Section 1 Overview and SC Status

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Section 1 Overview Spacecraft Status
. . . Mike Cully Swales Aerospace, Inc.
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Overview Agenda

• Scope of Review
• Test Objectives
• Spacecraft Status
• Summary of WOA Problem Reports
• TV Staffing

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Scope Of EO-1 Second T/V TRR

• Demonstrate Readiness of all Subsystems to start
  T/V
• Status of flight hardware and software
• Short description of any changes since the last
  thermal vac test
• Status of open problem reports
• Trending plans
• Work required before pump down
• Status of critical limits in the ASIST database
• Review of any critical procedure steps
• Provide Red Team members an intermediate report
  card on EO-1 status
• To obtain review team concurrence to begin EO-1
  Second T/V

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Test Objectives

• Further demonstrate EO-1 Subsystems in Thermal
  Vacuum following significant de-integration
  activities (LVPC Fuse plugs, ACDS, GPS PCU, IRU,
  WARP, AST)
• Verify post T/V Flight Software Changes at
  operating temperature extremes
• Increase confidence in hardware/software
  integration by substantially increasing Power on
  time for WARP FSW
• Perform CPTs at hot and cold plateaus
• Perform Instrument Turn on Simulation
• Further characterize ALI Outgassing and validate
  on-orbit procedure
• Further develop MOC team capability for normal
  operations
• Verify modifications to heater circuits at system
  level (verification performed at panel level)
• Perform Spectral Registration Comparison for
  Hyperion LEISA/AC (secondary objective)

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Major Configuration Changes for T/V2

• Change to smaller chamber (225) required custom
  designed base plate and new GSE framing for Cryo
  panels and Heater panels
• Static load test performed of new base plate
• Fit check performed of frame during chamber
  certification
• Thermal balance not required. Therefore GSE MLI
  to separate bays not required
• Minimal changes to cabling with exception to
  extensions for GPS, WARP monitor cable (frequency
  shift anomaly) and new Hyperion/AC Spectral
  Registration Comparison cables. Solar Array HOPS
  GSE cables replaced as result of Fusing changes
• Use of Hyperion Heater Control GSE to allow
  better control of test heaters

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Spacecraft Status

• Completed Post WARP integration CPT on May 26th
• CPT went extremely well with minimal issues (AST
  was simulated)
• Completed Launch simulation Day 1 and Day 2 on
  June 6th
• Chamber Certification Completed on June 12th
• Spacecraft on Table, Wednesday June 14th
  (dependant on SADA Cable repair)
• EGSE to be setup around chamber 225 two days in
  advance of S/C on Table
• SRC Materials received and in bakeout
• S/C Roll in projected 6/20/00 (dependant on SADA
  Cable repair)
• Start compress following completion of Functional
  (12 hours) CPT0 (4 hours)

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Pre-T/V II Activities
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WOA Status

• Spacecraft IT WOA Statistics
• Total number generated as 3/24/98 through 6/9/00
  1064
• Total number from 3/28/00 (RTR) 112
• Number Closed out 1020 (96 closure rate)
• Open Work Orders 44 (TBR on 6/09/00)
• Work In Process 4
• Open PRs 16 (6/9/00)
• Future Work 1
• In Close Out Process 23

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Problem Report Status

• Total number generated from 5/1/98 through 6/9/00
  1619
• Total number from 3/28/00 (RTR) 47 (closed
  32)
• Number closed out ITD 1596 (98.6 closure
  rate)
• Number open 23 (TBR on 6/9/00)
• Work In Process 10
• Test verification required 2
• In Closure Process 8
• Red Book Items 3
• WOA 572 One Time Event observed Red Low Limits
  for bus chassis believed to be associated with
  SAS cable problem (GSE)
• WOA 770-20-3 One Time Event Chassis Current
  during EMC Testing
• WOA 837-20-1 One Time Event LVPC Current Red Limit

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Open Problem Reports
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Solar Array Cable Damage

• Background
• During final panel closeout inspections on June 6
  a hair line mark (centered around three o'clock)
  was noticed on the 92 wire bundle that comes out
  of the SADA.
• The hair line mark was further inspected and
  determined to be a cut of the insulation for
  seven wires. The geometry of the cut indicated a
  razor or sharp object. It must be noted that
  this cut was very difficult to see. The location
  of the cut is approximately 0.75 inches off the
  face of the SADA interface which is approximately
  at the start of the bend radius for the cable
  bundle as it is folded up against the Solar Array
  Yoke. This obviously high stress area.
• Under higher magnification it was determined that
  at least three wires had copper showing. In
  addition oxidation has occurred indicating the
  damage was done some time ago.

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Solar Array Cable Damage

• Background Continued
• All seven wires were verified as
  followsgtConnector Pin Description -
  FunctiongtCable Wrap J2 7 Inboard S/A panel
  structural groundgtCable Wrap J2 37 Circuit 11
  (outboard panel fixed string)gtCable Wrap J2 19
  Circuit 4- (Outboard panel, shuntable)gtCable
  Wrap J2 38 Guard (ground wire shield for
  CSS)gtCable Wrap J2 14 GuardgtCable Wrap J2 42
  GuardgtCable Wrap J2 27 Coarse Sun Sensor 2
• There is currently 5 spare wires in this cable
  system