- \n
- STS-134 LIVE UPDATES<\/li>\n
- L2 STS-134 Special Section<\/li>\n
- Click here to Join L2<\/li>\n<\/ul>\n
However, due diligence from the MMT \u2013 based on a recommendation from the Damage Assessment Team (DAT) \u2013 resulted in a call to use the pre-planned placeholder in the flight plan to carrying out a Focused Inspection on a relatively small area of tile damage, located on the starboard side of Endeavour\u2019s belly, between the Main Landing Gear Door and (MLGD) External Tank Door (ETD).<\/p>\n
The damage is historically minor, but due to a need for additional data to be plugged into DAT\u2019s extensive computational analysis models, and less than perfect imagery of the damaged area from Flight Day 3 RPM photography, the FI option is an opportunity to add confidence in what is expected to be full clearance for entry in around 24 hours.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/05\/B3.jpg\" "\\"B3\\"")
The OBSS instrumentation package \u2013 which rides on the end of the 50 foot boom \u2013 consists of visual imaging equipment, the Laser Dynamic Range Imager (LDRI), and the Laser Camera System (LCS). The post-Columbia modification has sensors that can resolve at a resolution of few millimeters, and can scan at a rate of about 2.5 inches per second.<\/p>\nThanks to Neptec\u2019s Laser Camera System (LCS), engineers will gain detailed high resolution images and even a 3D model to provide additional data for their thermal modelling and requirements within hours of the survey.<\/p>\n
The Focused Inspection by the OBSS will be one of its final roles with the orbiter, ahead of the Docked Late Inspection (DLI) which will then result in the Canadian superstar being handed over to the ISS for a role as the Integrated Boom Assembly (IBA).<\/p>\n
Although imagery requirements were refined in real time, baseline Focused Inspection requirements were provided to the MMT a few days ago, providing some procedural outlines into the dual use of two elements of the OBSS package \u2013 namely the LCS and the IDC (Digital Camera).<\/p>\n
\u201cPriority Location 1: Large Tile Damage: Damage ID: D-134-RPM-600_2-001. Location: Starboard side between MLGD and ETD. Location X= 1243.85, Y= 106.07 , Z= 267.33. Sensors: LCS and IDC (with LDRI illumination \u2013 Mode 6, record LDRI),\u201d outlined a DAT procedure document (L2).<\/p>\n
Spaceflight
<\/path>Space Technology <\/path>Spaceflight news subscription <\/path>\n (adsbygoogle = window.adsbygoogle || []).push({});<\/p>\n
\u201cRequested Views Details: 5 total views are required for damage assessment. The first four of the five views should be optimized for IDC imaging, but LCS data is requested as well. Views 1 thru 3 have IDC\/LCS positioned slightly outboard of damage site and pointed inboard (approx 5 degrees off normal).\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/05\/B41.jpg\" "\\"B4\\"")
Those five total views are all the DAT engineers need for their data requirements, which will refine the dimensions of the damage and should result in not just imagery, but 3D computational models, as was seen during STS-118\u2019s Focused Inspection.<\/p>\n\u201cView #1: IDC approximately 6\u2033forward (-X direction) of damage. View #2: IDC approximately even (X direction) with damage. View #3: IDC approximately 6\u201d aft (+X direction) of damage. View #4: IDC positioned directly above the damage pointing to the damage at normal incidence,\u201d added the DAT overview.<\/p>\n
\u201cView #5: LCS positioned directly above the damage pointing to the damage at normal incidence. Need to capture 20\u201d minimum all the way around damage site. IDC is not required for this additional data acquisition.\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/05\/B81.jpg\" "\\"B8\\"")
The robotics operations also require the crew to follow set instructions on ensuring the imagery taken with the Digital Camera on the end of the OBSS is based on the real-time environment, as the Endeavour\/ISS stack race through daylight and darkness on orbit.<\/p>\n\u201cSensor Package 2 IDC Preferred Parameters: Range: 75\u201d for Views 1 thru 4. Boom Motion: Brakes On plus 90 second dwell before beginning data collection (NO EXERCISE). IDC Scenario: \u201cBlack Tile \u2013 Day\u201d and \u201cBlack Tile \u2013 Night\u201d. Crew will select proper file (day or night) per real-time environment,\u201d the requirements added.<\/p>\n
\u201cIDC Lighting: Daylight (direct or earthshine) or LDRI illumination at night (daylight is preferred). IDC FOV: Fixed at 16 deg x 9 deg. Notes: The engineering and imagery teams will be satisfied with a range between 66\u201d and 84\u201d. There is some risk that data collected between 60\u201d to 66\u201d or 84\u201d to 120\u201d will be unsatisfactory for this inspection, but it is better than no data at all (note: assume IDC in these ranges is better than ITVC at 60\u201d).<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/05\/A96.jpg\" "\\"A9\\"")
The expansive overview provided the crew with numerous instructions, notably showing that the use of the digital camera will be IDC tasks are the most involving tasks during the Focused Inspection.<\/p>\n\u201cTasks: Move the sensor package into position. Allow boom motion to dampen out. Pointing can be confirmed by the IDC in \u201cScan Lo-Res\u201d. If IDC view not used, from the LCC GUI, perform a Quickview scan to verify LCS pointing. Downlink the Desktop Downlink,\u201d the overview notes.<\/p>\n
\u201cStop IDC scan to allow LCS ops. Select the appropriate Detailed Area Scan name (as defined above), and press \u2018Start Area Scan\u2019. Restart IDC scan and select the proper scenario file. Activate \u2018Acquire Set\u2019 function. Data will finish collecting in approximately 30 seconds.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/05\/B71.jpg\" "\\"B7\\"")
\u201cActivate the IDC \u2018Scan Lo-Res\u2019 feature. Crew adjusts (moves\/sizes) the exposure window if necessary. Check MCC. Activate \u201cScan Hi-Res\u201d feature. Collect IDC data for 30 seconds. Leave the IDC on and collecting data as the boom is moved into the next view. After completion of data take, stop LDRI recorder and select \u2018Power Off\u2019 to power down the IDC to safe it from accidental exposure to sunlight.\u201d<\/p>\nThe Focused Inspection, which began after some troubleshooting with an associated monitor on the middeck, was completed after 55 minutes.<\/p>\n
A similar overview was also provided for the damage on the Inboard Elevon \u2013 ahead of DAT engineers clearing it, as expected, for entry.<\/p>\n
In fact, with the Reinforced Carbon Carbon (RCC) and all other areas of the orbiter cleared, the final clearance of the Focused Inspection area will result in Endeavour being fully cleared for Entry, pending Docked Late Inspection (DLI) results.<\/p>\n
\u201cFocused inspection CHIT (Documentation) developed to assess damage site: D-134-RPM-600_2-001. IDC and LCS sensors will be utilized. IDC will provide details of the tile cavities. No color,\u201d noted a DAT presentation to the MMT (L2).<\/p>\n
\u201cLCS will provide point cloud data of the tile cavities and surrounding TPS. Surrounding TPS topography req\u2019d for overlay repair option for 600_2-001. Elevon damage site removed from request based on 3D thermal model and command TPS Stress model utilized on assessment. TPS and Stress tile margins remain positive.\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/05\/B51.jpg\" "\\"B5\\"")
The additional data will also provide managers \u2013 via computational models \u2013 with extra confidence the damaged area will still provide \u2013 as if fully expected \u2013 the protection for the underlying structure, with DAT showing numerous images of the inside of the orbiter in the damage location.<\/p>\n\u201cStructure in damage region is aluminum skin with mechanically attached aluminum stringers and structural fittings. Skin panel thickness is 0.146\u201d constant under damage with minimum thickness 0.114\u201d within 6\u201d inches of damage location,\u201d the always-impressive DAT presentation added.<\/p>\n
\u201cMechanically fastened stringers and fittings provide additional 0.08\u201d to 0.23\u201d structure thickness in portions of the damaged region. Yo105 MID Fuselage Longeron and Xo 1249 Wing Spar provide additional structure mass.\u201d<\/p>\n
Although no sub-system components are located on the lower skin in the wing region between Xo1191 and Xo1307 inboard of Yw167, DAT\u2019s recommendation for a Focused Inspection is outlined in their findings.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/05\/B61.jpg\" "\\"B6\\"")
\u201cInitial analysis indicate that if Filler Bar is exposed, Structure temperatures will exceed 350 degrees F. Structural exceedances of 350 degrees F require detailed assessment. Detailed Stress assessment will not be available prior to Focused Inspection.<\/p>\n\u201cMitigations to overcome modeling issues for exposed Filler Bar are continuing in preparation for Focused Inspection. Damage Assessment Team split over value of determining crack tile in damage site. Portion of team recommending Focused Inspection regardless of thermal results. DAT recommends execution of Focused Inspection.\u201d<\/p>\n
With the FI is complete, engineers on the ground got to work on the data within hours, with Mission Management Team (MMT) chair expecting a 24 hour process to clear the area for Entry. No preparations were carried out for any further action, such as an EVA repair.<\/p>\n
UPDATE: However, given the clear margins of safety based on the results of the point cloud data from the FI, the DAT gave a recommendation to clear the area of damage \u2013 and as a result the entire vehicle \u2013 for entry, with the MMT agreeing with no dissenting opions.<\/p>\n
Later in the Flight Day, his Holiness the Pope addressed the astronauts aboard the International Space Station. ESA astronauts Roberto Vittori and Paolo Nespoli and their colleagues talked for 20 minutes with His Holiness Benedict XVI, who was in the Foconi Room of the Vatican Library.<\/p>\n
During the call, the Pope asked several questions, and blessed the crew.<\/p>\n
STS-134 Specific Articles: http:\/\/www.nasaspaceflight.com\/tag\/sts-134\/<\/p>\n
The crew then completed their proceedure reviews and tool checkouts for the second of four EVAs scheduled for STS-134, which will be the focus of Flight Day 7.<\/p>\n
(Images via L2 documentation and videos. Extensive coverage is being provided on the news site, forum and L2 special sections \u2013 the latter of which is the world\u2019s best front row seat to Shuttle missions. With specific and extensive flight day coverage, from interactive \u201cone stop\u201d FD live coverage in the open forum, to internal documentation, photos, videos and content in the specific L2 FD areas).<\/p>\n","protected":false},"excerpt":{"rendered":"
Following the decision made by the Mission Management Team (MMT) to press ahead with a Focused Inspection (FI) on one area of Thermal Protection System (TPS) damage located on Endeavour\u2019s belly, the Orbiter Boom Sensor System (OBSS) was used to gain imagery which has successfully allowed managers to clear the vehicle for entry. Later on Flight Day […]<\/p>\n","protected":false},"author":1,"featured_media":29671,"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":[9171,3366,7935],"class_list":["post-40445","post","type-post","status-publish","format-standard","has-post-thumbnail","hentry","category-news","tag-dat","tag-sts-134","tag-tps"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40445"}],"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=40445"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40445\/revisions"}],"wp:featuredmedia":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media\/29671"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=40445"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=40445"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=40445"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}