Overall Conclusion to Date

• HSP operates as it did pre-launch with no detectable degradation. Physical appearance is as it was with no change, except for the nominal, anticipated creep of the Bray oil rivet lubricant.

Tests and Inspections Performed

Visual inspection & photographic documentation

• The exterior surfaces appeared to be in good condition with no damage or degradation. (One of the latch fittings was later nicked during installation/removal from the HFMS). The Bray oil migration (creep) was no more extensive than previously observed before launch. Interior condition of the HSP was excellent.

Close inspection and photos of all filters

• No changes from pre launch condition.

Contamination inspection and tests

• Ref: HST FSM Contamination Report P442-0667 and Colony memo to Greenberg dated 1/31/94.

• Swab sample taken 1/25/94 from HSP top found traces of oxides and barely detectable hydrocarbons.

• Tape lifts from HSP top & side were similar to pre-launch findings.

Electrical Interface Tests

• A complete verification of the electrical interface (EICIT and IVT) was performed, including redundant units. All results were nominal.

Functional Tests (including thruput)

• A complete set of functional tests were run using the HSP EGSE. All functions were nominal and in agreement with pre-launch results. The redundant electronics were also tested for the first time since pre- launch functional tests were completed (The redundant electronics were never exercised during the mission.) A thruput test was performed using a simple "flat" field source, and no changes were observed.

Flaw Detection Tests

• Ref: Lugmayer Associates Report #LAJ-1850-94.

• Tests conducted 4/4/94 to 4/14/94.

• Both eddy current and ultrasonic tests performed to determine if any stress corrosion cracks had appeared in the HSP structure (near the latch fittings) since similar tests were performed before launch. HSP structure is made from 2024 aluminum (a "table 3" material). Tests showed no cracks, and verified features (e.g. repair plug) found in previous testing.

Quarter panel test

• The HSP envelope dimensions and position of the focal plane were measured and verified. No changes noted from pre-flight data.

Ship to UW-Madison

• Before shipment, HSP RIUs and Latches removed, one filter aperture assembly removed for transmission tests.

• Shipped from GSFC to UW Space Astronomy Lab for further testing. Chamberlin Hall freight elevator failure marooned the HSP on the sixth floor before it was removed from the shipping container. Activities on hold.

Plan

• Remove HSP from shipping container (must install hoist on 6th floor).
• Move to SAL cleanroom.
• Remove tape samples from front bulkhead for GSFC contamination analysis.
• Complete postflight testing and calibration.
  • Verify polarizer orientation.
  • Perform thermal sensor calibration.
• Perform subsystem tests.
  • Test electronic boxes: functional, temperature.
  • Detector testing: VIS tube investigation.
  • Selective internal visual inspection.