameter Nominal value Remarks

Field of View (FoV) 2.5° x 2.5° The S/C must ensure that the Sun is maintained inside that

FoV during the event duration.

Pixel FoV 0.0025°²

Target wavelength range 400 - 900 nm

Mandatory wavelength range 550 - 650 nm

Mandatory spectral resolution < 10 nm@FWHM Over the whole wavelength range

Spectral resolution target < 5 nm@FWHM

Detector resolution (RGB pixels) 2048x2048

Spectral image size (in pixel) 1024x1024 A set of R, G1, G2 and B pixels reduces to one spectral

pixel

Dynamic range 16 bits

Operational temperature [-25°C ; +30 °C]

Life time and robustness 2 years VISION should be sized for 2 years of lifetime

Amount of snapshots 2 x 107

Temperature cycles 10000

Working hours 600

Mass <700 g

Peak power consumption < 8 W

Average power consumption when

switched on < 4 W

Orbit averaged power 0.2 W Data processing power excluded

Dimensions (mm) 50x95x95 Will fit in half a cube.

Lens aperture 15 mm

Picture size 8 MB 2048 x 2048 x2 bytes

Short historical review

Spring 2009: concept starts within QB50 frame…

Spring 2010: contacts with VTT Finland

Summer 2011: funding by Belgian National Lottery

2012: beginning of the build-up of the solution from the bottom-up

2013:

BELSPO involvement in CubeSats Iterations and convergence on the technical solution Public call for the platform Clyde-Space is selected. Delivery: Oct 2014

2014:

ESA Call (June), Proposal (July, including a description of the technical solution) Negotiation (Oct) Contract (Nov) Kick-off (Oct), progress meeting 1 (Dec)

2015:

Independence from QB50 (March) Radiation tests (PLC and SLP, April) Preliminary design review (April)

Project overview

PICASSO: PICo-Satellite for Atmospheric and Space Science Observations

End-to-end in-orbit demonstration (IOD) mission, CubeSat Technology Pre-Developments

ESA Contract N° 4000112430/14/NL/MH

GSTP and TRP

Total duration: 29 months

Main scientific objectives:

Atmospheric Ozone and T° vertical profile retrieval Local electron density and temperature

Avionics: 3U CubeSat with

Performant ADCS S-Band for scientific data downlink Star tracker & GPS 4 deployable solar panels … and all the rest

Payload:

VISION: a miniaturized tuneable hyper-spectral imager in the visible SLP: a 4-needle Langmuir probes whose electric potential is swept Powerful dedicated computer for data onboard processing

Roles

BISA (prime):

Management All scientific aspects (including inflight scenario definition and data analysis) VISION data processing software SLP Launch Platform (in-kind contribution, subcontracted to Clyde-Space)

CSL:

Technical coordination / follow-up Verification of the interfaces PA/QA

Clyde-Space:

Mission Design Integration of the payload Integrated spacecraft functional and environmental testing Operations (in-kind contribution, incl. the ground-station)

VTT:

VISION hardware

Initial planning (summary)

PICASSO and SIMBA (RMI) divorced from QB50 in Jan 2015 .

Looking now for a commercial flight in Q3-Q4/2016 (and for extra

funding 200 k€ …)

Some new kind of remote sensing measurements with a spectral imager…

picasso - bespacebe-space.eu/wp-content/uploads/2015/11/picasso_fussen.pdf · picasso, 9-oct-2015...

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