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Section 25 Lightweight Flexible Solar Array . . . John Lyons EO-1 Lightweight Flexible Solar Array Lead Lightweight Flexible Solar Array (LFSA) Technology Need: Increase payload mass fraction. Description:

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Section 25

Lightweight Flexible Solar Array

. . . John Lyons

EO-1 Lightweight Flexible Solar Array Lead

slide2

Lightweight Flexible Solar Array (LFSA)

  • Technology Need:
  • Increase payload mass fraction.
  • Description:
  • The LFSA is a lightweight photovoltaic(PV) solar array which uses thin film CuInSe2 solar cells and shaped memory hinges for deployment. Chief advantages of this technology are:
    • Greater than 100Watt/kg specific energies compared to conventional Si/GaAs array which average 20-40Watts/kg.
    • Simple shockless deployment mechanism eliminates the need for more complex mechanical solar array deployment systems. Avoids harsh shock to delicate instruments.
  • Validation:
  • The LFSA deployment mechanism and power output will measured on-orbit to determine its ability to withstand long term exposure to radiation, thermal environment and degradation due to exposure to Atomic Oxygen.
  • Benefits to Future Missions:
  • This technology provides much higher power to weight ratios (specific energy) which will enable future missions to increase science payload mass fraction.

Status:

see upcoming charts

Partners

AFRL, NASA/LaRC, Lockheed Martin (Boulder Co)

changes since red team review
Changes Since Red Team Review
  • No changes to Verification Matrix
  • No configuration changes
  • LFSA was powered up in idle mode during T/V II hot and cold plateaus
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Special Topic Follow-Up:

LFSA Repair, Modification, and Re-Integration

. . . John Lyons

EO-1 Lightweight Flexible Solar Array Lead

lfsa power interface issues
LFSA Power Interface Issues
  • Post S/C environmental testing and final integration of LFSA with S/C indicated problem with readout of I-V data, which was diagnosed as power up sequence error in software code within the LFSA microcontroller
  • Further examination of power interface logic from S/C to LFSA indicates that a “smart short failure scenario” in LFSA might result in degraded power services (+5V,15V,-15V) to main S/C processor, putting mission at risk.
  • Decision made on 11/24 to modify LFSA power interface to accept unregulated 28V input rather than current (+5,-15V, +15V) interface.
  • Plan developed with LM to modify current power interface and correct microcontroller software:
    • Delta CDR (modified power, re-qual requirements) held Dec 3rd
    • Functional testing with S/C on Dec 20th
    • Environmental requalification (vib, thermal, EMI) Dec 20- Jan 15th
    • Reintegration with S/C on Jan 17th
  • Revised interface allows LFSA microcontroller to be powered up separately and turned off if it causes any problems.
lfsa power interface issues9
LFSA Power Interface Issues

1) Develop and present Delta CDR - Dec 3rd Complete

2) Lockheed Martin to modify LFSA to Complete

accommodate new power interface and

functionally test unit with new

micro-controller software at LM - 12/17/99

3) Swales to modify and test S/C harness Complete

to new interface (before Dec 16)

4) Lockheed Martin to functionally test LFSA Complete

with S/C at GSFC 12/21

5) Lockheed Martin to perform environmental Complete

re-qualification of LFSA at LM and GSFC

(thermal cycle, vibration at LM, EMI at GSFC)

Dec 27- Jan 12

6) Reintegration of LFSA with EO-1 S/C - Jan 13 Complete

lfsa summary
LFSA Summary
  • Recent re-integration and test demonstrated no residual risk to spacecraft
  • No Redbook candidates
  • LFSA ready to fly