Transcript スライド 1 - TAMA 300

Japanese Gravitational
Wave Detectors:
LCGT and DECIGO
Sora
Frontiers in Optics 2009
Laser Science XXV
Oct. 13, 2009
San Jose, USA
Seiji Kawamura (NAOJ),
LCGT Collaboration, DECIGO Working Group
Outline
Roadmap
 Ground-based detector

 TAMA300
 CLIO
 LCGT

Space antenna
 DECIGO
 DECIGO Pathfinder
Roadmap of
the Japanese GW detection
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Ground-based
Advanced LCGT
TAMA
LCGT
CLIO
▲
▲
▲
Space
R&D
DECIGO Pathfinder
Pre-DECIGO
DECIGO
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Ground-based Detector
TAMA300
 CLIO
 LCGT

TAMA300




300 m power-recycled FP
Michelson interferometer
located on the NAOJ
campus in Tokyo
Project started 1995
Best sensitivity in world
2000-2002
5
New Seismic Attenuation System
Joint development with LIGO (Riccardo DeSalvo
et al.) based on earlier Virgo concept
Photo: Nikon
6
CLIO



100 m cryogenic
prototype
Differential FP
interferometer
located in the Kamioka
mine in Gifu
TAMA300
Ground motion in Kamioka mine
Sensitivity of CLIO
Displacement noise 1/√Hz
Mirror suspension thermal noise
--inversely proportional to f 2.5
Thermal noise limit by eddy
current damping between actuator
magnets and metal solenoid holder
--inversely proportional to f 2
Mirror thermal noise
Frequency
LCGT
3km
 Underground at Kamioka
 Cryogenic mirrors

Goal Sensitivity of LCGT
Detection range of LCGT
LCGT in network
LIGO(H)+LIGO(L)+Virgo
LIGO(H)+LIGO(L)+Virgo+LCGT
Max sensitivity (M.S.): +13%
 Coverage at 0.5 M.S.: 100%
 3 detector duty cycle: 82%

Coverage at 0.5 M.S.: 72%
 3 detector
L/H+L/L+Vduty
50% cycle: 51%

L/H+L/L+V+LCGT
50
B. F. Schutz
Organization
LCGT: hosted by ICRR under MOU with NAOJ and KEK.
LCGT collaboration: 118 members (92 domestic, 26 oversea members)
Funding Status
Proposal for the 2010 start did not go
through.
 We will submit a proposal for the 2011
start.
 Application for the stimulus fund was
turned down.

What is DECIGO?
Deci-hertz Interferometer Gravitational Wave Observatory
(Kawamura, et al., CQG 23 (2006) S125-S131)
 Bridges the gap between LISA and terrestrial detectors
 Low confusion noise -> Extremely high sensitivity
Strain [Hz-1/2]
10-18
10-20
Terrestrial
detectors
(e.g. LCGT)
LISA
DECIGO
10-22 Confusion
Noise
10-24
10-4
10-2
100
102
Frequency [Hz]
104
Pre-conceptual design
Differential FP interferometer
Arm length: 1000 km
Mirror diameter: 1 m
Laser wavelength：0.532 m
Finesse: 10
Laser power: 10 W
Mirror mass: 100 kg
S/C: drag free
3 interferometers
Arm cavity
Arm cavity
Laser
Photodetector
Drag-free S/C
Mirror
Transponder type
(e.g. LISA)
Why FP cavity?
Shorten
arm length
Implement FP cavity
Strain
Shorten
arm length
Shot noise
Shot noise
Transponder type
(e.g. LISA)
Implement FP cavity
FP cavity type
Frequency
Better bestsensitivity
Drag free and FP cavity:
compatible?
S/C I
S/C II
Mirror
FP cavity and drag free :
compatible?
Relative position
between mirror
and S/C
S/C II
Local
sensor
S/C I
Mirror
Thruster
Thruster
Drag free and FP cavity:
compatible?
Relative position
between mirror
and S/C
S/C II
Local
sensor
No signal
mixture
S/C I
Mirror
Thruster
Thruster
Actuator
Interferometer
output (GW signal)
Orbit and constellation
(preliminary)
Earth
Correlation
for stochastic
background
Record disk
Sun
Increase angular
resolution
Science by DECIGO
Mini-black
hole

Dark matter
10-19
Formation of 10-20
supermassive BH 10-21
Coalescence
Brans Dicke
parameter
5 years
1 unit
3 months
10-22
10-23
10-24
10-25
Verification
of inflation 10-26
10-3
Shot noise
Correlation
Inflation (3 years)
Coalescence
10-2
10-1
1
10
Frequency [Hz]
102
103
Acceleration
of Universe

Dark energy
Requirements

Force noise of DECIGO should be 50
times more stringent than LISA
 Acceleration noise in terms of h: comparable
 Distance: 1/5000
 Mass: 100

Sensor noise of DECIGO should be10
times looser than LCGT
 Sensor noise in terms of h: comparable,
 Storage time: 10
Roadmap
2009 10
11
12 13
14
17 18 19 20 21
Mission
R&D
Fabrication
R&D
Fabrication
SWIM
15 16
DICIGO Pathfinder
(DPF)
22 23 24
25
26 27 28 29
R&D
Fabrication
Pre-DECIGO
DECIGO
Objectives
Test of key technologies
Detection of GW
w/ minimum spec.
Test FP cavity
between S/C
Full GW
astronomy
Scope
1 S/C
1 arm
3 S/C
1 interferometer
3 S/C,
3 interferometer
3 or 4 units
DEDCIGO Pathfinder (DPF)
Single satellite
 Earth orbit
 Altitude: 500km
 Sun synchronous

Thruster
Local Sensor
Actuator
Arm length: 1000 km
Arm length: 30 cm
conceptual design and
objectives of DPF
Test of frequency
stabilization
system in space
Iodine cell
Test of dragfree system
Floating mirror
Laser
Test of laser
in space
Actuator
Local
Sensor
Thruster
Observation of
GW at 0.1 – 1 Hz
Test of locking
system in space
Payload and standard bus
DPF Payload
Size :
950mm cube
Weight : 150kg
Power : 130W
Data Rate: 800kbps
Mission thruster x12
Mast
structure
Mission
Thruster head
Stabilized.
Laser source
On-board
Computer
Power Supply
SpW Comm.
Satellite Bus
(‘Standard bus’ system)
Size :
950x950x1100mm
Weight : 200kg
SAP :
960W
Battery: 50AH
Downlink : 2Mpbs
DR:
1GByte
3N Thrusters x 4
Interferometer
module
Satellite
Bus system
Bus thruster
Solar Paddle
–13
10
]
1/2
PM
ac
og
Ge
–14
10
–15
ler
–16
10
at
io
n
s
ru
Th
10
ter
–17
no
10
–2
10
–1
10
–13
10
–14
10
6
–15
10
–16
No
Laser
Frequency
10
is
La
se e
noise
–17
r
pr R
10
es ad
Shot noise
su iat
–18
re ion
M
i
r
10
r
o
no
r therm
al
ise
–19
10
0
1
2
10
10
10
ise
–18
10
ce
ity
rav
Noise level [1/Hz
Cavity length: 10cm
Laser: 1064nm, 25mW
Finesse: 100
Mirror mass: 1kg
Q–value of a mirror: 10
–12
10
Frequency [Hz]
1/2
–12
10
Displacement Noise [m/Hz
–11
10
]
Goal sensitivity of DPF
[kpc, SNR=5]
Observable Range
Detection range
2
10
BH QNM
BH Inspiral
1
10
Galactic Center
0
10
–1
10
3
10
4
10
5
10
Mass [M solar]
6
10
R&D for Subsystems
Test mass module
Frequency-stabilized laser
Electrostatic sensor/
actuator
Drag-free
model
Interferometric sensor
Thruster
SWIM launch and operation
Tiny GW detector module
Launched in Jan. 23, 2009
Photo：
JAXA
In-orbit operation
TAM: Torsion Antenna Module with free-falling test mass
(Size : 80mm cube, Weight : ~500g)
Test mass
~47g Aluminum, Surface polished
Small magnets for position control
Coil
Photo sensor
Reflective-type optical
displacement sensor
Separation to mass ~1mm
Sensitivity ~ 10-9 m/Hz1/2
6 PSs to monitor mass motion
Interim organization
PI: Kawamura (NAOJ)
Deputy: Ando (Tokyo)
Executive Committee
Kawamura (NAOJ), Ando (Tokyo), Seto (NAOJ), Nakamura (Kyoto),
Tsubono (Tokyo), Tanaka (Kyoto), Funaki (ISAS), Numata (Maryland),
Sato (Hosei), Kanda (Osaka city), Takashima (ISAS), Ioka (Kyoto)
Detector
Science, Data
Numata
(Maryland)
Ando (Tokyo)
Tanaka (Kyoto)
Seto (NAOJ)
Kanda (Osaka city)
Pre-DECIGO
Sato (Hosei)
Satellite
Funaki (ISAS)
Design phase
DECIGO pathfinder
Leader: Ando (Tokyo)
Deputy: Takashima (ISAS)
Mission phase
Drag free
Detector
Laser
Housing
Ueda
(NAOJ)
Ueda (ILS)
Musya
(ILS)
Sato
(Hosei)
Moriwaki
(Tokyo)
Sakai
(ISAS)
Thruster
Bus
Data
Funaki
(ISAS)
Takashima
(ISAS)
Kanda
(Osaka
city)
Collaborations

LISA
 1st LISA-DECIGO workshop held in JAXA/ISAS (Nov. 2008)

Stanford Univ.
 Charge control using UV LED, etc. ⇒

NASA Goddard
 Fiber laser

MOU
⇒
started discussion
JAXA formation flight group
 Formation flight

Big bang center of the Univ. of Tokyo
 DECIGO adopted as one of the main themes

Advanced technology center of NAOJ
 Will make it a main nucleus of DPF

UNISEC (University Space Engineering Consortium)
 Started discussion
Funding Status
Proceeded to the final hearing as one of the
two candidates for the 2nd small science
satellite run by JAXA/ISAS (launching three
missions between 2012 and 2016), but not
selected.
 We will apply for the 3rd mission. (The
selection will take place in 2010.)

Conclusions

We need LCGT and DPF funded as
soon as possible to establish the GW
astronomy in the future!