The Advanced Thin Ionization Calorimeter (ATIC) Long Duration Balloon Experiment

LSU 01/12/05 Project Initiation Conference 01/13/05

1

The Advanced Thin Ionization Calorimeter (ATIC) Long Duration

Balloon Experiment

A ~1,660 kg experiment, carried to the near-space environment (~36 km) by a large volume (sufficient to fill a football stadium) helium filled balloon for 14

– 30 days over the continent of Antarctica, will measure the charge composition and energy spectra of primary cosmic rays over the energy range

from about 1010 to 1014 eV in order to investigate the relationship between high energy galactic matter and remnant supernova shock waves.

Louisiana State University, Marshall Space Flight Center, University of Maryland, Southern University, Moscow State University, Max Plank Institute for Solar System Research


2

The ATIC Collaboration

1. Louisiana State University, Baton Rouge, LA, USA

2. Marshall Space Flight Center, Huntsville, AL, USA

3. University of Maryland, College Park, MD, USA

4. Skobeltsyn Institute of Nuclear Physics, Moscow State University, Russia

5. Southern University, Baton Rouge, LA, USA

6. Max Plank Institute for Solar System Research, Lindau, Germany

7. Purple Mountain Observatory, Chinese Academy of Sciences, China

J.H. Adams2, H.S. Ahn3, G.L. Bashindzhagyan4, K.E. Batkov4, J. Chang6,7, M. Christl2, A.R. Fazely5, O. Ganel3

R.M. Gunasingha5, T.G. Guzik1, J. Isbert1, K.C. Kim3, E.N. Kouznetsov4, M.I. Panasyuk4, A.D. Panov4,

W.K.H. Schmidt6, E.S. Seo3, N.V. Sokolskaya4, J.P. Wefel1, J. Wu3, V.I. Zatsepin4


3

Standard Model of Cosmic Ray Acceleration • Supernova shock waves may accelerate cosmic rays

via first order Fermi process– Model predicts an upper energy limit of E ~ Z x 1014 eV

ATIC Energy Range


4

ATIC Program Summary Investigate relationship between Supernova

Remnant (SNR) Shocks and high energy galactic cosmic rays (GCR)

Are SNR the “cosmic accelerators” for GCR

Measure GCR Hydrogen to Nickel from 50 GeV to ~100 TeV total energy

Determine spectral differences between elements

Flight test pixilated Silicon detector

Multiple flights needed to obtain necessary exposure ATIC-1 test flight during 2000-2001 ATIC-2 during 2002-2003 – 17 days exposure ATIC-3 anticipated for 2005

Scientific Ballooning programs at Universities provides unique education experiences for the future aerospace workforce ATIC involved over 45 LSU & SU students


5

Ionization Calorimetry only practical method to measure high energy light elements Silicon Matrix has 4,480 pixels to measure GCR charge in presence of shower backscatter Plastic scintillator hodoscope, embedded in Carbon target, provides event trigger plus charge

& trajectory information Fully active calorimeter includes 320 Bismuth Germinate (BGO) crystals (400 BGO crystals

for ATIC-3) to foster and measure the nuclear - electromagnetic cascade showers Geometrical factor: 0.24 m2sr (S1 – S3 – BGO6)

ATIC Instrument Summary


6

Preliminary results from ATIC-1 and ATIC-2 Fill gap between low energy AMS and high energy JACEE with accurate measurements Preliminary indication that Hydrogen and Helium spectral indices are very similar Measurements of Iron group show flattening of spectrum Have measured GCR electrons up to about 2 TeV At the highest energies, the heavy ion spectra show deviations, which might suggest that a

modified Leaky Box Model, including a constant residual pathlength (0.13 g/cm2), is needed.

Preliminary charge histograms for E > 50 GeV from the ATIC-2 flight

Preliminary Results Summary

C

O Ne

Mg

Si

S

Fe

SCa


7

All particle spectrum: ATIC, emulsion, and EAS data

RUNJOB

JACEE

CASA-BLANCA

TibetKASKADETUNKA

ATIC-2


8

Energy spectra for H and He


9

C

O/10

Ne/100

Mg

Si/10

Fe/100

HEAO-3-C2 CRNATIC-2

Energy spectra of abundant nuclei


10

ATIC also is able to identify CR electrons

e

• High energy electrons provides addition information about the GCR source• Possible bump at 600 – 800 GeV seen by both Kobayashi and ATIC may be

a source signature?


11

ATIC Instrument Details Si-Matrix: 4480 pixels each 2 cm x 1.5 cm mounted on offset ladders; 0.95 m x 1.05 m area; 16 bit ADC; CR-1 ASIC’s; sparsified readout.

Scintillators: 3 x-y layers; 2 cm x 1 cm cross section; Bicron BC-408; Hamamatsu R5611 pmts both ends; two gain ranges; ACE ASIC. S1 – 336 channels; S2 – 280 channels; S3 – 192 channels; First level trigger: S1-S3

Calorimeter: 8 layers (10 for ATIC-3); 2.5 cm x 2.5 cm x 25 cm BGO crystals, 40 per layer, each crystal viewed by R5611 pmt; three gain ranges; ACE ASIC; 960 channels (1200 for ATIC-3).

Data System: All data recorded on-board; 70 Gbyte disk (150 Gbyte for ATIC-3); LOS data rate – 330 kbps; TDRSS data rate – 4 kbps (6+ kbps for ATIC-3); Underflight capability (not used).Housekeeping: Temperature, Pressure, Voltage, Current, Rates, Software Status, Disk statusCommand Capability: Power on / off; Trigger type; Thresholds; Pre-scaler; Housekeeping frequency; LOS data rate, Reboot nodes; High Volt settings; Data collection on / offGeometry Factors: S1-S3: 0.42 m2sr; S1-S3-BGO 6: 0.24 m2sr; S1-S3-BGO 8: 0.21 m2sr


12

Assembly of ATIC at Willy

Assemble / test detector stack and mount in lower support structure

Install Kelar pressure vessel shells

Attach the upper

support structure

Attach the thermal protection insulation

Solar arrays provide power &

the payload is rolled out the hanger

door

ATIC is transported to the launch pad


13

Flight and Recovery

The good ATIC-1 landing on 1/13/01 (left) and the not so good landing of ATIC-2 on 1/18/03 (right)

Flight path for ATIC-1 (2000) and ATIC-2 (2002)

ATIC is designed to be disassembled in the field and recovered with Twin

Otters. Two recovery flights are necessary to

return all the ATIC components. Pictures

show 1st recovery flight of ATIC-1


14

ATIC Test Flight from McMurdo 43.5 Gbytes Recorded Data 26,100,000 Cosmic Ray triggers 1,300,000 Calibration records 742,000 Housekeeping records 18,300 Rate records Low Energy Trigger > 10 GeV for protons >70% Live-time >90% of channels operating nominally Internal pressure (~8 psi) held constant Internal Temperature: 20 – 30 C Altitude: 37 1.5 km

Launch: 12/28/00 04:25 UTC Begin Science: 12/29/00 03:54

UTC End Science: 01/12/01 20:33

UTC Termination: 01/13/01 03:56

UTC Recovery: 01/23/01;

01/25/01


15

First ATIC Science Flight from McMurdo 65 Gbytes Recorded Data 16,900,000 Cosmic Ray triggers 1,600,000 Calibration records 184,000 Housekeeping records 26,000 Rate records High Energy Trigger > 75 GeV for protons >96% Live-time >90% of channels operating nominally Internal pressure (~8 psi) decreased slightly

(~0.7 psi) for 1st 10 days then held constant Internal Temperature: 12 – 22 C Altitude: 36.5 1.5 km

Launch: 12/29/02 04:59 UTC Begin Science: 12/30/02 05:40

UTC End Science: 01/18/03 01:32

UTC Termination: 01/18/03 02:01

UTC Recovery: 01/28/03;

01/30/03


16

Preparation for ATIC-3 Refurbish detectors Fall 2003 – Spring 2004 Reconstruct missing structure (left on ice) Spring 2004 Procure missing carbon target (left on ice) Spring 2004 Reconstruct pressure vessel ring / flanges March – June 2004 Leak & Proof pressure test vessel July 2004

Assigned extra task by NASA to certify ATIC for 2004 July 17, 2004

Arrive NSBF for Pre-deployment Integration August 19, 2004

Complete Pre-deployment Integration Hang-Test September 16, 2004

Receive stand-down for 2004 season from NASA October 20, 2004 Directed to maintain ATIC in near flight ready status Extra effort remains unreimbursed by NASA

Packed and ready to ship on 5 days notice Instrument powered in shipping container for running preventative maintenance

tests


17

Pre-deployment Integration Hang Test

Obtained weight for fully assembled payload Verified structural analysis for ATIC-3 configuration Following test, disassembled payload and packed for shipment to McMurdo

Assembled & tested instrument in ATIC-3 flight configuration Added two layers to calorimeter

Flight configuration software loaded and tested

Integrated with NSBF SIP VHF, TDRSS, Iridium All uplink & downlink channels tested

Ground system assembled & tested Through ROCC to flightline control Though POCC to flightline & LSU

control Integrated & tested all NSBF equipment

Pointing rotator NSBF solar arrays Flight ladder, UTP


18

ATIC Weight MeasurementsATIC-1 (2000) ATIC-2 (2002) ATIC-3 (2005)

(493N) (515N) (NSBF 2004)Balloon 3701 lbs 3709 lbs 4050 lbsScience Gondola 3408 lbs 3386 lbs 3515 lbsScience Solar Array 64 lbs 64 lbs 80 lbsNSBF Electronics (SIP,etc.) 481 lbs 481 lbs 505 lbsNSBF Solar Array 140 lbs 128 lbs 150 lbsNASA Rotator 154 lbs 159 lbs 160 lbsParachute & susp. 486 lbs 458 lbs 590 lbsBallast 161 lbs 200 lbs 600 lbsMisc. (1 Ballast Hopper,etc.) 41 lbs 51 lbs 300 lbsGross Load 8636 lbs 8636 lbs 9950 lbs

Added two layers to the calorimeter for total of 10, otherwise no

changes relative to ATIC-2 Use 40M balloon for 2005 Able to carry 600 lbs ballast


19

ATIC Mechanical Certification Initial ATIC Mechanical Report July 2000 ATIC structure certified by NSBF August 2000 Thermal analysis reviewed and approved August 2000 Approval to fly Kevlar vessel at 8 psi November 2000 Successful test flight (ATIC-1) Dec 2000 to Jan 2001

Pressure Vessel Test (10 psi for 24 hrs.) May 2002 Mechanical Report Update July 2002 ATIC structure certified by NSBF August 2002 Thermal analysis reviewed and approved August 2002 Successful science flight (ATIC-2) Dec 2002 to Jan 2003

Pressure Vessel Test (10 psi for 24 hrs.) July 2004 Verified that original FEA was for 10 layer calorimeter July 2004 Mechanical Report Update August 2004 ATIC structure certified by NSBF September 2004


20

ATIC Data Rates Exact data rate is trigger dependent

ATIC-2 high energy trigger resulted in an event rate of 550 to 700 per minute

Average event record size was ~2,200 bytes Data rate was 200 kbps to 250 kbps Other record types add ~10 kbps to this

average data rate.

Downlink telemetry: During line-of-sight (LOS) downlink data stream < 333 kilobits/s via auxiliary

science transmitter Downlink over TDRSS housekeeping, rates, high priority data, some calibration <

4-7 kilobits/s Downlink compressed status information over Iridium via SIP < 29 bytes / min

All data will be recorded on-board the instrument using a 150 Gbyte hard disk Should be able to record all ATIC data for > 50 days

Feasible to reduce average data rate to ~130 kbps and use High Gain TDRSS Downlink >75% of data during flight & be less dependent upon recovery


21

ATIC Commands Discrete Commands

10 discrete lines for power on/off control 4 discrete lines for pressure control Used only at launch, termination, and emergencies

Serial Commands Simple protocol - Uplink cmd, downlink cmd ACK, execute cmd, downlink cmd status/return All primitive cmds are 10 bytes long, so are encoded twice in each 20 byte cmd packet for error

checking Almost all uplinked cmds will be two bytes long and will execute a script of primitive cmds. Command types

Software - Reboot node, Restart process, Start/stop LOS XMTR, etc. Power - Power on/off subsystem, etc. Detector - Calibrate BGO, Select trigger, etc.

Uplink Commands: LOS for experiment check-out max of 100 cmds / hr All primitive cmds are 10 bytes long, so are encoded twice in each 20 byte cmd packet for error

checking During normal ops max of 4 two byte cmds / hr Problem diagnosis & resolution during LDB flight.

Require cmd rate > 4 cmds/hr May require LOS link via airplane underflight


22

ATIC Power System

Flight Data System:

102 Watts- Flight Control Unit - Hard Disk Drives- Data Archive Unit- Detector Control Unit- Auxiliary Science Stack

Detector Electronics:- Silicon Matrix (Fem's, Aclb's, Bias Supply )

62 Watts- Plastic Scintillator (Fem's, Aclb's, Bias Supply )

44 Watts- BGO Calorimeter (Fem's, Aclb's, Bias Supply )

52 WattsTotal Science Power:

260 Watts

Thermal Control Heaters (Not needed during flight)

200 WattsTotal Power:

460 Watts

Solar Array Max Output:

~580 Watts


23

The ATIC Thermal Control System Passive System:

pressure vessel containing internal science

1.5 in fiberglass double-faced insulation blanket

outer facing: Atlas vps white laminate

inner facing: FSK aluminum Absorptivity: 0.26 Emissivity: 0.88

Active System: Internal resistance heaters (200W)

SIP platform external components: battery (5 to 10W) and sci-stack

(2W) insulated from deck charge controller (10 to 20W)

attached to deck as heatsink insulation blanket over components


24

ATIC Success Criteria Project Success:

To meet science goals ATIC needs > 10 good H events at energies > 100 TeV Minimum TOTAL exposure > 40 days with altitude above 110,000 feet Implies multiple flights over multiple years

Minimum Success per Flight: About 8 days with altitude above 110,000 feet with stability of 10,000 feet Integrity of Aux Sci XTM data at 80% while in range 90% of Silicon Matrix area, S1, S3 and BGO layers 2 through 8 are operational Recovery of data from flight recorders Recovery of all critical payload components Photographs to assess structural damage

Desired Performance per Flight: 14 days with altitude above 124,000 feet and stability of 5,000 feet All detectors fully operational Recovery of all data and entire payload

Two (or more) circumnavigations (~30 days) is HIGHLY desired Reduce need for fourth flight Now have two payloads as precedent (TIGER, CREAM)


25

ATIC Launch Site Support Workspace:

~1000 square feet experiment setup and work area 20 feet linear bench/table space for detector work 20 feet linear bench/table/desk space for computers 6 chairs 3 ton overhead hoist with 20 feet clearance

Power: One 220 V, 3 phase, 60 Hz, 6 Amp nominal Two 120 V, single phase, 60 Hz, 15 Amp on UPS Two 120 V, single phase, 60 Hz, 15 Amp

Gas: 3 cylinders of dry Nitrogen System to transfer gas to flight cylinders Clean, dry, compressed air

Communication: Telephone, Internet connection

Other: Access to machine shop Dedicated van for crew transport


26

ATIC Flight Operations Support Launch:

Electrical generator to power ATIC up to launch Command & Data Interface:

Interface to ATIC Ground Data System at McMurdo Interface to ATIC internet repeater at Palestine

Telemetry: Line of sight used during experiment check-out tuning

Downlink 333 kbits/s via Aux. Sci. Transmitter Uplink max of 100 cmds / hour

TDRSS and/or VHF for status & data Max of 4 two byte cmds / hour

Flight Operations: 24 x 7 monitoring of payload at ROCC and POCC Underflight for emergency payload control (if needed)

Termination & Recovery: Air support for termination, follow-down and chute cutaway Air support for recovery of flight data disks and all critical payload

components


27

ATIC On-board Support Orientation:

Rotator to keep PV arrays pointed to the sun

Telemetry: Auxiliary science transmitter to downlink much of the ATIC data stream

during LOS (333 kilobits/s, bi-phase encoded) Will use TDRSS, VHF & Iridium High Gain TDRSS is HIGHLY desired

100 kbps would allow majority of data to be downlinked Reduce need for full recovery

Commanding: Discrete commands through Auxiliary Science Stack (about 14 cmds) From ground through SIP to experiment From underflight through SIP to experiment From experiment to SIP (GPS position, altitude)

Field of View: Minimum mass in field of view


28

ATIC Shipping

Purchased C-container plus using a NSBF C-container to consolidate shipping.

Shipping now reduced to about eight crates: Instrument C-Container (~5,600 lbs) Electronics C-Container (~5,500 lbs) Shell Crate (~2,300 lbs) Solar Array Crate (334 lbs) Battery Crate (260 lbs) Solar Array Struts Crate (276 lbs) Silicon Matrix Crate (440 lbs) Si Matrix Electronic Crate (476 lbs)


29

Anticipated ATIC Schedule

January 13, 05 Project Initiation ConferenceFeb - July 05 Preventative Maintenance Testing

July 05 Final packing for AntarcticaAugust 2, 05 Ship ATIC to McMurdo

~October 1, 05 Late shipment (if necessary)October 28, 05 Setup crew arrives on flight lineNovember, 05 Payload setup and testing

November 10, 05 Silicon Matrix crew arrives~November 27, 05 Partial crew change out

~December 1, 05 Calibrations / Testing with muons~December 6, 05 Flight Ready

~January 4, 06 Partial crew change out~February 3, 06 Instrument recovered, packed for shipment

and remaining crew leaves


30

Flight Operations Schedule


31

Our enthusiastic crew is looking forward to working with NSF, RPSC and NSBF for another successful ATIC flight!

link

Documents

The Advanced Thin Ionization Calorimeter (ATIC) Long Duration Balloon Experiment