{"id":38192,"date":"2018-12-15T00:24:23","date_gmt":"2018-12-14T16:24:23","guid":{"rendered":"https:\/\/wp-productionenv-bjg9h2g2bgg5b8aa.southeastasia-01.azurewebsites.net\/news\/plan-d-for-outer-space-nasa-updates-em-2-mission-baseline\/"},"modified":"2018-12-15T00:24:23","modified_gmt":"2018-12-14T16:24:23","slug":"plan-d-for-outer-space-nasa-updates-em-2-mission-baseline","status":"publish","type":"post","link":"https:\/\/starpath.global\/news\/plan-d-for-outer-space-nasa-updates-em-2-mission-baseline\/","title":{"rendered":"\u201cPlan D for Outer Space\u201d \u2014 NASA updates EM-2 mission baseline"},"content":{"rendered":"<p>Coming off this year\u2019s manifest changes to the early missions in NASA\u2019s Exploration campaign, the outline and major parameters for the first crewed Orion flight were formally updated to reflect those big picture updates. Exploration Mission-2 is still a test flight to check out Orion with crew system upgrades and circumnavigate the Moon, but the early part of the mission was reworked to take into account the change in configuration of the Space Launch System (SLS) launch vehicle.<\/p>\n<p>The SLS Boosters and Core Stage will leave its upper stage with Orion attached in a higher insertion orbit on EM-2. After a revised post-insertion sequence, the upper stage will take Orion and crew to an even higher and more elliptical orbit than earlier plans. Following separation from the upper stage, Orion will spend almost a day longer in Earth orbit than previously planned at the start of the mission before leaving Earth for a Lunar flyby.\n<\/p>\n<p>Transferring higher SLS performance to higher MECO orbit, ICPS<\/p>\n<p>The&nbsp;Exploration Mission-2 (EM-2) mission has always been the first Orion crewed flight, but the mission profile has gone through multiple revisions over the years, from a high-lunar orbit mission to a cislunar rendezvous with an asteroid redirect spacecraft to the current \u201chybrid triple\u201d outline.&nbsp; Even within that outline, the upper stage for the mission has gone back and forth between the Delta upper stage derivative Interim Cryogenic Propulsion Stage (ICPS) and the Exploration Upper Stage (EUS) that is still in development.<\/p>\n<p>With early SLS launches moving back to the Block 1 vehicle configuration, the mission baseline was formally revised recently. \u201cIt was an update to switch from the EUS to ICPS, so in that switch because of the performance differences in the stages we had to re-optimize part of the mission around the ICPS,\u201d Nujoud Merancy, NASA Exploration Mission Analysis Lead, explained.<\/p>\n<p><iframe id=\"twitter-widget-1\" scrolling=\"no\" frameborder=\"0\" allowtransparency=\"true\" allowfullscreen=\"true\" class=\"\" style=\"position: static; visibility: visible; width: 0px; height: 0px; display: block; flex-grow: 1;\" title=\"X Post\" src=\"https:\/\/platform.twitter.com\/embed\/Tweet.html?creatorScreenName=NASASpaceflight&amp;dnt=true&amp;embedId=twitter-widget-1&amp;features=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%3D%3D&amp;frame=false&amp;hideCard=false&amp;hideThread=false&amp;id=1054786242443792384&amp;lang=en&amp;origin=https%3A%2F%2Fwww.nasaspaceflight.com%2F2018%2F12%2Fplan-d-nasa-updates-em-2-baseline%2F&amp;sessionId=decb9d0cd371ace6a25ffcccc2dd99e77042cc02&amp;siteScreenName=NASASpaceflight&amp;theme=light&amp;widgetsVersion=6a3ad42b224df%3A1778106238597&amp;width=550px\" data-gtm-yt-inspected-14=\"true\" data-gtm-yt-inspected-21=\"true\" data-tweet-id=\"1054786242443792384\"><\/iframe><\/p>\n<blockquote class=\"twitter-tweet\" data-width=\"550\" data-dnt=\"true\" data-twitter-extracted-i1783497999921942117=\"true\">\n<p lang=\"en\" dir=\"ltr\">Mission option picked for EM-2 was D in the briefing package, thus we have a Plan D for Outer Space<\/p>\n<p>\u2014 Nujoud Fahoum Merancy (@nujoud) October 23, 2018<\/p>\n<\/blockquote>\n<p>\u201cSo this is the updated baseline for EM-2.\u201d<\/p>\n<p>In terms of launch and insertion, the first few minutes of EM-2 will look similar to the first SLS launch on the Exploration Mission-1 (EM-1) test flight of an uncrewed Orion spacecraft; however, in switching back to the Block 1 ICPS the new EM-2 baseline also changes some significant mission parameters from EM-1. The first change is to raise the high-end of the insertion orbit from 975 nautical miles to 1200.<\/p>\n<p>Rocket building kits<path d=\"M7.59009 18.59L9.00009 20L17.0001 12L9.00009 4L7.59009 5.41L14.1701 12\" style=\"animation: initial !important; background: initial !important; border: 0px !important; box-shadow: none !important; color: inherit !important; cursor: inherit !important; direction: inherit !important; display: inline !important; fill: currentcolor !important; filter: initial !important; float: none !important; margin: 0px !important; opacity: initial !important; outline: 0px !important; overflow: initial !important; padding: 0px !important; stroke: initial !important; transform: initial !important; vertical-align: initial !important; visibility: inherit !important;\"><\/path>Space Technology<path d=\"M7.59009 18.59L9.00009 20L17.0001 12L9.00009 4L7.59009 5.41L14.1701 12\" style=\"animation: initial !important; background: initial !important; border: 0px !important; box-shadow: none !important; color: inherit !important; cursor: inherit !important; direction: inherit !important; display: inline !important; fill: currentcolor !important; filter: initial !important; float: none !important; margin: 0px !important; opacity: initial !important; outline: 0px !important; overflow: initial !important; padding: 0px !important; stroke: initial !important; transform: initial !important; vertical-align: initial !important; visibility: inherit !important;\"><\/path>Space tourism guides<path d=\"M7.59009 18.59L9.00009 20L17.0001 12L9.00009 4L7.59009 5.41L14.1701 12\" style=\"animation: initial !important; background: initial !important; border: 0px !important; box-shadow: none !important; color: inherit !important; cursor: inherit !important; direction: inherit !important; display: inline !important; fill: currentcolor !important; filter: initial !important; float: none !important; margin: 0px !important; opacity: initial !important; outline: 0px !important; overflow: initial !important; padding: 0px !important; stroke: initial !important; transform: initial !important; vertical-align: initial !important; visibility: inherit !important;\"><\/path>\n<p>     (adsbygoogle = window.adsbygoogle || []).push({});<\/p>\n<p>In its Block 1 configuration the SLS Boosters and Core Stage will take a little over eight minutes to deliver the fully-loaded ICPS and its crewed Orion payload to an insertion orbit that is just below the velocity needed to stay in Earth orbit; this allows the empty Core Stage to safely breakup away from land and populated areas when it reenters the atmosphere.<\/p>\n<p><img fetchpriority=\"high\" decoding=\"async\" aria-describedby=\"caption-attachment-59481\" class=\"wp-image-59481 size-full\" src=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/gerst_nac-open_dec-2018_final.EM-2.Late-2018-Baseline.Slide-11.50pct.jpg\" alt=\"\" width=\"1500\" height=\"844\" srcset=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/gerst_nac-open_dec-2018_final.EM-2.Late-2018-Baseline.Slide-11.50pct.jpg 1500w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/gerst_nac-open_dec-2018_final.EM-2.Late-2018-Baseline.Slide-11.50pct-350x197.jpg 350w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/gerst_nac-open_dec-2018_final.EM-2.Late-2018-Baseline.Slide-11.50pct-622x350.jpg 622w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/gerst_nac-open_dec-2018_final.EM-2.Late-2018-Baseline.Slide-11.50pct-768x432.jpg 768w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/gerst_nac-open_dec-2018_final.EM-2.Late-2018-Baseline.Slide-11.50pct-1170x658.jpg 1170w\" sizes=\"(max-width: 1500px) 100vw, 1500px\"><\/p>\n<p id=\"caption-attachment-59481\" class=\"wp-caption-text\">Revised Exploration Mission-2 (EM-2) outline, as presented by NASA officials to the NASA Advisory Council (NAC) Human Exploration and Operations (HEO) Committee in early December. Credit: NASA.<\/p>\n<p>\u201cWe had performance on the Core Stage, so did we want to raise the insertion off the Core to push that performance uphill,\u201d Merancy said explaining the trade-off. \u201cWe did end up taking that option, it was a trade between a 975 nautical mile drop off \u2014 it drops off lower than that but the coasting apogee would be 975 \u2014 but we raised that up to 1200.\u201d<\/p>\n<h4 class=\"widget-title penci-border-arrow\">See Also<\/h4>\n<ul>\n<li>Orion Forum Section<\/li>\n<li>SLS Forum Section<\/li>\n<li>L2 SLS Section<\/li>\n<li>L2 Orion Section<\/li>\n<li>Click here to Join L2<\/li>\n<\/ul>\n<p>\u201cWe have that performance in the Core Stage on EM-1 as well, but being the first flight and we didn\u2019t need to push it uphill, we opted to keep that performance on the Core Stage for the first flight and it increases your engine-out capability on SLS,\u201d she elaborated.<\/p>\n<p>\u201cFor EM-2, the first stage would have been flown and because the ICPS and the in-space portion is more the performance driver, we\u2019re opting to raise that Core Stage insertion so we can have more margin on ICPS, which gives us more launch opportunities for ICPS.\u201d<\/p>\n<p>Increasing the apogee of the vehicle at Core Stage Main Engine Cut Off (MECO) also provides some improvement to the overall period of days each month where Orion can reach the Moon on SLS.<\/p>\n<p>\u201cThe elliptical parking orbit limits your launch opportunities in the month because you can only go when the Moon is in the direction of the apogee, so pushing performance on the ICPS increases the number of days,\u201d she said. \u201cI think basically we\u2019re between eight to ten days with the difference pushing that uphill.\u201d<\/p>\n<p>First upper stage burn moved up<\/p>\n<p>The second change reorders the sequence of post-insertion events after Orion and ICPS have separated from the Core Stage following MECO. Both the Orion\/ICPS mated combo and the Core Stage are still in an orbit with a perigee or low point of around 20 nautical miles that the ICPS must raise to a higher altitude to stay in orbit.<\/p>\n<p>On EM-1, the Perigee Raise Maneuver (PRM) is performed by ICPS when the vehicle reaches the apogee of the insertion orbit, about 40 minutes after liftoff and over thirty minutes after MECO, raising the perigee to 100 nautical miles. For EM-2, the PRM burn was moved up in front of Orion\u2019s solar array deployment with ignition ten minutes after MECO, in part to provide a bigger window of time in between major ICPS burns for initial Orion checkouts.<\/p>\n<p>\u201cThe apogee on EM-1 had been picked [for PRM] to maximize performance, but that puts it in sort of an awkward position for Orion because the solar array deploy occurs between MECO and PRM and then you have to park them for PRM and then you coast again,\u201d Merancy explained. \u201cSo we really wanted to look at whether we could move that PRM earlier.\u201d<\/p>\n<p><img loading=\"lazy\" decoding=\"async\" aria-describedby=\"caption-attachment-59484\" class=\"wp-image-59484 size-full\" src=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/sls_block_1_expanded_view_orion_copy.75pct.jpg\" alt=\"\" width=\"1800\" height=\"1371\" srcset=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/sls_block_1_expanded_view_orion_copy.75pct.jpg 1800w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/sls_block_1_expanded_view_orion_copy.75pct-350x267.jpg 350w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/sls_block_1_expanded_view_orion_copy.75pct-460x350.jpg 460w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/sls_block_1_expanded_view_orion_copy.75pct-768x585.jpg 768w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/sls_block_1_expanded_view_orion_copy.75pct-1170x891.jpg 1170w\" sizes=\"(max-width: 1800px) 100vw, 1800px\"><\/p>\n<p id=\"caption-attachment-59484\" class=\"wp-caption-text\">SLS Block 1 Crew vehicle configuration. The EM-2 mission baseline has formally moved back from Block 1B Crew to Block 1 Crew, which will be used for both EM-1 and EM-2. Credit: NASA.<\/p>\n<p>The PRM burn on EM-2 will raise the perigee and apogee to an orbit of 100 nautical miles by around 1450 nautical miles. Performing it earlier provides more time for Orion\u2019s solar array deploy and initial spacecraft checkouts between the two major ICPS burns with Orion. The resultant orbit also has a slightly longer period, which provides a little more time before the Apogee Raise Burn (ARB) that ICPS does at the end of the first orbit when the vehicle is at the 100 nautical mile perigee.<\/p>\n<p>\u201cIt de-optimizes the PRM so there\u2019s a little bit of a performance hit, but it\u2019s a much more I\u2019ll say stable period then for Orion to deploy the solar arrays after PRM and perform checkout in a quiescent, coasting LEO (Low Earth Orbit). So it\u2019s really an operational consideration to move it forward to make the rest of the Orion checkout more ops-friendly.\u201d<\/p>\n<p>The EM-2 mission profile now also baselines a single low-altitude Earth Orbit, which reduces MMOD risk. In the prior baseline when Orion was flying with EUS, it stayed in the low-altitude \u201cparking\u201d orbit for two revolutions; in that case, Orion and EUS were flying in a circular orbit around 100 nautical miles, which is largely below the altitudes with high MMOD risk.<\/p>\n<p>\u201cThe MMOD environment starts at around 500 nautical miles from those satellite breakups that occurred,\u201d Merancy explained. \u201cWhen we were staging on EUS we can do a couple of orbits and there\u2019s no real difference in MMOD risk; however with ICPS and the elliptical orbit, once the apogee gets above 500 nautical miles you have MMOD concerns.\u201d<\/p>\n<p>\u201cSo the other advantage to the early PRM is it boosts up that apogee, we have a slightly longer orbit,\u201d she added. \u201cWe went through the whole thing with flight ops (operations), they went through and made sure they could finish Orion checkout, and so we are opting for the first rev (revolution) to reduce MMOD risk but there\u2019s still sufficient time to perform the checkout needed prior to TLI, or in this case ARB.\u201d<\/p>\n<p>ICPS will do a full TLI burn with the uncrewed Orion on EM-1; for the first crewed Orion on EM-2, ICPS it will do an Apogee Raise Burn that takes Orion to the second orbit of the hybrid triple. The profile has Orion flying in three orbits: a low Earth orbit still attached to the booster upper stage, a high Earth orbit (HEO) by itself that was going to last for about one day, and a single solo lap around the Moon before returning to splashdown on Earth. NASA has been considering variations of this mission for EM-2 going back several years.<\/p>\n<p>\u201cThe ICPS is capable of doing the full TLI burn, we\u2019re only utilizing part of it,\u201d Merancy said. \u201cBoth are well within what ICPS can do, that\u2019s what it\u2019s doing on EM-1.\u201d<\/p>\n<p>Increasing High Earth Orbit altitude and duration<\/p>\n<p>The third change uses the ARB to burn to an even higher apogee than previous planned, increasing the duration of the High Earth Orbit from 24 hours to 42 hours by almost doubling an already very high apogee. \u201cThe HEO is around 205 by 59260 nautical miles,\u201d Merancy noted.<\/p>\n<p>\u201cThey\u2019ll have a really good view from the HEO and then they get to go by the Moon,\u201d she said of the future EM-2 crew.<\/p>\n<p>The long orbit allows an extended evaluation of the performance of new spacecraft systems close to home, especially the crew systems that will be making their first flight.&nbsp;&nbsp;\u201cThe whole point of the HEO is to provide a checkout near the Earth where you don\u2019t need big burns to come home, we\u2019re one to two days from home,\u201d Merancy said.<\/p>\n<p>The Environmental Control and Life Support System (ECLSS), crew displays, and other crew systems will be making their debut in Orion on EM-2.<\/p>\n<p>Orion will still do a Trans-Lunar Injection (TLI) burn on its own that provides the remaining change in velocity or delta-V needed to go from the HEO to a Lunar flyby, but the bigger ARB burn by the ICPS at the end of the first orbit reduces the delta-V for Orion\u2019s TLI. \u201cRaising the apogee [means] less demands on Orion\u2019s prop (propellant) system for the upcoming TLI, which leaves more performance should you need an abort post-TLI.\u201d<\/p>\n<p><img loading=\"lazy\" decoding=\"async\" aria-describedby=\"caption-attachment-59482\" class=\"wp-image-59482 size-full\" src=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/MES_2_web.40pct.jpg\" alt=\"\" width=\"1700\" height=\"958\" srcset=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/MES_2_web.40pct.jpg 1700w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/MES_2_web.40pct-350x197.jpg 350w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/MES_2_web.40pct-621x350.jpg 621w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/MES_2_web.40pct-768x433.jpg 768w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/MES_2_web.40pct-1170x659.jpg 1170w\" sizes=\"(max-width: 1700px) 100vw, 1700px\"><\/p>\n<p id=\"caption-attachment-59482\" class=\"wp-caption-text\">ICPS fires for a second time to carry Orion away from Earth. On EM-2, Orion\u2019s solar arrays will be deployed between the first two upper stage burns. Credit: Nathan Koga for NSF\/L2.<\/p>\n<p>\u201cIt\u2019s about a thousand pounds of Orion prop,\u201d Merancy said about the difference in orbits. \u201cSo there is an advantage to having that be a bigger orbit, in that then Orion has more prop available post-TLI should other emergencies occur.\u201d<\/p>\n<p>It would have been theoretically possible to pick an orbit with a period between 24 and 42 hours, but practically Merancy said they would not do the TLI burn in the middle of the crew\u2019s sleep period. \u201cWe could have gone up to around 27 hours and then you can\u2019t do the orbit period because TLI would have been in crew sleep. Forty-two hours was sort of the next morning for the crew day.\u201d<\/p>\n<p>The Orion TLI burn would be at perigee of the HEO, which would be at the end of that orbit\u2019s period.<\/p>\n<p>\u201cSo there is a method to the madness there,\u201d she added. \u201cWe got to 42 hours so we can align TLI with the crew being awake and it\u2019s performance that ICPS can get to and leaves more prop on Orion, so all of those factors sort of optimized that orbit period.\u201d<\/p>\n<p>\u201cAnd we found that the aborts from the HEO were roughly equivalent between the 24 and 42 [hour orbits], so there wasn\u2019t a reason to stay in the 24, comparatively.\u201d<\/p>\n<p>Circumlunar timeline mostly unchanged<\/p>\n<p>After the Orion TLI burn, the rest of the EM-2 mission remains as previously baselined, with the round trip to the Moon taking four days out and four days back. \u201cThe Orion in-space portion of the mission looks roughly the same as before, it\u2019s just the HEO that\u2019s different,\u201d Merancy said.<img loading=\"lazy\" decoding=\"async\" class=\"aligncenter size-full wp-image-58466\" src=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/10\/L2-banner@2x.jpg\" alt=\"\" width=\"4500\" height=\"2532\">\u201cSo the TLI, the Lunar flyby, Orion is targeting the same as it was before, it\u2019s just added hours in HEO before it goes there. So it was a nine-day mission before, now it\u2019s a ten-day mission.\u201d<\/p>\n<p>Orion and crew will swing around the Moon at an altitude of about 4800 nautical miles.<\/p>\n<p>Revisiting cubesats<\/p>\n<p>After dropping Orion off in its high, elliptical Earth orbit early on the first day of the mission, ICPS will make its own TLI burn using its flyby of the Moon to head into a heliocentric disposal orbit. \u201cI think we\u2019re in the like 20 to 30 minute range, but Orion will do the separation, do a burn to gather distance from ICPS, and then ICPS will do a disposal burn,\u201d Merancy explained.<\/p>\n<p>\u201cWe still baselined a heliocentric disposal for ICPS, so it essentially completes TLI after Orion is separated and will continue on to its disposal. It just has to wait enough time for Orion get safe separation.\u201d<\/p>\n<p>Although the major outlines of the mission are now rebaselined, it will continue to be iteratively refined with subsequent changes generally of smaller degrees. One of the things that will be looked at now is whether there is any secondary payload capability.<\/p>\n<p><img loading=\"lazy\" decoding=\"async\" aria-describedby=\"caption-attachment-59483\" class=\"wp-image-59483 size-full\" src=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct.jpg\" alt=\"\" width=\"1680\" height=\"1120\" srcset=\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct.jpg 1680w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct-350x233.jpg 350w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct-525x350.jpg 525w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct-768x512.jpg 768w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct-1170x780.jpg 1170w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct-585x390.jpg 585w, https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/12\/KSC-20180405-PH_GEB01_0025_orig.25pct-263x175.jpg 263w\" sizes=\"(max-width: 1680px) 100vw, 1680px\"><\/p>\n<p id=\"caption-attachment-59483\" class=\"wp-caption-text\">Orion Stage Adapter for EM-1 in the Space Station Processing Facility following arrival at Kennedy Space Center in April. The cubesat dispensers can be seen around the top circumference. Following the rebaselining of the basics of the EM-2 mission, NASA will re-examine whether secondary payloads like this can be accommodated. Credit: NASA\/Glenn Benson.<\/p>\n<p>On EM-1 thirteen cubesats are being flown in an adapter that sits on top of the ICPS; they will be deployed from ICPS after Orion has separated from the upper stage. Merancy said they set aside some of these questions while focusing on baselining the mission for its main objectives.<\/p>\n<p>\u201cWhen we were trying to baseline it we just sort of ground ruled out a lot of those secondary questions, so the baseline doesn\u2019t show cubesats,\u201d she said. \u201cThat is another item we\u2019re working now \u2014 do we want to now basically add cubesats or use performance in other ways.\u201d<\/p>\n<p>\u201cIt\u2019s sort of an iterative process, we\u2019ve figured out that much and now we\u2019re going to look to see do we want to add cubesats or not. We\u2019re working with the Science office and SLS on that question, actually.\u201d<\/p>\n","protected":false},"excerpt":{"rendered":"<p>Coming off this year\u2019s manifest changes to the early missions in NASA\u2019s Exploration campaign, the outline and major parameters for the first crewed Orion flight were formally updated to reflect those big picture updates. Exploration Mission-2 is still a test flight to check out Orion with crew system upgrades and circumnavigate the Moon, but the [&hellip;]<\/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":[4011,640,624],"class_list":["post-38192","post","type-post","status-publish","format-standard","hentry","category-news","tag-em-2","tag-orion","tag-sls"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/38192"}],"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=38192"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/38192\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=38192"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=38192"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=38192"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}