1	AMS-02 collaboration
FINLAND	  HELSINKI UNIV.
UNIV. OF TURKU

DENMARK	  NETHERLANDS	  USA	  FLORIDA A&M UNIV.
FLORIDA STATE UNIVERSITY
MIT - CAMBRIDGE
NASA GODDARD SPACE FLIGHT CENTER
NASA JOHNSON SPACE CENTERTEXAS A&M UNIVERSITY
UNIV. OF MARYLAND - DEPT OF PHYSICSYALE UNIVERSITY - NEW HAVEN

UNIV. OF AARHUS
RWTH-IRWTH-III
MAX-PLANK INST.
UNIV. OF KARLSRUHEFRANCE	  SPAIN	  CIEMAT - MADRID
I.A.C. CANARIAS.

MEXICO	  UNAM	  PORTUGAL	  LAB. OF INSTRUM. LISBON

I.K.I.
ITEPKURCHATOV INST.
MOSCOW STATE UNIV.

GERMANY	  ESA-ESTECNIKHEFNLRGAM MONTPELLIERLAPP ANNECYLPSC GRENOBLE

RUSSIA	  ROMANIA	  ISSUNIV. OF BUCHARESTSWITZERLAND	  ETH-ZURICH
UNIV. OF GENEVAITALY	  ASICARSO TRIESTE
IROE FLORENCEINFN & UNIV. OF BOLOGNAINFN & UNIV. OF MILANOINFN & UNIV. OF PERUGIAINFN & UNIV. OF PISAINFN & UNIV. OF ROMAINFN & UNIV. OF SIENA

KOREA	  EWHAKYUNGPOOK NAT.UNIV.

CHINA	   BISEE (Beijing)
IEE (Beijing)
IHEP (Beijing)
NLAA (Beijing)
SJTU (Shanghai)
SEU (Nanjing)
TAIWAN	  SYSU (Guangzhou)
SDU (Jinan) ACAD. SINICA (Taiwan)
AIDC (Taiwan)
CSIST (Taiwan)
NCU (Chung Li)
NCKU (Tainan)
NCTU (Hsinchu)
NSPO (Hsinchu)

16	  countries,	  60	  ins/tutes,	  600	  physicists	  since	  1994	   2		  1911 – 2011 : a century of Cosmic Rays
Hess,	  Wulf,	  Wilson,	  Anderson,	  Compton	  Bothe,	  Kohlorster,	  Millikan,	  	  BlackeK,	  Skobeltsyn,	  Rochester,	  	  Butler,	  Rossi,	  Pacini	  ,	  	  Conversi,	  Powell,	  Occhialini	  	  ……	  3	

4	

5	

CR & the Particle Physics connection

particle accelerators taking over (?)

6	Anti-protons by the balloon experiments

BESS/BESS	  POLAR-­‐II	  MASS	  91	  ﬂight	  HEAT-­‐PBAR	  	  7	

Anti-matter in space
The	  stratospheric	  balloon	  program:	  •	  	  	  	  Easy	  to	  ﬂy	  	  •	  	  	  Large	  payloads/mulWple	  ﬂights	  •	  	  Limited	  Time	  exposure	  •	  	  Atmospheric	  background	  &	  TOA	  correcWons	  8	Anti-matter in space:
PAMELA (2006-2011)
On	  orbit	  since	  06/2006	  on	  the	  Russian	  Satellite	  RESURS	  DK1:	  	  109	  triggers	  collected	  	  70°	  ellipWcal	  orbit	  at	  360-­‐600	  km	  	  	  20	  TB	  of	  downlinked	  data	  9	Anti-matter in space:
PAMELA (2006-2011)
The	  positron	  fracWon	  	  The	  anW-­‐proton	  fracWon	  	  10	

The	  all	  electron	  ﬂux:	  	  The	  positron	  fracWon	  	  11	Geomagnetic field + Earth shadow = directions fromwhich only electrons or only positrons are allowed
events arriving from West:e+ allowed, e- blocked

events arriving from East:e- allowed, e+ blocked
For	  some	  direcWons,	  e- or	  e+ forbidden	  Pure	  e+	  region	  looking	  West	  and	  pure	  e-­‐	  region	  looking	  East	  Regions	  vary	  with	  parWcle	  energy	  and	  spacecrab	  posiWon	  To	  determine	  regions,	  use	  code	  by	  Don	  Smart	  and	  Peggy	  Shea	  (numerically	  traces	  trajectory	  in	  geomagneWc	  ﬁeld)	  • Using	  InternaWonal	  GeomagneWc	  Reference	  Field	  for	  the	  2010	  epoch	  ••••12	Anti-matter in space:
PAMELA (2006-2011)
Break	  ?	  in	  p	  and	  He	  spectra	  13	Alpha Magnetic Spectrometer
TRD e/p separation

Particles/nuclei ID by• Charge Z• Rigidity R = p/Ze
• Energy E	

• Velocity v = βc

TOF v, Z	

MagnetSilicon Tracker Z, ±R	

RICH v, Z	

ECAL E (e+/e-, γ)14	Particle signals
e–p

He,Li,Be,..Feγ	

e+– –p, d––He, C

TRD
TOF
Tracker
RICH
ECAL
Physics
exampleCosmic Ray Physics

Dark matter

Antimatter
15	

Time	  of	  Flight	  System	  Measures	  Velocity	  and	  Charge	  of	  parWcles	  Velocity	  =	  Distance	  /	  Time	  ResoluWon	  =	  160ps	  TOF 1 and 22500	  2000	  1500	  TOF 3 and 41000	  500	  1,	  2	  0	  -­‐1.5	  -­‐1	  -­‐0.5	  0	  0.5	  1	  1.5	  Wme	  of	  ﬂight	  (ns)	  PMTs	  ScinWllator	  Light	  Guides	  PMTs	  Light	  Guides	  He	  C	  O	  Al	  Ca	  Plane	  4	  3,	  4	  nuclear	  charge	  Q	  16	One	  of	  20	  layers	  	  TransiWon	  RadiaWon	  Detector	  (TRD):	  	  idenWﬁes	  Positrons	  and	  Electrons	  	  radiator	  Signal	  wire	  Straw	  Tube	  Xe/CO2	  heavy	   electron	  parWcle	  e+	  17	

18	Calorimeter	  (ECAL)	  19	Silicon Tracker
Tracker	  Layers	  1	  2	  3	  4	  5	  6	  7	  8	  9	  20	Silicon sensor
Wafer• Thickness
300 μm	• Size7×4 cm2• Total number 2264	

• Total area
6.75 m2

Ohmic (n) side
• Implant pitch 104 μm	

• Readout pitch 208 μm• Read out channel 384	• Non-bending coord. (X)Junction (p) side
• Implant pitch 27.5 μm• Readout pitch 110 μm• Read out channel 640	• Bending coord. (Y)B21	

Resolution VS angle (Muons on ground)
NIM A 613 (2010) 207
X

Y: Bending direction~10 μm resolution(vertical)

22	

Magnetic Rigidity	

Relation between the curvature and momentum or Rigidity		p 	= qeρB [eV/c]		

R 	= cρB 	

(R = pc/qe [V])
R/GV ≈ 0.3 (ρ/m) (B/Testa)
q < 0  R < 0	e.g.
p = 1 GeV/c, q = 1 (R = 1 GV), 
B = 1 Tesla  ρ ≈ 3.3 mρ	✕B

R = pc/qe	23	Sagitta	s	 	= ρ- √ρ2-(L/2)2		 	≈ ρ- ρ(1-(L/ρ/2)2/2)	

2	0.3BL	 	= L2/ρ/8 = 	8R	

ρ	L	

✕Bs	

√1-x ≈ 1-x/2 (x << 1)	

R = pc/qe	e.g.	

R = 1 GV, B = 1 Tesla, L = 1 m  s ≈ 38 mm 	24	

Rigidity resolution	

0.3BL2	s ≈
8R	ΔR	8Δs	

Δ(1/R) =≈	R2	

0.3BL2	 L	 s	ρ	

✕B

R = pc/qe	e.g.	

B = 1 Tesla, L = 1 m, Δs = 0.1 mm	

 ΔR/R ≈ 2.7 % (R = 10 GV) 	

25	

Maximum Detectable Rigidity	

8Δs	

0.3BL2	

R = 1  RMD =0.3BL2	8Δs	

MDR	ΔR		 	 	 	 =R26	

Multiple scattering	• x/X0 : Thickness in radiation length	• e.g.
x/X0 = 1 %  θ0 = 1.1×10-3 rad /βR	27	

Simulation with scattering	B = 1 Tesla, σx = 0.1 mm ×3, x/X0 = 1 %	ΔR	 	 7.5 ×10-3	=R	β	28	AMS-02 : Timeline 2009~2011
Oct-Dec 	

2009 	

Spectrometer integration at CERN	

Feb 	 	

2010 	

Beam test at CERN	

Mar-Apr	2010 	Space qualification tests at ESTEC	Apr-Jul 	2010 	

Reconfiguration with Perm.Magnet	

Aug 	 	

2010 	

Beam test at CERN	

Sep-Dec 	

2010 	

Payload integration at KSC	May 	 	

2011 	

Launch	 	 	 	 	Start the mission on the ISS	29	

AMS-PM
B= 0.15 T, Lmax= 3m

AMS-SCB = 0.8 T, L = 1 m
Tracker	  Layers	  1	  Tracker	  Layers	  1	  2	  2	  3	  3	  4	  4	  5	  5	  6	  6	  7	  7	  8	  9	  8	  30	

Exposures VS Resolution
MC estimation	

Inner only (L2-8)
4500 cm2sr, MDR 0.2 TV	

L2-8 + L1
1600 cm2sr, MDR 0.6 TV	

L2-8	

L2-8 + L9
950 cm2sr, MDR 0.8 TV	

L2-8 + L1 + L9 (Max Span)
300 cm2sr, MDR 2.0 TV	

L1	1m

L9	31	

Exposures VS Resolution
MC estimation	

Inner only (L2-8)
4500 cm2sr, MDR 0.2 TV	

L2-8 + L1
1600 cm2sr, MDR 0.6 TV	

L2-8	

L2-8 + L9
950 cm2sr, MDR 0.8 TV	

L2-8 + L1 + L9 (Max Span)
300 cm2sr, MDR 2.0 TV	

L1	3mL9	32	

Exposures VS Resolution
MC estimation	

PAMELA
Inner only (L2-8)
2006 ~	

4500 cm2sr, MDR 0.2 TV	

L2-8 + L1
1600 cm2sr, MDR 0.6 TV	

L2-8	3m
1m L1-7	

L2-8 + L9
950 cm2sr, MDR 0.8 TV	

L2-8 + L1 + L9 (Max Span)
Acceptance
300 cm2sr, MDR 2.0 TV	

2L1	L1N	21.5 cm sr L9	

MDR ~1 TV	

33	

Exposures for positrons
L1	L2-8	AMS-PM	

L2-8 + L9
950 cm2sr, MDR 0.8 TV	

L2-8 + L1 + L9 (Max Span)
300 cm2sr, MDR 2.1 TV	AMS-SC	

L1-8 + Ecal
950 cm2sr, MDR 2.2 TV	

L9	34	

Dark	  Ma?er	  Candidate	  χ0	  χ0→	  e+e−	  for	  mχ0	  =	  200	  GeV	  AMS-SC
3 years	e+/(	  e+	  +	  e−)	  PAMELA	

Energy	  [GeV]	  e+/(	  e+	  +	  e−)	  Energy	  [GeV]	  AMS-PM
10 years	

Energy	  [GeV]	  35	

AMS-02 : Timeline 2009~2011
Oct-Dec 2009 Spectrometer integration at CERN
Feb2010 Beam test at CERN
Mar-Apr 2010 Space qualification tests at ESTEC
Apr-Jul 2010 Reconfiguration with Perm.Magnet
Aug
2010 Beam test at CERN
Sep-Dec 2010 Payload integration at KSC
May
2011 LaunchStart the mission on the ISS
36	

37	

Test	  Beam	  Results	  with	  permanent	  magnet	  –	  8-­‐19	  Aug	  2010	  N	  N	  Velocity	  measured	  to	  	  an	  accuracy	  of	  1/1000	  for	  400	  GeV	  protons	  Bending	  Plane	  Residual	  (cm)	  N	  e±	  Energy	  ResoluWon:	  2.5-­‐3%	  Reconstructed	  Velocity	  Energy	  TRD:	  400	  GeV	  protons	  38	

Tracker alignment ~900 beam positions
416

280

80

120

Proton 400 GeV (primary beam)
416
positions: 2 external layers (Full Span)
280+80 positions: At least 1 external layers (Half Span)120
positions: Internal layers
39	

Beam profile on each layer40	Ladder alignment3.5cm• 5 parameters for each ladder have been
determined from residual in the track fittingwith fixed momentum (5×192 = 960 in total)− Translation (dx, dy, dz)
− Rotation(dx/dy, dz/dx, dz/dy)	

30~60cm

41	

Momentum resolution
Momentum resolution dP/P	

AMS-PM: Aug./2010

AMS-SC: Feb./2010

Proton momentum (GeV/c)	

42	

AMS-02 : Timeline 2009~2011
Oct-Dec 2009 Spectrometer integration at CERN
Feb2010 Beam test at CERN
Mar-Apr 2010 Space qualification tests at ESTEC
Apr-Jul 2010 Reconfiguration with Perm.Magnet
Aug
2010 Beam test at CERN
Sep-Dec 2010 Payload integration at KSC
May
2011 LaunchStart the mission on the ISS
43	

44	

Planes alignment check with muons@ KSC (w.r.t. CERN Beam test)
1	Δx < 1 μm	TRD	

2	

3,4	

5,6	

7,8	Δy < 1 μm	

RICH	

Ecal	

9	45	

External planes alignment• Fitting residuals :Prediction of Inner tracker
Multiple scattering
Hit resolution
Alignment shift

1	TRD	

2	3,4	5,6	7,8	Residual sigma

RICH	Prediction

Ecal	9	46	

Alignment Accuracy VS statistics
Measured with muons on ground47	

Alignment Accuracy VS statistics
Estimation for protons on the ISS

48	

Alignment check with EEcal/PTracker	

using e+ and e- sample

SimulationP	γ	e	

EEcal = Ee+ Eγ	

49	

MDR extimated with muons @ KSC
AMS-­‐02	  SC	  Rigidity	  resoluWon	  %	  AMS-­‐02	  AMS-­‐02	  SC	  AMS-­‐02	  Test	  Beam	  Result	  	  	  400	  GeV	  protons	  Rigidity	  (GV)	  50	

AMS-02 : Timeline 2009~2011
Oct-Dec 2009 Spectrometer integration at CERN
Feb2010 Beam test at CERN
Mar-Apr 2010 Space qualification tests at ESTEC
Apr-Jul 2010 Reconfiguration with Perm.Magnet
Aug
2010 Beam test at CERN
Sep-Dec 2010 Payload integration at KSC
May
2011 LaunchStart the mission on the ISS
51	

52	

53	

54	

55	

AMS	  AMS	  	  OperaWons	  TDRS	  Satellites	  Ku-­‐Band	  High	  Rate	  (down):	  Events	  <10Mbit/s>	  	  Astronaut	  at	  ISS	  AMS	  Laptop	  	  AMS	  Payload	  OperaWons	  Control	  and	  Science	  OperaWons	  Centers	  	  (POCC,	  SOC)	  at	  CERN	  S-­‐Band	  Low	  Rate	  (up	  &	  down):	  Commanding:	  1	  Kbit/s	  Monitoring:	  30	  Kbit/s	  White	  Sands	  Ground	  Terminal,	  NM	  AMS	  Computers	  	  at	  MSFC,	  AL	  

56	

57	

Event from the first minutes: e- 20 GeV	58	

Event from the first minutes: Carbon 40 GeV/c	59	Orbital DAQ Parameters

DAQ	  rate,	  average	  700	  Hz	  Proton	  rates	  at	  several	  	  geomagneWc	  laWtudes	  	  DAQ	  eﬃciency,	  average	  85%	  60	AMS collected over 8 billion events
for the first 6 months

Million	  Events	  9235	  8312	  7388	  	  	  	  	  Events	  collected	  	  	  	  	  Events	  reconstructed	  6465	  5541	  4618	  3694	  2771	  1847	  924	  19-­‐May	   	  	  	  7-­‐Jun	   25-­‐Jun	   	  	  13-­‐Jul	  1-­‐Aug	   	  	  19-­‐Aug	  7-­‐Sep	   	  25-­‐Sep	   	  14-­‐Oct	   	  1-­‐Nov	  	  20-­‐Nov	  61	Solar	  Beta	  Angle	  (β)	  The	  angle	  between	  the	  ISS	  Orbital	  Plane	  and	  the	  Solar	  Vector	  ISS	  Ol	  rbita	  PlanSolar	  Beta	  Angle	  (β)	  Orbital	  InclinaWon	  51.6o	  e	  Earthʼs	  Orbital	  Plane	  23.4o	  bit	  rO	  s’
htEarPlane	  Solar	  Vector	  SUN	  ISS	  Orbit	  Plane	  Equatorial	  Plane	  Not	  Drawn	  to	  Scale	  The	  Earth’s	  Orbit	  around	  the	  Sun	  changes	  the	  Solar	  Beta	  Angle	  ~1o	  per	  day	  Ken	  Bollweg	  	  	  NASA/JSC	  62	•	  	  T=	  ~90	  min.	  
63	Solar beta angle
Beta	  angle	  80	  Mar.	  

Jun.	  

Sep.	  

Dec.	  

40	  0	  -­‐40	  -­‐80	  ISS	  64	Apparent beta angle
Beta	  angle	  80	  Mar.	  

Jun.	  

Sep.	  

Dec.	  

40	  0	  -­‐40	  -­‐80	  ISS	  STS-­‐135	  Docking	  and	  	  Undocking	  65	AddiWonal	  thermal	  variables:	  •Shading	  from	  adjacent	  AKached	  Payload	  (Express	  LogisWcs	  Carrier	  –	  ELC)	  ELC2	  Ken	  Bollweg	  NASA/JSC	  66	Thermal	  variables:	  •Solar	  Array	  posiWons	  Solar	  Array	  67	

Beta	  angle	  Ecal	  Temperature	  (°C)	  20	  80	  10	  40	  0	  0	  -­‐10	  -­‐40	  Jun.	   Jul.	  

Aug.	   Sep.	  

68	Outer Tracker Temperatures

High	  beta	  	  +	  shadow	  	  	  	  by	  solar	  array	  STS-­‐135	  Docking	  and	  	  Undocking	  Outer	  Tracker	  (L1)	  Outer	  Tracker	  (L9)	  May/2011	  Oct./2011	  69	Solar beta angle
Beta	  angle	  80	  Mar.	  

Jun.	  

Sep.	  

Dec.	  

40	  0	  -­‐40	  -­‐80	  ISS	  70	

Solar	  Beta	  Angle	  (β)	  The	  angle	  between	  the	  ISS	  Orbital	  Plane	  and	  the	  Solar	  Vector	  ISS	  Ol	  rbita

Orbital	  InclinaWon	  51.6o	  	  Plane	  Earthʼs	  Orbital	  Plane	  Tracker	  Plane	  1	  Sensor	  1N-­‐5	  23.4o	  Solar	  Vector	  SUN	  o	  Warning	  Limit	  o	  Co	  4.5o	  Beta	  Angle	  β	  o	  o	  DestrucWve	  Limit	  Date	  and	  Time	  o	  71	Inner Tracker Temperatures
TTCS	  tests	  May/2011	  Oct./2011	  72	

ADC Mean pedestals

May/2011	  Oct./2011	  73	AMS-02 in flight experience: TOF

proton	  σβ= 4.6%	

TOF	  1	  	  TOF	  2	  	  He	  σβ= 3.0%	

TOF	  3	  	  TOF	  4	  	  74	

AMS-02 in flight experience: TRD

Electrons	

protons	

Test	  Beam	  data	ISS	  data	75	

AMS data on ISS

Photon 40 GeV, 23 May

Direction
reconstructed with 3D
shower samplingGamma 40 GeV, 3D Sampling of Shower
AMS data on ISS

Energy	  (GeV)	  Longitudinal	  proﬁle,	  energy	  40	  GeV	  Layers	  0	  2	  4	  6	  8	  10	  12	  14	  16	  18	  Charge measurement
70	  days	  staWsWcs	  Rich	  ring	  by	  Z=14	  (Si)	  A.Oliva	  CIEMAT	  78	Charge measurement
70	  days	  staWsWcs	  Tracker	  dE/dx VS β	A.Oliva	  CIEMAT	  79	Conclusions• AMS mission started on 19/May/2011 after
successful launch and installation onto ISS• All the detectors are fully operational with theexpected performance• Data calibration (e.g. Tracker alignment,e/p separation study, etc…) is on going• Expecting data taking for more than 10 years

80