Electrical Ground Support Equipment Verification Test Support. EGSE Verification Test Support

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1 Electrical Ground Support Equipment Verification Test Support Tom Leisgang Orbital Network Engineering T. Leisgang 1

2 EGSE Functions Provide common infrastructure Command and control, including test procedures Telemetry acquisition, archive, and distribution Health, status, and data quality monitoring Support data visualization tools Support subsystem engineering displays and EGSE Support subsystem development Trigger & dataflow system Flight software testbed ACD, CAL, and TKR subsystems I&T Support integration and test Verification Testing Qualification/Calibration Unit I&T Subsystem receiving inspections LAT I&T including environmental testing Mission Systems Integration & Test T. Leisgang 2

3 EGSE Requirements EGSE requirements are traceable to several sources LAT Trigger & Dataflow Specification LAT Flight Software Performance Specification LAT IOC Performance Specification LAT Performance Specification LAT Verification Plan LAT Integration & Test Plan Subsystem Integration & Test Plans LAT IOC Verification Plan SI-SC Interface Requirements Document, 433-IRD-0001 GLAST Mission Assurance Requirements, 433-MAR-0001 EGSE must support testing to verify requirements T. Leisgang 3

4 Dataflow Performance Verification Matrix Verification Types: T: Test; I: Inspection; A: Analysis; D: Demonstration; Test /Measurement Types: F: Functional; P/F: Pass/Fail; P: Performance; Ti: Time; DR: Data Rate; An: Analog; Dg: Digital T. Leisgang 4

5 Dataflow Performance Verification Matrix Item Description Origin Verification Test Type 7.4 Science Housekeeping Readout 7.5 Science Housekeeping Bit Rate ACD Rate Counter Maximum Bit Rate ACD Rate Counter Average Bit Rate CAL Rate Counter Maximum Bit Rate CAL Rate Counter Average Bit Rate The readout of the science housekeeping rate counters shall be initiated by a command signal. The counters are reset via a Reset command and latched in a buffer on a Latch command. Readout is initiated via a Readback command. Since these are broadcast commands, the instrument counters can be reset and latched synchronously. The DFS shall have the capability to read out the science rate counters up to maximum rate of 100 Hz. The DFS shall have the capability to read out the ACD discriminator and supertile rate counters at a bit rate of (number of counters, TBR) * 16 bits * 16/second = y kbps The DFS shall have the capability to read out the ACD discriminator and supertile rate counters at a bit rate of (number of counters, TBR) * 16 bits * 1/second = y kbps. The DFS shall have the capability to read out the CAL diagnostic rate counters at a bit rate of 16 modules * 16 bits * (number of counters, TBR) * 1/sec = y kbps (TBR) instrument maximum. The DFS shall read out the CAL rate counters at an average bit rate of 16 modules * 16 bits * y counters * 1/64 seconds = y kbps assuming one sample every 64 seconds. Metric TRGlevel4_1 T P Ti TRGlevel4_1 T P DR TRGlevel4_1 T P DR TRGlevel4_1 T P DR T. Leisgang 5

6 Dataflow Performance Verification Matrix Item Description Origin Verification Test Type Metric TKR Rate Counter Maximum Bit Rate TKR Rate Counter Average Bit Rate Housekeeping Data from the DFS Time Distribution to DFS The DFS shall have the capability to read out the TKR rate counters at a maximum bit rate of 16 towers * 16 bits * 2 counters * 16/sec = 8 kbps (TBR) instrument average. The DFS shall read out the TKR rate counters at an instrument average bit rate of 16 towers * 16 bits * 2 counters * 1second = 512 bps assuming one sample per second. TRGlevel4_1 T P DR TRGlevel4_1 T P DR The DFS shall transfer the housekeeping data packet. The DFS shall receive a time message that gives Global Positioning System (GPS) time at the 1 Pulse Per second (PPS) signal. This message will be issued 50 to 100 ms (TBR) after the transition of the 1 PPS signal Ancillary Data To DFS The DFS shall receive ancillary data from the Spacecraft (SC) Attitude The DFS shall receive from the SC a time-tagged attitude vector from the SC Attitude Control Subsystem (ACS) at the attitude control loop rate of 5 Hz (TBR) Orbit Position Vector The DFS shall receive the SC-determined orbit position data Observation Identification (ID) Ancillary Data Downlink Other ancillary data, such as observation IDs that are generated on the ground, shall be received by the DFS in the data field of commands sent by the SC. The DFS shall include the SC ancillary data received via the command/data bus in the telemetry data stream. TRGlevel4_1 T P Ti T. Leisgang 6

7 Dataflow Performance Verification Matrix Item Description Origin Verification Test Type 9.3 Redundancy Control The DFS shall control whether the primary or secondary power supply is used for the electronics modules with the exception of the SIU. 9.4 Subsystem Electronics The DFS shall control the on/off state of the subsystem electronics, i.e. the 16 CAL, 16 TKR and 12 ACD front-end electronics, independently. 9.5 Subsystem Electronics The DFS shall operate the rest of the system while part of the front-end electronics is powered off. 10 Instrument Health Housekeeping Requirements The DFS shall provide housekeeping monitors for the instrument Temperature Monitors The DFS shall provide temperature monitors for the instrument ACD Temperature Monitors CAL Temperature Monitors TKR Temperature Monitors DFS Temperature Monitors Power Supply Temperature Monitors Electronics Board Temperature Monitors Grid Temperature Monitors The DFS shall monitor the temperature of the ACD at 12 (TBR) places, one for each front-end board. The DFS shall monitor the temperature of each CAL module at 4 (TBR) places (one for each front-end board) The DFS shall monitor the temperature of each TKR at 8 (TBR) places (one for each cable). The DFS shall monitor the temperature at 16 (TBR) locations within the DFS and Grid. The DFS shall monitor the temperature of each power supply. The DFS shall monitor the temperature of each electronics board within the DFS. The DFS shall monitor the temperature at 16 (TBR) places on the Grid and other structural elements of the instrument external to the DFS housing. Metric T. Leisgang 7

8 LAT Electronics Subsystems B A B SIU A B LAT Monitor A Pwr B A Clk Data Cmd Reset A / B Spacecraft Bus A Spacecraft Bus B Spacecraft Commands 1553 Databus Status / Readback LAT Commands LAT Communications B A 1 TEM TEM EP EP 5 1 ACD 2 ACD LAT Power Distribution 1 GT 2 GT Global Trigger Communications Power Supply A Power Supply B + = E-Box E-Boxes TEM = Tower Electronics Module EP = Event Processor ACD = Anti Coincidence Detector GT = Global Trigger T. Leisgang 8

9 LAT EGSE Functional Block diagram Subsystem Component Under Test EGSE Breakout Panel Power Temp Digital Serial Electronics Subsystem EGSE Hardware Software Tracker Calorimeter TEM ACD Voltage Current DC Power Bus V DC Power 3.3 V A DC Power 3.3 V D DC Power 1.5 V A DC Power 2.5 V A DC Power 2.5 V D DC Power V Bias DC Power 5 V D DC Power -12 V D DC Power +12 V D Analog Analog - Temp Serial / Digital Drivers SIU Emulator Test System Control S/W Test Executive S/W GT 1553 EPU Emulator EPU Signal Capture & Processing Digital & Timing GT Emulator SIU SLAC Custom TKR/CAL/ DAQ Interface Card Driver TEM Emulator VxWorks T. Leisgang 9

10 EGSE Operational Components DC Power Analog Measurement Voltage, Current, Resistance, Temperature Serial / Digital Communications LAT communications interfaces 1553 Data Bus Emulates spacecraft bus communications Signal Capture & Processing Waveform measurement & analysis Digital & Timing Timing Analysis, LAT discrete commands SLAC Custom TKR/CAL/DAQ Subsystem test signal processing T. Leisgang 10

11 EGSE Software Drivers SLAC custom electronics COTS data acquisition products Interface emulators TEM Global trigger Event processors SIU Test system control software Configuration Script execution Data communications Test executive Test performance Reporting T. Leisgang 11

12 TKR/CAL EGSE Test Configurations Emulates TEM I/F + Power TEM,ACD,EPU GT Emulates SIU, GT + Power Emulates SIU, TEM,ACD,EPU +Power SUI & Housekeeping Emulations: Spacecraft Bus I/F LAT Communications LAT Command & Control T. Leisgang 12