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Under the current processing schedule, MLP-3 (Mobile Launch Platform 3) will be moved into VAB High Bay 3 in early\/mid April ahead of SRB stacking operations \u2014 which are currently baselined to occur in a 20+10 days contingency timeframe beginning in mid- to late-April.<\/p>\n
Following completion of SRB stacking and closeout operations, SRB\/ET mate operations would pick up on May 27 \u2013 16-days after the Tank\u2019s arrival at the Kennedy Space Center.<\/p>\n
Orbiter Endeavour would then rollover from her OPF on June 17 after 108-days of OPF processing for mating with her External Tank.<\/p>\n
Following a week of mating, integration, and vehicle checkouts, Endeavour and the STS-134 stack would then be moved to Launch Pad 39A on June 24 for 30+5 contingency days worth of pad processing for a July 29th launch.<\/p>\n
According to the 93 page Launch Site Flow Review (LSFR) document \u2013 available for download on L2 \u2013 the current baselined (as of January 19, 2010) Ascent Performance Margin for Endeavour and STS-134 is 577lbs.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2010\/03\/A73.jpg\" "\\"A7\\"")
Additionally, Endeavour\u2019s total weight (with payload and onboard propellant) meets all emergency abort and landing constraints expect for one, the Contingency Return case which would occur after the deployment of ELC-3 to the ISS but before deployment of AMS-02 and any middeck transfers.<\/p>\nFor this case, Endeavour\u2019s weight (with a Forward Center of Gravity case) would be 233,473lbs \u2014 473lbs over the 233,000lbs contingency return weight limit.<\/p>\n
The LSFR document further notes that, in the event of a RTLS (Return to Launch Site) abort, a 185-second ARCS (Aft Reaction Control System) and 25-second FRCS (Forward Reaction Control System) propellant dump would be required to meet RTLS landing CG and weight requirements.<\/p>\n
Similarly, a 120-second ARCS and 65-second FRCS dump would be required for a TAL (Trans-oceanic Abort Landing) abort to meet landing CG and weight requirements.<\/p>\n
In all, Endeavour will carry nine primary payloads during the 12+1+2 day mission.<\/p>\n
These payloads include the AMS-02, the ExPRESS Logistics Carrier 3 (with numerous payloads attached), and a new MISSE (Materials on International Space Station) experiment in Endeavour\u2019s payload bay.<\/p>\n
Riding up on Endeavour\u2019s middeck will be a new GLACIER (General Laboratory Active Cryogenic on ISS Experiment Refrigeration) and CGBA (Commercial General Bioprocessing Apparatus) payload.<\/p>\n
Additionally, Endeavour will carry the now-standard MAUI (Analysis of Upper Atmosphere Injections), RAMBO-2 (RAM Burn Observations-2), SEITE (Shuttle Exhaust Ion Turbulence Experiment), and SIMPLEX (Shuttle Ionspheric Modification with Pulsed Local Exhaust) Payloads of Opportunity which, as the name suggests, will only be performed is conditions and mission timelines allow.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2010\/03\/A46.jpg\" "\\"A4\\"")
Furthermore, Endeavour and her six person crew will also be tasked with two Development Test Objectives \u2014 or DTOs.<\/p>\nThese include DTO 805, Crosswind Landing Performance, and DTO 703, Sensor Test for Orion Relative-Navigation Risk Mitigation (STORRM).<\/p>\n
For Endeavour\u2019s 25th and final scheduled flight, the orbiter will utilize LP03 (Left Pod 03) and RP04 (Right Pod 04) for her two Orbital Maneuvering System (OMS) pods, External Tank 137 (which is currently expected to arrive at the Kennedy Space Center on May 11), SRB BI set 144 and RSRM-112 (Reusable Solid Rocket Motor stack 112), and Operational Increment software OI-34.<\/p>\n
LSFR Baseline Modification for Endeavour:<\/p>\n
As with all Space Shuttle missions, Endeavour will undergo a series of evaluations and modifications before her STS-134 mission.<\/p>\n
For this flight, technicians in OPF-2 (Orbiter Processing Facility bay 2) will undertake one final modification to NASA\u2019s youngest orbiter, as well as three (possibly four) Mission Kit modifications.<\/p>\n
For the only Orbiter modification, a \u201cdedicated power feed to the Fuel Cell H2 (hydrogen) flowmeter [that is] separate from the Cell Performance Monitor (CPM)\u201d will be installed to ensure the protection of power to the CPM during flight.<\/p>\n
This modification adjusts MPCAs 1 and 3 (Mid Power Cell Assemblies 1 and 3) to \u201cutilize spare MPCA pin locations and 1-amp fuses to provide a dedicated power feed to the Fuel Cell H2 flowmeter separate from the CPM to protect against power loss of the CPM,\u201d notes the STS-134 LSFR presentation.<\/p>\n
The existing design feeds power to the Fuel Cell H2 flowmeter and CPM from the same 1-amp fused circuit.<\/p>\n
\u201cSeparation of H2 flowmeter and CPM power feed would eliminate impact to CPM.\u201d<\/p>\n
A loss of power to a CPM during a countdown would result in an automatic launch scrub; likewise, a loss of power to a CPM during flight would \u201c[result] in crew impact for alternate data collection to verify Fuel Cell health.\u201d<\/p>\n
Technicians have been tracking this problem through all three orbiters via inconsistent flowmeter behavior.<\/p>\n
The worst of these behaviors came during the STS-124 flight of orbiter Discovery when a blown out fuse caused a loss of power to a CPM.<\/p>\n
A temporary fix was devised in the form of flying the #1 and #3 H2 flowmeters in a powered down pattern after de-pinning them \u2014 a modification that was flown twice, once each of Discovery (STS-128) and Endeavour (STS-127).<\/p>\n
LSFR STS-134 Mission Kits Modification Baseline Overview:<\/p>\n
In all, three Mission Kit modifications are planned, with the possibility of one additional mission kit modification pending.<\/p>\n
The first modification relates to a change in the IBA boom configuration.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2010\/03\/A55.jpg\" "\\"A5\\"")
For STS-134, the IBA (Inspection Boom Assembly) would be modified to \u201creflect new boom and sensor pack 1 installation changes as well as Orbiter return without Boom,\u201d notes the LSFR presentation.<\/p>\nSince the OBSS (Orbiter Boom Sensor System) will be transferred to the ISS at the end for Endeavour\u2019s docked mission, the IBA will be modified during this flight to an EIBA (Enhanced Inspection Boom Assembly) that is \u201cmore compatible\u201d with the SSRMS (Space Station Remote Manipulator System).<\/p>\n
The EIBA will have a modified grapple fixture interface and numerous, minor hardware modifications to better support long-term on-orbit stay.<\/p>\n
For part of this modification, two crewmembers during one of the three STS-134 EVAs (spacewalks) will replace the standard Shuttle EFGF (Electrical Flight Grapple Fixture) from the grapple end of the OBSS with a standard ISS PDGF (Power Data Grapple Fixture).<\/p>\n
The second baselined Mission Kit mod is for the STORRM (Sensor Test for the Orion RelNav Risk Mitigation).<\/p>\n
This DTO is designed to \u201ctest the Vision Navigation Sensor (VNS) and Docking Camera planned for Orion\u201d and will be tested during Endeavour\u2019s docking and undocking to\/from the ISS.<\/p>\n
The modification here provides for a revision to the \u201corder blanket installation and MECSLSI (Mission Equipment Cargo Support Launch Site Installation) plan.\u201d<\/p>\n
Finally, the last baselined Mission Kit modification relates to the Payload Cable Harness.<\/p>\n
\u201cPayload Cable Harness modification for ROEU (Remotely Operated Electrical Umbilical) and AMS-02 updates MECSLSI to include two longer ELC-3 ROEU Power\/Control cables to allow the ELC Sill Latch cables to be mated further forward on the starboard sill,\u201d notes the LSFR presentation.<\/p>\n
In this manner, STS-134 is a unique flight in that all 12 Payload Retention starboard sill location connections are required for the mission. Also, this is the first flight in which 2 ROEUs are required on the same side of the payload bay since both ELC-3 and AMS-02 require 2 starboard latch connection locations.<\/p>\n
Each ROEU power\/control requires \u201c6 cables for 3 Sill connector locations and ELC3 ROEU power\/control cable lengths are short for 2 available starboard sill connector locations.\u201d<\/p>\n
In short, this modification will lengthen the ELC-3 ROEU power\/control cables and will \u201cmate the ELC-3 Sill Latch cables further fwd to allow for the ELC ROEU Pwr\/Control cable connections on the starboard sill.\u201d<\/p>\n
Finally, the yet-to-be-baselined modification pertains to the IBA.<\/p>\n
\u201cPort LWTSA (Light Weight Tool Stowage Assembly) Cushion modification\u201d will modify the port LWTSA to accommodated the return of the OBSS\u2019s EFGF \u2014 which will be removed as part of the EIBA (Enhanced Inspection Boom Assembly) modification.<\/p>\n
Fit checks were planned for January 2010.<\/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":"
Despite new concerns about the readiness of the AMS-02 (Alpha Magnetic Spectrometer -02) payload to meet the currently targeted July 29, 2010 launch of the STS-134 mission, Space Shuttle Program mangers and flight planners are continuing their efforts to prepare all necessary components for flight on the 133rd Space Shuttle mission. No launch date decision […]<\/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":[3366],"class_list":["post-40849","post","type-post","status-publish","format-standard","hentry","category-news","tag-sts-134"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40849"}],"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=40849"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40849\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=40849"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=40849"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=40849"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}