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The three hour loading process hasn\u2019t suffered from any issues since two major modifications, the first to the LH2 Feedthrough Connector \u2013 which was sending false Engine Cut Off (ECO) sensor indications during tanking, most notably on STS-122.<\/p>\n
The tanking process involves numerous checks on the health of the tank\u2019s instrumentation\/sensors \u2013 via what are called SIM checks, which switch the sensors on and off (DRY and WET) and checks the health of the sensors\u2019 voltages.<\/p>\n
The other problem related to unacceptable levels of leakage from the Ground Umbilical Carrier Plate (GUCP), which was solved by a change of the flight seal design, and modifications to the alignment of the GUCP\u2019s feet on the tank. No tanking related issues were recorded on the previous launch \u2013 STS-129.<\/p>\n
During the latter stages of the countdown, an issue with the Cabin Pressure \u2013 which was registering a very high 125 psi reading, required engineers at the pad to check an associated regulator.<\/p>\n
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Go for tanking was given by the Mission Management Team (MMT) pending the engineers clearing the pad after working on the pressure issue \u2013 ultimately delaying tanking by around 30 minutes. The IPR on the pressure issue was resolved and closed as a constraint, as tanking proceeded to plan \u2013 with good ECO sensor SIM checks. The only other IPR (62) related to a SRB issue, which was minor and soon cleared.<\/p>\n
Once the crew has ingressed the orbiter, weather concerns with cloud cover led to an initial decline in the probability for a constraint to launch of 40 percent, before later rising to 70 percent no go. This resulted in a scrub during the polling to come out of the T-9 minute hold.<\/p>\n
A new article will follow later on Sunday for the second launch attempt. Refer to the live update pages for a review of the up-to-the-second updates for attempt 1.<\/p>\n
STS-130 Specific Articles: http:\/\/www.nasaspaceflight.com\/tag\/sts-130\/<\/p>\n
Modified ET-134:<\/p>\n
Despite the shuttle program only having five more launches remaining, the efforts to improve the safety of the vehicle have never stopped and remains as vigorous as ever. The latest improvements can be seen via the 50+ STS-130 Flight Readiness Review (FRR) presentations acquired by L2.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2010\/02\/A44.jpg\" "\\"A4\\"")
One such example is the ET presentation by Lockheed Martin, which included an overview on the final stage of structural improvements that have been made to Endeavour\u2019s tank.<\/p>\n\u201cFinal phase of plan for structural productivity enhancement design changes implemented. Material substitution on Intertank thrust panels and LO2 tank aft ogive,\u201d noted the FRR presentation. \u201cFriction Stir Weld (FSW) implemented on remainder of LH2 (barrels 1 and 2 ) and LO2 tank barrel welds. LO2 tank barrel weld land optimized to minimize structural weight.\u201d<\/p>\n
Ironically, the switch to FSW production of the tanks was mainly part of the Michoud Assembly Facility (MAF) preparations for the fabrication of Ares I and Ares V stages \u2013 which are currently both cancelled via the President\u2019s FY2011 budget proposal.<\/p>\n
The successful use of this technology on the shuttle external tank \u2013 along with an improvement to the materials used \u2013 was also a positive for the potential to extend the shuttle program via the new tooling now in place. That too is ruled out in the budget proposal.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2010\/02\/A24.jpg\" "\\"A2\\"")
\u201cUse of Al 2219 (original ET pressure vessel material) in place of Al 2195 (SLWT (Super Light Weight Tank), ET-96) to mitigate welding repair issues on complex curvature structure LO2 tank Aft Ogive,\u201d added the FRR overview. \u201cReplace Al 2219 with Al 2297 on Intertank thrust panels same configuration.<\/p>\n\u201cImplementation of FSW on all LO2 and LH2 tank barrel welds. Overall design and verification approach accepted by multiple technical panels and industry experts and reviewed at combined PDR\/CDR (Prelim and Critical Design Reviews). All previously implemented changes successfully flown.\u201d<\/p>\n
Noting the changes in greater depth, the presentation notes gives a specific overview of the thrust panel changes since STS-129\u2019s ET-133 \u2013 which has resulted in additional mass margin on other areas of the tank.<\/p>\n
\u201cDescription of Change: Intertank +\/-Y thrust panel material substitution to reduce structural weight (~7 percent, ~226 lbs total). Was: Al 2219, Now: Al 2297. Al 2297 material has lower density (7 percent) with similar mechanical properties.<\/p>\n
\u201cHardware geometry and thicknesses unchanged. No change to TPS (Thermal Protection System foam), primer configuration, process or acceptance testing.<\/p>\n
\u201cBackground: Al 2297 aluminum-lithium (Al-Li) material similar to Al 2195 alloy used extensively on ET pressure vessel components. Al 2297 material originally developed and successfully implemented on military aircraft in non-welded applications.<\/p>\n
\u201cUsed on F-16 since 1995. ET Project performed testing to characterize properties for ET design conditions. Results used to establish lot acceptance test requirements for mechanical and fracture properties.\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2010\/02\/A34.jpg\" "\\"A3\\"")
Buying the mass savings from the thrust panel changes, additional structural improvements were added to the Ogive gore panels \u2013 which marked the final improvement that will be made to the tank, pending new issues over these final five flights.<\/p>\n\u201cDescription of Change: Substituted Al 2219 in place of Al 2195 for all twelve (12) aft ogive gore panels. Minimum gage strength critical gores optimized to reduce structural weight (6 gores @ +\/- Z axes). Was: Al 2195-T8 chem-milled\/stretch. Now: Al 2219-T87 chem-milled\/stretch,\u201d added the presentation.<\/p>\n
\u201cAl 2219 material has higher density (5 percent) with lower tensile yield and ultimate strengths (8 percent ~+226 lbs total). Stability critical gore membrane thickness unchanged (6 gores @ +\/- Y axes).<\/p>\n
\u201cWeld land thickness unchanged. Same process as LWT with increased thickness retained. No change to TPS configuration, process or acceptance testing.\u201d<\/p>\n
\u201cBasis for Certification: Design change verified by combination of acceptance proof test and analysis. Stress analysis confirms adequate structural margins for critical failure modes. Hydrostatic acceptance proof test demonstrates a minimum of 120 percent design limit load for strength critical membranes \/ welds and verifies 4 mission life requirement.<\/p>\n
\u201cTPS bondline delamination failure mode test-based verification unchanged (TDFS > 1.25 requirement). Maximum substrate mechanical strain reduced due to increase in minimum membrane thickness.\u201d<\/p>\n
Overall, the TPS design configuration for this tank is the same as previous flight. The In Flight Anomaly Review (IFA) for STS-129\/ET-133 flight performance assessment noted nominal performance observed for all TPS applications in critical debris zone.<\/p>\n
STS-129\u2019s tank was the first flight of the redesigned LH2 Ice Frost Ramp base closeout (return to NCFI 24-124). Only one IFA declared for the Intertank TPS losses on the Z side of the tank \u2013 which held no threat to the orbiter. These intertank acreage losses are consistent with the events noted on ET-131\/STS-127.<\/p>\n
TPS NDE (Non Destructive Evaluation) assessments on ET-134 were also noted as successfully completed, with all indications within expected performance and previous observations. All potential divot masses are predicted to be less than 0.010 lbm prior to 135 seconds into ascent, which would not cause damage to Endeavour.<\/p>\n
L2 members<\/em><\/em>: Documentation \u2013 from which the above article has quoted snippets \u2013 is available in full in the related L2 sections, now over 4500 gbs in size<\/em><\/p>\n","protected":false},"excerpt":{"rendered":"
Clouds over the Kennedy Space Center (KSC) have scrubbed Endeavour\u2019s launch by 24 hours. Earlier, tanking was delayed tanking by 30 minutes to allow engineers to clear the pad after working on a cabin pressure issue, prior to a smooth countdown. Meanwhile, External Tank (ET-134) \u2013 which will be flying with Endeavour on STS-130 \u2013 is sporting […]<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"","ping_status":"","sticky":false,"template":"","format":"standard","meta":{"_acf_changed":false,"inline_featured_image":false,"footnotes":"","_links_to":"","_links_to_target":""},"categories":[2],"tags":[9021,9183],"class_list":["post-40875","post","type-post","status-publish","format-standard","hentry","category-news","tag-et","tag-sts-130"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40875"}],"collection":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/users\/1"}],"replies":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/comments?post=40875"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40875\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=40875"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=40875"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=40875"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}