Verification Process

1
Section 7 Verification
. . . Mark Perry EO-1 Spacecraft Systems
Engineer, Swales Aerospace, Inc.
2
Verification Agenda

• Verification Matrix (Special Topic 7A and RFA
  4.4)
• Satellite Environmental Test Flow
• Summary of Satellite and Component Test Time
• Verification Since the Red-Team Review
• System tests CPTs, functionals, aliveness
• Thermal Balance/Thermal Vacuum
• Simulations
• Remaining verification
• Alignment
• Mass Properties
• Simulations and system tests

3
As Run Final System Level Spacecraft
Verification (as conducted) Note Shaded areas
indicate change from Red Team Review.
7 - 3
7 - 3
7 - 3
4
Spacecraft Verification Flow
5
Projected Power On Time
6
Pre-TV CPT

• Held June 2000
• Post-WARP re-integration
• Complete, thorough test of the WARP
• Verified all WARP functions in system environment
• Provided 50 hours of run time on WARP
• Verified changes since December 1999, both S/W
  and H/W

7
Problem Reports for Each EO-1 CPT
8
TV Test Profile
Instrument Contigency Sim (4hrs) All Instrument
DCE (1hr) Power Down CPT0(4hrs) CPT 1(5hrs) (WARP
on) CPT2 (With CTV) (10 hrs) ACS Special Tests
(1.5hrs) CPT 3 (7hrs) CPT 4F(4hrs) CPT 5 (12
hrs) CPT 6 (5 hrs) CPT 7 (without AC) (3 hrs) CPT
8 (without AC) (3 hrs) CPT 11 (5 hrs) (Hyp
bakeout after DCE) CPT 9 (6 hrs) CPT 10 (7
hrs) 1773 Characterization Test (4hrs) Open ALI
Aperture Door (in parallel) ALI Bakeout (3
hrs) Close ALI Aperture Door (1/4 hr) Power Down
(1/4 hr)
Functional Test (12 hrs)(ALI Hyp to outgas) ALI
Warm_Period Terminated CTV S-band Special Test
(2hrs) CTV X-band Test (2hrs) Turn off Hyperion
Outgas heaters All Instrument DCE (AC off) (1
hr) MOC Cont Procs (non-inst) (4hrs) Power Down
(1/4 hr)
Instrument Turn-on Sim, continued (12hrs) MOC
Instrument/WARP Proc Checkout (4hrs) ALI
Decontamination Test (6 hr) Hyperion ASP
Temperature Test (2hrs) M5 Stress Test (5 hrs)
All Instrument DCE (AC off) (1hr) Power Down
(1/4 hr)
External Stim. Verif. Test (6hrs) Roll S/C into
T/V chamber(4hrs) Functional Test (12
hrs) CPT0(4hrs) Depress CPT 1(4hrs) Turn on
Hyperion Outgas heaters (GSE) Power down (4hrs)
40oC
Power Up (1/2 hr) (Prelaunch Aliveness
Test) (WARP on, ALI radiator htrs on)
3 (24 hrs)
13 (80hrs)
9 (28 hrs)
14 (4hrs)
Repress Attach cooling air (1 hr) Functional Test
(12 hrs) ALI latch reset
Transition - Powered off
Transition - Powered off
10 (6 hrs)
Nominal Operations SIM (12 hrs)
15 (6hrs)
Transition - Powered off
Instrument Turn-on Sim, Continued RCS Sec Htr
Test (1hr)
2 (6 hrs)
12 (12 hrs)
4 (13 hrs)
8 (12 hrs)
Ambient
16 (8 hrs)
17 (13 hrs)
0 (16hrs)
1 (8 hrs)
Shroud goes Cold
Power On - Run Launch Config
(12 hrs)
5oC 0oC
CPT Config WARP Power on (Htr proc-1/2hr) CPT2
(w/ CTV 10 hrs) ACS Special tests (1.5hrs) CPT 3
(7 hrs) CPT 4F (4hrs) CPT 5 (12 hrs) CPT 6
(5hrs) CPT 7 (3hrs) CPT 8 (3hrs) AC/Hyperion
Cross Cal Test (2 hr) CPT 11 (5 hrs) CPT 9 (6
hrs) CPT 10 (7hrs) Power off (0.5 hr) 1773
Characterization Test(4hrs) Observatory Power On
(1/2hr)
7 (60 hrs) (5,6,7)
11 (75 hrs)
6
Power Up (1/2 hr) Heater Verification
(1hr) Powerdown Functional Test (12 hr) CTV
S-band Special Test (2hrs) CTV X-band test
(2hrs) Powerdown CPT 0(4hrs) CPT1(5 hrs) (WARP
on) M5 Stress Test (5 hrs) Hyperion ASP Temp Test
(2hrs) All InstrDCE (1 hr) (AC/Hyp Stim) Config
for Instrument Turn On Sim Instrument Turn on Sim
(24 hrs)
5
Note Total Estimated continuous time from start
of 0 (Functional Test) through end of 17
16.0 days (383hrs) - excludes external stim and
roll in time (10 hrs)
9
T/V Results

• All objectives met
• S-Band Anomaly (Special Topic)
• Additional demonstration of nominal operation of
  EO-1 Spacecraft and payloads at temperature
  extremes
• Additional bake-out of ALI and Hyperion
  instruments
• Conclusion
• After S-Band replaced, EO-1 S/C qualified for
  on-orbit operation
• Post Thermal Vacuum Functional Test was nearly
  flawless

10
Plan for Final CPT

• CPT following S-Band Re-integration at Vandenberg
  Air Force Base (VAFB)
• Verify S-band performance in EO-1 system
• Verify full EO-1 performance after shipment
• Scheduled for September 2000

11
Additional Verification

• Alignment
• Final alignment measurement still planned for the
  launch site
• Mass properties conducted just prior to shipment
• Adjustment will be made for missing S-band
• No existing issues
• Electrical testing of deployables at S/C level
  still planned for the launch site
• The remaining S/A deployment will be conducted
  with the flight fuse plugs installed, on the
  redundant side with no EGSE in the loop (at
  launch site).
• The primary HOP path will be verified following
  the deployment to verify actuator motion with the
  flight fuse plugs.
• Remaining testing planned will guarantee system
  functionality on-orbit