XUVLab

Tecnologie ottiche per lo spazio Tecnologie ottiche per lo spazio

Emanuele PaceEmanuele Pace

INFN – Sez. di FirenzeINFN – Sez. di FirenzeDip. Astronomia e Scienza dello SpazioDip. Astronomia e Scienza dello Spazio

Università di FirenzeUniversità di Firenze

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Ottica per lo spazio a FirenzeOttica per lo spazio a Firenze

INFN FirenzeINFN Firenze

Dip. Astronomia e Scienza dello Spazio – Università di Dip. Astronomia e Scienza dello Spazio – Università di Firenze Firenze

INAF - Osservatorio di ArcetriINAF - Osservatorio di Arcetri

INOAINOA

Galileo AvionicaGalileo Avionica

LAVLAV

Environmental Research ServicesEnvironmental Research Services

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= 330 = 330 ÷ 400 nm÷ 400 nmEUSOEUSO

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Progettazione otticaProgettazione ottica

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Esempio: HERSCHELEsempio: HERSCHEL

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Secondario adattivo: tecnologia provata al telescopio Secondario adattivo: tecnologia provata al telescopio MMT (6.5m diam.)MMT (6.5m diam.)

Gen. 2003 – Courtesy of CAAO

336 attuatori642mm diam.

Primo secondario adattivo al mondo

Oggetto debole

Oggettodebole

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StruttureStrutture Gruppi di progettazione ottica di sistemi ottici (INOA, Gruppi di progettazione ottica di sistemi ottici (INOA,

DASS, INAF)DASS, INAF) Laboratorio di fabbricazione prototipi ottici (INOA)Laboratorio di fabbricazione prototipi ottici (INOA) Laboratorio di progettazione e produzione di coatings e Laboratorio di progettazione e produzione di coatings e

fabbricazione di specchi e filtri multistrato (LAV, DASS)fabbricazione di specchi e filtri multistrato (LAV, DASS) Camere bianche per sviluppo rivelatori e per la Camere bianche per sviluppo rivelatori e per la

produzione di ottiche strutturate (Dipartimento di produzione di ottiche strutturate (Dipartimento di Astronomia e Scienza dello Spazio)Astronomia e Scienza dello Spazio)

Laboratori di test e allineamento ottiche e FPA (DASS, Laboratori di test e allineamento ottiche e FPA (DASS, INFN)INFN)

Proposta alla Commissione Luce di Sincrotrone LNF per Proposta alla Commissione Luce di Sincrotrone LNF per facility di test nell’IR-VIS-UV-softX per sistemi spaziali facility di test nell’IR-VIS-UV-softX per sistemi spaziali anche di grandi dimensioni (DASS, INFN)anche di grandi dimensioni (DASS, INFN)

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Consorzio per l’otticaConsorzio per l’ottica

Centro per le ottiche spazialiCentro per le ottiche spaziali INOA, Dip. Astronomia - UNIFI, INAF, LENSINOA, Dip. Astronomia - UNIFI, INAF, LENS Attività:Attività:

Progettazione otticaProgettazione ottica Ottiche ultraleggereOttiche ultraleggere Ottiche di grandi dimensioniOttiche di grandi dimensioni Sistemi di ottica adattivaSistemi di ottica adattiva Multilayers e filtriMultilayers e filtri RivelatoriRivelatori LIDARLIDAR

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Technological issues for Technological issues for large area space optics large area space optics

WeightWeight a conventional 3 m a conventional 3 m lens or mirror is too heavy (> 1000 kg) for any lens or mirror is too heavy (> 1000 kg) for any

reasonable spacecraftreasonable spacecraft Ultralightweight optics requiredUltralightweight optics required

Surface qualitySurface quality A sufficient optical surface quality must be guaranteed after launch and A sufficient optical surface quality must be guaranteed after launch and

under orbital conditionunder orbital condition Active surface control possibly neededActive surface control possibly needed

DeploymentDeployment 3 m is about the maximum diameter possible with available launchers 3 m is about the maximum diameter possible with available launchers

(2.5 m for Shuttle)(2.5 m for Shuttle) In orbit mechanical deployment necessaryIn orbit mechanical deployment necessary

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Space mirrors’ areal densitySpace mirrors’ areal density

Technologies Kg/m2 Kg @ 5 mHubble primary 180 3533Current 10 196Developing 1 20Membrane mirror 1.0E-02 2.0E-01Reflective coating 1.0E-04 2.0E-03

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Concept of thin glass Concept of thin glass active mirrorsactive mirrors

The optical surface is coupled to stiff lightweight support structure The optical surface is coupled to stiff lightweight support structure through array of actuators, adjusted on wavefront measurements.through array of actuators, adjusted on wavefront measurements.The thin mirror is made out of thicker glass substrate while held to rigid blocking body with pitch The thin mirror is made out of thicker glass substrate while held to rigid blocking body with pitch

..

Mass~ 5 Kg/m2

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Suitable mirror materialsSuitable mirror materialsNeeds:Needs: 1.1. stiffstiff and and lightweightlightweight structure for structural integrity during launch structure for structural integrity during launch

and operations;and operations;2.2. lowlow coefficient of thermal expansion (CTE); coefficient of thermal expansion (CTE);3.3. isotropicisotropic materials. materials.

GLASS (low stiffness, low CTE, eg. Silica-based glass)GLASS (low stiffness, low CTE, eg. Silica-based glass) METAL (highly reflective, high stiffness, high CTE, eg. Al)METAL (highly reflective, high stiffness, high CTE, eg. Al) CERAMIC (eg. Silicon Carbide: very high stiffness, low CTE)CERAMIC (eg. Silicon Carbide: very high stiffness, low CTE) POLYMER (eg. Kevlar: negative CTE; high stiffness)POLYMER (eg. Kevlar: negative CTE; high stiffness) COMPOSITE (mixing of materials, eg.fibers & matrices)COMPOSITE (mixing of materials, eg.fibers & matrices) FOAM (replacing web structure FOAM (replacing web structure lighter & stiffer struct,) lighter & stiffer struct,)

A-Technology, Consorzio Technologis, ProtekA-Technology, Consorzio Technologis, Protek

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In orbit deployment (I): Inflatable In orbit deployment (I): Inflatable conceptsconcepts

Launch into orbit large piece of thin foil that has been rolled up Launch into orbit large piece of thin foil that has been rolled up with supporting ring structure.with supporting ring structure.

Assemble pieces and inflate reflective and stretchable material Assemble pieces and inflate reflective and stretchable material (membrane) with a gas.(membrane) with a gas.

If membrane stretched beyond elastic limit permanent shape If membrane stretched beyond elastic limit permanent shape change, after pressure is released.change, after pressure is released.

Eg: Inflatable reflector: 25 m Ø with ~ 1 Kg/m2 - ARISE antenna

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In orbit mirror deployment (II)In orbit mirror deployment (II)The proposed mirror diameter requires in orbit deployment or assemblingMaximum diameter possible with current launchers is 3 - 5 m Angular tolerances are not so stringent, 0.1° (0.001 ° mechanically possible)

Possible deployment techniques

• Self deployment (like most antennas)• Assembling by robots on the Shuttle• Assembling by robotic arms on the ISS

After assembling on ISS, the system could remain as external payload

ORSeveral systems could be assembled this way then moved to a different orbit as free flyers

(space factory concept)

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A concept from NASA: OWLA concept from NASA: OWLDeployable Schmidt camera

During deployment

Packaged in the spacecraft

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ALSOALSO project proposal project proposal

Advanced Lidars for Space Operation

laser beam Laser

electronics

detector

light shade

main mirror

2

10

m Ø

A new generation of advanced LIDAR for active Earth observation (atmosphere, land, waters)

large ultralight mirrors

Already proposed as Italian contribution in the ESA Roadmap for LIDAR Technology Development for Earth Observation Programme

Atmospheric monitoring also needed for UHECR trace modeling cooperation ?

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Deployable antennas Deployable antennas technologiestechnologies

40 m

JAXA Engineering Test Satellite ETS-VIII

Purpose:orbital experiments on Large-Scale Deployable Reflectors,

Application:High-Power Transponder for mobile satellite communications from geostationary orbit

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KLYPVE: tecnologia dalla RussiaKLYPVE: tecnologia dalla Russiaa segmented Fresnel mirror 1.8 m , 14° FOV

A reduced version (TUS, 0.6 m ) is under construction

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Lightweight mirror designsLightweight mirror designs Open backOpen back: material removed from back side.: material removed from back side. ~ 8 Kg/m~ 8 Kg/m22

Sandwich styleSandwich style: : contiguous mirror surface- front and back - with contiguous mirror surface- front and back - with sparsely supported center section. sparsely supported center section. ~~ 7 Kg/m 7 Kg/m22

Contoured backContoured back: unnecessary mass removed from back outer : unnecessary mass removed from back outer perimeter (the simplest form).perimeter (the simplest form).

DeformableDeformable: accommodate surface figure compensation with : accommodate surface figure compensation with actuators.actuators.

Open back Deformable

2020 XUVLab

Ottiche adattiveOttiche adattiveAdaptive telescope mirrors:• Fast control of (curved) mirror shape (> 1 kHz)• Small scale of correction (~ 30 mm actuator separation)

Use • a very thin (gass) mirror • a rigid (glass) “back plate” as short term shape reference• magnetic levitation of the thin mirror• capacitive sensing of the gap thickness• a complex real-time digital closed loop control• Optical wavefront sensing for control loop

Adaptive primary segment. Conceptual study for the European Large Telescope

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Interesse per l’INFNInteresse per l’INFN

Rivelazione raggi cosmici e gamma-raysRivelazione raggi cosmici e gamma-rays Controparti ottiche e X dei GRBControparti ottiche e X dei GRB

Telescopi multibandaTelescopi multibanda Fondi di radiazione UV in atmosferaFondi di radiazione UV in atmosfera Progettazione ottica e meccanica payloadsProgettazione ottica e meccanica payloads Optical GSE e facilities di test ottiche e rivelatoriOptical GSE e facilities di test ottiche e rivelatori Problemi di contaminazioneProblemi di contaminazione Test di radiation hardnessTest di radiation hardness Test ottici di payload ottici scientificiTest ottici di payload ottici scientifici Applicazioni per luce di sincrotrone/FELApplicazioni per luce di sincrotrone/FEL

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Progetti e proposteProgetti e proposte

Micro-satellite per la misura multi-wavelength Micro-satellite per la misura multi-wavelength del background – interesse per misure di del background – interesse per misure di tracce di fluorescenza in atmosfera tracce di fluorescenza in atmosfera

raggi cosmici raggi cosmici Petrolini Petrolini

meteore e micro-meteoriti meteore e micro-meteoriti meeting meeting Firenze 28 feb.- 1 mar.Firenze 28 feb.- 1 mar.

Space LIDARsSpace LIDARs