1. GLAST Large Area Telescope: I & T Peer Review EGSE/Online System
Gamma-ray Large Area Space Telescope
GLAST Large Area Telescope:
I & T Peer Review
EGSE/Online System
Elliott Bloom
SU-SLAC
Subsystem Manager

2. Outline How subsystem work integrates with I&T
Items that are deliverables.
Flow of Flight SW test and GSE migration
Engineering Models
EM 1 (ACD, CAL, DAQ, TKR)
EM 2 (DAQ, Test Bed)
CU (I&T)
FU (I&T, IOC)
Command and telemetry Database Coordination
Test Bed for Verification

3. Division of Responsibility
GLAST Mission
Coordinate with spacecraft vendor EGSE
LAT
Coordinate EGSE flow across subsystems
ELECTRONICS
EGSE hardware (except for workstation) & front end software
I&T
EGSE workstation, workstation software and support. I&T test, analysis, visualization, and script software
SAS
LAT event reconstruction software
IOC
Ultimate customer
Elect.
I&T
Mission
LAT
IOC
SAS
ONLINE

4. EGSE Deliverables (Electronics + I&T Support)
Hardware/Software support for various incarnations of I&T test-stands
Engineering Model 1 (EM1). Delivered 12/02.
Engineering Model 2 (EM2). Due 8/03.
Calibration Unit (CU). Due 2/04
Flight Unit (FU). Due 5/04.
Test-stand system composition
Infrastructure (workstations, networking, crates, etc.)
Test executive
Graphical User Interfaces (GUIs)
Databases and tools
Data analysis tools
Data archiver
Test procedures
Code management, release control and distribution
Remote debugging tools

5. Migration EM-1: No FSW beyond hardware drivers
Will be used for the EM test (cosmic rays, Van de Graaff photons)
EM-1+: EM-1 plus additional code from FSW
FSW for commanding, telemetry and housekeeping
EM-2: Development platform for multi-tower support
Embedded systems run FSW code
Commanding will be done through a more realistic dictionary
Event format changes from TEM/AEM output to FSW filter output
Test bench scripts will still be able to be run
CU: Four tower system used for the Beam Test at SLAC
Limited ACD contribution
Evolution of EM-2
Will need to handle external sources of data
1553, SSR and SIS communications not required to satisfy test
FU/LAT: The complete system
Communications through SIIS (1553 and SSR), and test point.
Will need IOC/MOC-like interface.
Test bench scripts will still be able to be run (via test point).

6. Subsystem I&T Test-stand Requirements and Schedule
Type
Number of instances
Release date
Development support
EM1 4
Done
Subsystem support
2 CAL+ 3 ACD +
4 TKR
Integration Testing 1
SLAC DAQ hardware development
Flight Software Testbed
EM2
5/03
Calibration CU 2
3/04
Flight Unit I&T FU
10/04
EM1 includes TEM interfaces (LAT-COMM cards)
EM2/QU/FU include SIS (Spacecraft Interface Simulator) and IPS (Instrument Power Supply)

7. EGSE & Online Software Real-time system
Embedded processors running the VxWorks RTOS
Data acquisition and control by Trigger & Dataflow system
Gathering of Housekeeping quantities
3rd party data acquisition, e.g., during beam tests
LAT Test Executive (LATTE) developed using Python, Qt and XML provides:
Configuration management
Commanding
Online data acquisition, archiving and distribution
Persistent data stored in FITS files
Data quality and Housekeeping quantity monitoring
Data visualization and analysis
HippoDraw: a visualization tool.

8. Main Dataflow Ethernet
EM1 EGSE Configuration
Electronics/Online
Online
Workstation
Test Exec
Configuration
Commanding
Telemetry
Event Processing
Monitoring
Visualization
Data base
Message logger
Alerts
Electronic log
Subsystem/simulator
Back door debug RS-232
Subsystem
(or simulator)
Central
Database
VME Chassis
CPU
Commanding
Telemetry
Monitoring
Hardware Drivers
AEM/TEM
WAN
Main Dataflow Ethernet
Ethernet
LAT-COMM
External Trigger
Ethernet Router
and Firewall
DC Power
External Hardware

9. Testing LAT System: Tower EGSE
LCB: LAT Communication Module
Transistion-card: Trigger Module
Power-PC Processor
Flight Software
TEM DAQ Assembly
Tower Power Supply Assembly
(1.5V/2.5V/3.3V/ 0-100V/0-150V)
28-V Power Supply
Processor: Motorola Power-PC
Flight Software
PMCIA LAT Communication Board for
LAT Communication
Transition Board
Trigger
TEM DAQ Assembly
TEM Power-Supply Assembly
28-V Supply
LAT-TD-00861

10. GASU Based Configuration (EM-2)
T&DF System (LAT)
EGSE
ACD or
Sensor
Simulator
EGSE Crate
CPU
LCB
WAN
GASU
28 V Supply
Central
Database
EBM
VME
AEM
GEM
Online
Workstation
TEMs
Firewall
Developmental configuration (subsystem hardware, software and system software) which has a GASU at its core. Baseline configuration leading to the Beam test (CU configuration.
CAL, TKR or
Sensor
Simulator
SLAC

11. Beam Test (CU) Configuration
T&DF System (LAT)
EGSE
ACD or
Sensor
Simulator
EGSE Crate
CPU
LCB
WAN
GASU
28 V Supply
Central
Database
VME
EBM
AEM
GEM
Online
Workstation
TEMs
Firewall
Auxiliary contributor is for contribution 3rd party data (e.g., ESA reflective memory, etc.) to the LAT event data. This idea has not been signed off on with all concerned.
External Data
CAL, TKR or
Sensor
Simulator
CPU
LAT-COMM
External
Hardware
SLAC
VME

12. LAT Assembly Configuration
T&DF System (LAT)
EGSE
Spacecraft simulator
ACD or
Sensor
Simulator
SIU
CPU
Discretes
1553
1553
WAN
GASU
LCB
28 V Supply
Central
Database
EBM
AEM
SSR
3 EPUs
GEM
CPU
Online
Workstation
LCB
TEMs
Firewall
This configuration is used during LAT assembly when parts are constantly being added and tested during each step. Grayed out parts are attached last. (Animation should maybe show them becoming non-grayed out). Software on the SIU and EPUs is Flight Unit level. This configuration is used for Thermal Vac at NRL with all the grayed out items present.
EGSE Crate
Test Point on LAT EMI Skirt
CAL, TKR or
Sensor
Simulator
CPU
LCB
SLAC

13. Complete Flight Unit Configuration
T&DF System (LAT)
EGSE
SSR
1553
Discretes
Spacecraft simulator
ACD or
Sensor
Simulator
SIU
CPU
1553
WAN
GASU
LCB
28 V Supply
Central
Database
EBM
AEM
3 EPUs
GEM
CPU
Online
Workstation
LCB
TEMs
Firewall
This is the final validation configuration prior to shipment to the spacecraft vendor. The EGSE crate can be added to assist in debugging this configuration as necessary.
EGSE Crate
Test Point on LAT EMI Skirt
CAL, TKR or
Sensor
Simulator
CPU
LCB
SLAC

14. FU On-Orbit Configuration
T&DF System (LAT)
Spacecraft
ACD
SIU
CPU
Discretes
Central
Database
1553
1553
WAN
GASU
LCB
28 V Supply
EBM
AEM
SSR
3 EPUs
GEM
Firewall
CPU
LCB
TEMs
IOC
Workstation
Test Point on LAT EMI Skirt
(Flight cover installed -Green Tag item)
CAL
and
TKR
MOC
SLAC

15. Command and telemetry Database Coordination
The command and telemetry database must be coordinated between FSW, I&T and IOC.
IOC will build upon and maintain the software produced by I&T.
The Schema describing commands and telemetry will written in a meta language (TBD, e.g., XML or MySQL)
Schema design will be driven by the details of the ITOS and Astro RT data bases. We will have the ability to translate to either.
The choice of META language may be influenced by the ease of creating/changing/maintaining the data base.
The decision of META language and the database partially populated by IOC CDR.

16. Flight Software Test Bed - EGSE Verification
Full DAQ set with EM2 hardware (identical interfaces and functionality as flight)
Incremental built according to plan (complete test bed Feb04)
All DAQ modules including 16 TEM’s
TKR and CAL front-end electronics for 1 tower, front-end simulator boards for other 15 towers
Harness like flight
Full set of ACD EM2 electronics
Spectrum Astro SC simulator
TKR and CAL Electronics Simulators
DAQ electronics module (DAQ-EM)
Power-supplies for tower electronics
Global-Trigger/ACD-EM/Signal-Distribution Unit*
3 Event-Processor Units (2+1 spare)
Event processing CPU
LAT Communication Board
Spacecraft Interface Unit
Spacecraft Interface Board (SIB): Spacecraft interface, control & data
LAT control CPU
LAT Communication Board (LCB): LAT command and data interface
Power-Distribution Unit (PDU)*
Spacecraft interface, power
LAT power distribution
LAT health monitoring
12 ACD Electronics Cards
Spectrum Astro Simulator
LAT EGSE

17. Extra Slides

18. Number of Registers per Block
Quantities (1)
7 x 32-bits 4
GCCC
Calorimeter Cable Controller
18 x 32-bits 1
GTIC
Trigger Interface Controller
5 x 64-bits
1728 = 72 x 24
GTFE
Tracker Front-End ASIC
2 x 64-bits
72 = 8 x 9
GTRC
Tracker Readout Controller
6 x 32-bits 8
GTCC
Tracker Cable Controller
3 x 16-bits
192 = 16 x 12
GCFE
Calorimeter Front-End ASIC
8 x 16-bits
16 = 4 x 4
GCRC
Calorimeter Readout Controller
GTEM
Tower Electronics Module
Number of Registers per Block
Total Number per TEM
TEM Functional Block
Totals:
~2000
~10000

19. Number of Registers per Block
Quantities (2)
11 x 16-bits
216 = 18 x 12
GAFE
Calorimeter Front-End ASIC
43 x 16-bits 12
GARC
Calorimeter Readout Controller
5 x 32-bits 1
GAEM
ACD Electronics Module
Number of Registers per Block
Total Number per AEM
AEM Functional Block
Totals:
~200
~3000
1 LAT = 16 TEMs + 1 AEM + 1 GEM
= ~ ~ few registers
= ~ registers

20. Multi-Tower and ACD System EGSE (EM2)

21. Transition Board

22. DAQ EGSE to support ACD FREE

23. Event Building/CPU Communications
LAT
GASU
20 Mbps
GLT
20 Mbps
AEM
20 Mbps
Tower 0
20 Mbps
?? Mbps
Tower 15
SSR
20 Mbps
160 Mbps
EPU 0 Tx
EPU 0 Rx
20 Mbps
160 Mbps
EPU 1 Tx
EPU 1 Rx
20 Mbps
160 Mbps
SIU Tx
SIU Rx

24. GASU SIU GASU EPU EPU CRU Command/Response RAD750 cPCI SIB LCB EB
? x ? bit registers
PDU
TEM0
cPCI
SIB
TEM1
TEM2 . .
LCB
TEM15 EB
31 x 32 bit registers
EPU
Event Builder
RAD750
SIU In
SIU
EPU 0 In
cPCI
EPU 0
GEM
(SIB)
EPU 1 In
EPU 1
22 x 32 bit registers
17 x 64 bit registers
19 x 96 bit registers 1 x 112 bit register
LCB
Merge
SSR
EPU
RAD750
AEM
cPCI
(SIB)
GEM
LCB
TEM0
Combinatoric Logic
TEM1
Event Data
TEM2
Event Data Fragments
Command/Response . .
Trigger Data
TEM15
Trigger Data

25. T&DF Overall Architecture (not accurate)
Tower Electronics Module
Interconnect Function
Event Processing Unit
Spacecraft
Tower PWR Mgt 16 ~4 P C I B U S
Event Builder C O N T R L
HSK/LRS
Tower Front End Electronics
TKR
TKR ASICS
Processor
CAL
CAL ASICS 1
CPU I/O
Trigger Primitives
ACD Front End Electronics
ACD Electronics Function
Global Trigger Function
Spacecraft Interface Unit
Tower PWR Mgt
DAQ PWR Mgt C O N T R L C O N T R L
HSK/LRS
HSK/LRS P C I B U S ~4
CPU I/O
ACD
ACD ASICS
TRG FIFO
LAT I/O
1553
TRG Configuration
Processor
SSR
Trigger Primitives
Trigger Logic
Spacecraft I/O
Discretes
Key
Trigger Primitives:
Event Data:
Configuration/Housekeeping/Low Rate Physics Data:
Trigger Message:
All event fragments:
Command, Configuration and Control:

26. Hardware hierarchy

27. Software hierarchy Tower Electronics Module
AntiCoincidence Detector Electronics Module
Global Trigger Electronics Module

28. Run Control State Diagram
Reset
Stopped
Running
Paused
Setup
Teardown
Start run
Pause
Stop run
Stop
Resume

29. Run Control

30. HippoDraw Views (1)

31. HippoDraw Inspector

32. Housekeeping Monitoring

33. Message Logger

34. Block Diagram Tower EGSE

35. Read Schema
simpleTemschema.xml read
GTEM 0, GCCC 3, GCRC 0 selected

36. Write Schema
GCCCs for TEM 0 added
New GLAT, TEM 0 added

37. Write Schema
GCRCs for GCCC 0 added
GCFEs for GCCC 0, GCRC 0 added

38. Software block diagram
Workstation (NT, Python, etc.)
Embedded System (VxWorks)
Disp.
tools
Command
Client
Command
Server
Network
(LAN or 1553)
Script
Execution
Engine
Network
Interface
Network
Interface
Hardware Interface
Processing
Data
Logger
Event Data
Client
Event Data
Server

39. System Block diagram Ethernet Debug LAT Online “IOC” CCSDS packets
Power
Discretes
Analogs
SSR
1553
“MOC”
CCSDS
packets
Spacecraft
Interface
Simulator
MOC simulator

40. Command Model Online/EGSE Test stand/Instrument Command Request
Dispatch
Raw Cmd Encoder
Raw Cmd Decoder
Raw
Command
Packet
Raw
Command
Packet
Raw to CCSDS
CCSDS to Raw
“IOC”
CCSDS
packets
Open CCSDS
Command
Packet
Open CCSDS
Command
Packet
Open
Restricted
Obfuscator
Deobfuscator
“MOC”
CCSDS
packets
NDA/ITAR
Command
Packet
NDA/ITAR
Command
Packet

41. Telemetry Model (1)
Test stand/Instrument
Online/EGSE
TEM
Raw
Data
Packet
Raw
Data
Packet
Event Data
Server
Event Data
Dispatch or
AEM
Only one TEM or AEM allowed in the system at a time

42. Telemetry Model (2)
Test stand/Instrument
Online/EGSE
TEM
Raw Data
Filter (EPU)
Event
Data
Packet
Event
Data
Packet
Event Data
Dispatch …
AEM
Multiple contributors (TEMs, AEM, GEM, filter statistics, etc.) allowed

43. Telemetry Model (3)
Test stand/Instrument
Online/EGSE
TEM
Raw Data
Filter (EPU)
Event Data
Compression
Event Data
Decompression
Event Data
Dispatch …
AEM
CCSDS
Encoding
Telemetry
Data
Packet
Telemetry
Data
Packet
CCSDS
Decoding
Multiple contributors (TEMs, AEM, GEM , filter statistics, etc.) allowed
Development for EM-2
Will also be used for the CU beam test

44. EGSE: Front-End Data Simulator
System uses 9 PC’s
8 PC’s for 16 TEM’s
1 PC for ACD
Data transported to towers via high-speed data link; PCI bridge to local bus on simulator
Data Simulators interface to TEM like CAL and TKR sub-system electronics
CAL and TKR simulator board identical except code in FPGA’s
Patch cable connect simulator to CAL and TKR TEM connectors
Can operate TEM or LAT with data generated from simulations
Data simulator board in layout

45. Verification & Test: Spacecraft Interface
Use Spectro-Astro provided Spacecraft Instrument Interface Simulator (SIIS)
Power
Manual off-on switch
Control & Data Handling (C&DH)
MIL1553
Science Interface (LVDS)
1-PPS timing signal (LVDS)
GBM GRB Candidate signal (LVDS)
Discretes (CMOS)
Analog Monitoring
Present Plan is for SIIS to only provide
primary interface
can’t test prim-redundant interface response
Timing accuracy of 1 PPS interface not sufficient to test timing interface performance
Work in progress
LVDS: Low-Voltage-Differential-Swing signaling

46. I&T Schedule Overview EM test March/April 2003 through September 2003
EM-1+ FSW coming August 2003
CDR
May 2003
SIIS (Spacecraft Instrument Interface Simulator)
April 2003
CU beam test
April/June 2004
FU/LAT integration & Test
June 2004/January 2005
Environmental testing at NRL
February/May 2005
Ready to ship
May/June 2005