SPICA
SPICA

Birth & Evolution of Galaxies
Early Universe

Current Universe

Space Infrared Telescope forSpace
Infrared
Telescope for Cosmology and Astrophysics
CosmologyandAstrophysics→(formerly called HII/L2)
Star-formation History

SPICA Working Group

Takao Nakagawa
http://www.ir.isas.ac.jp/SPICA/index.html(ISAS, Japan)

MIR-FIR: less extinction, total energy (Deep Imag.)Redshift: PAH features (Low resolution spect.)

Birth & Evolution of AGNs



Outline of SPICA

MIR Diagnostic Lines (Spect.)

Birth & Evolution of Stars
Orion: Optical

Telescope: 3.5m, 4.5 K
 Core λ: 5-200 μm
 Orbit: Sun-Earth L2 Halo
 Warm Launch, Cooling onOrbit Launch: 〜2010→InfraredStar-formation: Holy Grail of Infrared Astronomy
Chemical Evolution of ISM (spect.)

Formation of Planetary Systems
Proto-Planetary Disks

Scientific Motivation

Exoplanets found !

History of our Univserse

Birth & Evolution of Galaxies
Birth & Evolution of Stars
Birth & Evolution of Planetary Systems


Systematic Study of Proto-Planetary Disks

Direct Detection of Jovian PlanetsHigh-Resolution Obs. on the basis of ISO, SIRTF, ASTRO-F
High-Resolution, High-Contrast Observations

1Wanted !
A Large, Cooled Telescope
Telescope Size

Importance of Mid- and Far-Infrared

SIRTF and ASTRO-FHSO, JWSTThe larger, the better,but….
 Feasible Size: D = 3.5 m
Beautiful results of ISO
But they have D<1m

Much larger than those ofprevious missions (D < 1m)
 Monolithic (not deployable)
mirror → high feasibility

But they are warm↓
We want a large, cooled telescope

Warm Launch, Cooling on Orbit

DesignEffective RadiativeCooling

Warm Launch

Cooling on orbit

No Cryogen

Radiative Cooling & Mechanical Coolers

Old Design

S-E L2 Halo Orbit
Easy Thermal
Shielding

L3

L1Sun

Mechanical
Cryocoolers


Revolution of Design
Philosophy

L4

L2EarthL5

Essential for 4.5K

Thermal Model

New Design
Radiator
Baffle

Heavy
VesselTelescope
Tube

Light
Structure

Shield #1
Shield #2

Large
He Tank

Spacecraft

Shield #3

MirrorFPI

Small
TelescopeSpacecraft

Stressed
Ge:Ga

Large
Telescope

Sun Shield

Sun Shield MLI
Conduction
Radiation

No Cryogen → Large Telescope

20K Pre-cooler 1.7 K Stage Cooler
Bus Module
Bus MLI
4.5K Stage Cooler

2SPICASensitivity

Heat Flow

Optimized for Mid& Far-InfraredEffective Radiation
Into SpaceSPICA Mission
Telescope: 3.5m
 Launching Vehicle: H-IIA-202
 Orbit: Sun-Earth L2 Halo
 Warm Launch → Light Weight (2.6t)
 Radiation Cooling + Mechanical Cooler
TTEL = 4.5K, TFPI < 4.5K (possibly < 2K)
 Launch: 2010


Focal Plane Instruments
First Priority
Technology Development
Programs








NIR Camera & Spectrometer
Sub-mm Camera & Spectrometer

JT Cooler (1)Second Priority

200 mW @ 20 K
similar to those onboard ASTRO-F (2004)

To cool Telescope and MIR instrument
30 mW @ 4.5 K
 similar to those onboard SMILESHigh Resolution
 3.5” @ 50 μm (c.f. 30” for ASTRO-F)Stirling Cooler (Precooling)with Coronagraphic Capability

Far-Infrared Camera & Spectrometer

Mechanical Cryocoolers
Light-weight TelescopeCryocoolers

Mid-Infrared Camera & SpectrometerComplimentary to
HSO & JWSTModest Cryocoolers(Q~30 mW@4.5K)

4.5K(fixed)

Most Sensitive
among proposedmissions@15-130μm

JT Cooler (2)To cool FIR instrument
10 mW @ 1.7 K Under development


3

Stirling Cooler

JT Cooler (2)It is Working !
Results: 10mW
@1.66 K

C.f. Goal: 10mW
@ 1.7KASTRO-F

Goal: 200 mW @ 20 K → Ok !
Working for more than 3 years !
To be flight-proven in 2004



JT Cooler (1)Spec. of Telescope System

Developed for SMILES(Superconducting Submillimeter-waveLimb-emission Sounder)

3.5m Clear Aperture
Diffraction Limit at 5μm

Goal: 30 mW @ 4.5 K → OK !
Working for more than 8,000 hours !
To be flight-proven in 2005

Very Smooth Surface forCoronagraphOperation Temp. 4.5 K
Light Weight < 700 kg
Area Density of Primary < 25 kg/m2

JT Cooler (2)Goal: 10 mW @ 1.7 K
He for Low Temp.
Under Development

ASTRO-F Telescope3６７ cm R.C.
 Oper. Temp. 5.8 K
 Diff. Limit @5μm
 SiC
Porous CoreCVD Coat2
 Area Density 28 kg/m
 But D<1m4

ハンマーヘッド型
冷却治具

試料台

図３

極低温熱変形評価

New Material C/SiC
C/SiC

4CTE (PPM/K)
）
K/mpp
（率張膨線

32

Previous C/SiC
10Current C/SiC‑1050100150200250

温度（K）
Temperature(K)Advantage: 図４
Large極低温熱変形評価
Monolithic Mirror
Disadvantage: Large
CTE at low T? →高Solved
精 度 鏡面 実 現の た め
プリプレ グ積層離型シート

ブリー ザークロスの課 題

Summary

SPICA: 3.5 m telescope cooled to 4.5 K
Warm Launch, No Cryogen, Cooling on Orbit

Optimized for Mid- and Far-Infrared
Astronomy Ideal Successor of ISO, SIRTF, and ASTRO-FA BIG Jump

Complimentary to HSO and JWST High FeasibilityOn the basis of technologies available now (or tobe available soon)

SPICASpace Odyssey 2010

5天体観測日本の宇宙科学の将来構想• 恒星の世界へ• 銀河の世界へ• 宇宙の果てへ
中川貴雄（宇宙科学研究所）

1. Space Astronomy at ISAS
Scientific Objectives
1. Early Universe
Formation of large scale structure and galaxies
2. Formation of stars and planets
Origin of life
3. Physics in extreme condition
Fundamental physics
X-ray
Radio
InfraredSolar Science(ASCA) ⇨・HALCA

ASTRO-EII⇨・
ASTRO-F
SOLAR-B

Tenma (1983)ISAS
SATELLITESANDSPACECRAFTS⇨・⇨・NeXT, XEUS
VSOP-2
SPICA

X-ray astronomy

Hakucho (1979)

ASCA (1993)

Ginga (1987)

1

ASTRO-EIIRadio AstronomyHALCA satellite• Recovery Mission of Astro-E

Deployment of 8m antenna
Launched by M-V-1 in 1997
• Highest Spectral Capability
in 3 - 10 keV• Wide-band Spectroscopy
over 0.5 - 600 keV

Angular Resolution||λ／Diameter
6cm／30,000 km||
2／10,000 arc sec

High Resolution
SpectrometerdE ≤ 10 eV
at 60 mK°

• Mission - Start : April, 2001
• Launch : Scheduled in Jan.- Feb., 2005

Future mission:

New X-ray Telescope Mission (NeXT)

Very Long Baseline
Interferometer in space

Future mission:

VSOP-2 Mission

・Space VLBI mission
Successor of HALCA
・ Compared with HALCA
10 times higher sensitivity
9 times better angular resolution(at 5 GHz)

Scientific objectives○Acceleration mechanism in Universe

・Specification of VSOP-2
Telescope aperture 12m
Observation wavelengths
38mm, 13mm, 7mm
Orbit：perigee：1,000km○Structure and kinematics in Universe○Evolution of Universe

apogee ：30,000km

Launch target: 2009
Launcher: MーV

Future mission:
XEUS: X-ray observation of early Universe

・Launch target
On 2008 with M-V rocket

Infrared Astronomy

International collaboration with ESA

IRTS (Infrared Telescope in Space)
15cm telescope cooled by liq.He
Launched on March 1995
1 month observation period

ISO: Infrared Space Observatory
ESA mission
ISAS contributed receiving station

2ASTRO-F

月・惑星探査First dedicated infrared mission of ISAS
Advanced Infrared Survey
50 times higher sensitivity,
10 times better spatial resolution,
has longer wavelength band,
than IRAS• 固体惑星の起源– 月(LUNAR-A,SELENE)– 小惑星 (MUSES-C)

Advanced cryogenic technology
With 2-stage Stirling refrigerator

Science: Formation and evolution of galaxies, stars, and planets
Launch : February, 2004
Orbit : sun synchronous orbit, 750km altitude
Mission life: >1 year (liq. He holding time)+ 2 years (dedicated to NIR Observations)

Future mission: SPICA• 惑星大気・環境– 火星 (のぞみ)– 金星

Nozomi (Mars Orbiter)

SPace Infrared telescope for Cosmology and Astrophysics

L2 halo orbit, launched with H2A rocket
Telescope aperture ~3.5m
Temperature of the telescope ~ 4.5K
Warm launch, cooled in space
Effective radiation cooling
Mechanical cooler (JT)

Science targets•Upper atmosphere- Solar wind interaction- Atmosphere escape- Magnetic field• Dust•Surface and subsurface

Observatory for mid- and far IR astronomyHigh spacial resolution,
High spectral resolution
in wavelength range 10µm ~200µm

Launch target~2010

Complementary mission to NGST(1-10µm), FIRST(100µm-1mm)

Launched :July, 1998
Mars Orbit Insertion : January, 2004

MUSES-C

Solar Physics
Sample return mission
Target : 1998SF36
Yohkoh satellite (1991- )Hionotori satellite (1981-1991)

Engineering challengeElectric propulsion
Navigation
Sample capture
Reentry

SOLAR-B(2005)

Launch :November, 2002 〜January, 2003 M-V-5
Arrival :June, 2005
Return to earth :June, 2007

3

LUNAR-A•Future mission: Bepi Colombo Mission(Mercury Exploration)

Penetrater mission

Comprehensive study of Mercury
global mapping
magnetismatmospheremagnetosphere

Lunar Seismology
Heat Flow⇩・Internal structure of the Moon

Under evaluation in SCSSInternational collaboration
ESA :Senior partmer
ISAS: Junior partner

Launch : August-September 2003
M-V-2
Lunar Orbit Insert : June-July 2004

Launch :Arrival :20092012

Future Mission: GEOTAIL-II
SELENE

Lunar remote-sensing mission
Lunar Orbiter Satellite + two Sub Satellites
Global Mapping of the lunar surface
14 science instruments for measurements;
elemental abundance, mineral composition, topography,
geological structure, gravity field, magnetic field,
plasma environment, and terrestrial atmosphere

・Multipoint measurements: Formation flight・Particle acceleration in the Earth’s magnetosphere
Magnetic reconnection
Shock

ISAS-NASDA joint mission
Launch in 2005

PLANET-C: Venus Climate Orbiter
Atmospheric dynamics
Remote sensing mission

宇宙航空研究開発機構（仮称)

ISAS approved, and is requiring budget
Launch : Feb.-Apr. 2007 (backup in 2008)
Arrival : September 8, 2009
3-D meteorological observation by multiwavelength cameras

Near-IR• 宇宙三機関 (NASDA, ISAS, NAL) の統合• 2003年10月に、独立行政法人として発足• チャンスか？危機か？

UV4