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However, while the November Human Space Exploration Community Workshop on the Global Exploration Roadmap \u2013 which is being serialized by this site \u2013 has provided some interesting mission options, the SLS Con Ops document \u2013 finalized just a few weeks prior to the workshop \u2013 reveals the actual foundation of SLS\u2019 hardware, operations and indeed mission baselines.<\/p>\n
Known as Exploration Systems Development (ESD) Design Reference Missions (DRM), the Con Ops document \u2013 available to download via L2 \u2013 introduces the SLS capability as one which provides multiple mission options, ahead of expanding into the current thought process for utilizing the vehicle\u2019s unrivalled upmass capability.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/A7111.jpg\" "\\"A711\\"")
\u201cThe SLS will have the largest payload lifting capacity of any launch vehicle previously manufactured in the United States: 70 metric ton (t) class evolvable to 130+ t class (ESD Requirement R-11),\u201d noted the document in the introductory sections.<\/p>\n\u201cThis will allow the SLS to accommodate many mission profiles, starting with Orion missions for lunar fly-by and high lunar orbit and eventually deep space near Earth asteroid (NEA) and Mars missions that extend human presence across the solar system (requiring ~130 t).<\/p>\n
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\u201cThe SLS will also accommodate Orion-MPCV missions to low Earth orbit (LEO) for system test and checkout and as a back-up access to the International Space Station (ISS), including transport of replacement ISS modules. Other mission profiles that can be supported by the SLS include science-based missions for deep space astronomy and solar system exploration.<\/p>\n
\u201cThe SLS payload capability will enable a new generation of planetary (such as a Europa fly-by to collect samples with return capability), Earth, and heliophysics science missions. SLS will also be capable of supporting commercial-based missions and missions supporting other Government agencies, including sending larger objects into LEO, such as commercial space stations.\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/A81.jpg\" "\\"A81\\"")
While the introduction provides little by way of additional substance into age-old adage of \u201cMoon, Mars and Beyond\u201d \u2013 as used by the now-defunct Constellation Program (CxP), the document goes on to provide an expansive and up-to-date overview of the DRMs, whilst adding the caveat the missions may not occur in any particular order and are not set requirements, but are used as a framework to ensure SLS capability.<\/p>\n\u201cThe ESD DRMs are categorized as Tactical, Strategic, Architecture, and Analysis timeframe DRMs. The Tactical Timeframe DRMs are intended to reduce overall design risk and help to preserve operations capabilities by allowing missions to be flown earlier in the design process,\u201d the document notes.<\/p>\n
\u201cThe Strategic DRMs build on the capabilities demonstrated in the Tactical timeframe to ensure a path to achieve the operational capabilities as laid out in the ESD Requirements. The collection of these DRMs is the architecture framework necessary for multi-destination exploration.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/B4311.jpg\" "\\"B431\\"")
\u201cThe Architectural timeframe DRMs address the missions where evolved capabilities will be needed to achieve the long-term exploration objectives. These DRMs are critical in understanding the requisite system functionality, and deriving the Program-specific operations block designs that will enable an effective block delivery evolution path. Analysis DRMs are candidate DRMs that are under formal ESD consideration. Analysis will be performed on these DRMs as part of a cost\/benefit assessment.<\/p>\n\u201cOnce ESD leadership has determined the status of an analysis DRM, the DRM will either be added to the appropriate timeframe DRMs or will be discarded. While programs will need to perform some level of analysis to support this decision-making process, the analysis that supports the evolvability design assessments is not necessary for Analysis DRMs.\u201d<\/p>\n
The wording of the above shows some of the challenges of formulating the definitive exploration plan \u2013 and the likely reason that as of today such a plan does not exist. NASA\u2019s future plans continue to be hindered by a budget that lacks stability, as much as lawmakers have shown their hand in wishing to protect SLS and Orion from such budget fluctuations.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/Z10.jpg\" "\\"Z10\\"")
Ironically, one area of NASA funding which is being subjected to uncertainty is the commercial handover of Low Earth Orbit (LEO), not least from the commercial crew standpoint. With threats of slips \u2013 based on lower-than-expected funding and internal technical challenges \u2013 there is potential for the need of a back-up, as SLS was intended to be \u2013 per the 2010 Authorization Act \u2013 for the International Space Station.<\/p>\nHowever, with SLS\u2019 opening mission \u2013 one which is BEO in design \u2013 not set to fly until 2017, such slips would have to be serious in nature for NASA to use a vehicle which is now designed specifically for exploration, as opposed to LEO.<\/p>\n
Regardless, the back-up ability to transport four crew members on Orion, launched on a basic SLS, opens the DRM list.<\/p>\n
\u201cISS Back-Up Crew Delivery (Analysis): The International Space Station (ISS) Back-Up Crew Delivery mission (DRM ID: LEO_Util_1A_C11A1) is flown with the SLS and the Orion-MPCV, with SLS providing any necessary ballast and launch stack spacers,\u201d noted the presentation.<\/p>\n
\u201cThis DRM is a single launch of up to four crew members to and from the ISS and is a back-up to the planned commercial crew capability for transportation to the ISS. This mission is flown using the Block 1 SLS without an iCPS.\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/Z111.jpg\" "\\"Z11\\"")
The next DRM is currently in the documented approach for SLS\u2019 opening mission in 2017, one that involves an uncrewed test flight around the Moon, on a mission which \u2013 according to Con Ops \u2013 will last around eight days.<\/p>\n\u201cBEO Uncrewed Lunar Fly-by (Tactical Timeframe): This mission uses a single Block 1 SLS launch with an iCPS and lunar Block 1 Orion-MPCV. This DRM will go beyond Earth orbit (BEO) and test critical mission events and performance in relevant environments,\u201d the Con Ops document noted.<\/p>\n
\u201cIt will take 3-4 days of transit time, with the Orion-MPCV trajectory taking it around the Moon performing burns as required, and then 3-4 days to return to Earth. The liftoff mass will be approximately 66 t.\u201d<\/p>\n
SLS-2 will carry out a similar mission, this time with a crew. Initially manifested for 2021 on the \u201cworst case\u201d scenario, moves have already been made by the Orion Project office to push this up to 2019, or potentially 2018. This mission will last around 14 days, with four days in Lunar orbit.<\/p>\n
\u201cBEO Crewed Lunar Orbit (Tactical Timeframe): This mission requires a single Block 1 SLS launch with an iCPS and Lunar Block 1 Orion-MPCV to LEO. It will take 4-5 days of transit time, 4 days in lunar orbit, and 4-5 days for return to Earth. The liftoff mass will be approximately 66 t.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/Z121.jpg\" "\\"Z12\\"")
\u201cThe iCPS performs the orbit raise burn and TLI (Trans-Lunar Injection) burn prior to disposal. When approaching high lunar orbit, the Orion-MPCV provides the lunar orbit insertion (LOI) burn to insert the Orion-MPCV into a high lunar orbit. The Orion-MPCV will remain in lunar orbit for several days and then perform a trans-Earth injection (TEI) burn and return to Earth.<\/p>\n\u201cThe lunar orbit will be selected to maintain the total delta-V for LOI and TEI maneuvers within the Orion-MPCV design capability.\u201d<\/p>\n
Opportunities to collect data on the hardware \u2013 most notably on Orion\u2019s performance \u2013 will be taken via the Exploration Test Flight (EFT-1), scheduled for early 2014.<\/p>\n
While these two missions appear to be the most solid part of the short-term mission plan for SLS and Orion, everything that follows is open for evaluation. However, the DRM content in the Con Ops provides multiple options, along with clues as to how such missions would be conducted.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/Z131.jpg\" "\\"Z13\\"")
One such example can be found under the DRM of a mission to Geostationary Orbit (GEO), utilizing two SLS launches, 180 days apart. Such a DRM scenario also dismisses the worst-case scenario which shows a maximum near-term flight rate of one launch per year \u2013 which would clearly be uneconomic for the HLV.<\/p>\n\u201cGEO (Analysis): The GEO vicinity mission (DRM ID: CIS_GEO_1B_C11B1) requires two SLS launches, with the first carrying CPS1 and a cargo hauler. The second launch, approximately 180 days later, will contain CPS2 and the Orion-MPCV,\u201d noted the overview.<\/p>\n
\u201cThe mass-to-orbit for both launches will be approximately 110 t each. This would allow crew to perform servicing or deployment missions in GEO, depending on the payload inside the cargo hauler.\u201d<\/p>\n
Reverting back to aspirations involving the Moon, the next DRM has seen a large increase in interest over 2011, namely a mission to return humans back to the surface of the Moon.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/Z62.jpg\" "\\"Z6\\"")
Work appears to be making good progress on setting up a preferred flight profile for such a Lunar Surface, with one of three options set for deletion. Two of the options can be carried out prior to the evolved SLS coming on line.<\/p>\n\u201cLunar (Strategic and Architecture Timeframes): The lunar set of missions ranges in distance from lunar vicinity Lagrange Point 1 (L1), to low lunar orbit, to a lunar surface mission,\u201d noted the ConOps.<\/p>\n
\u201cThe first two of the three mission set, lunar vicinity and low lunar orbit (DRM IDs: CIS_LP1\/LLO_1A1A_C11B1, Concept of Operations), which are in the Strategic timeframe, require one SLS launch with the Orion-MPCV and CPS to L1 or low lunar orbit (LLO). The mass-to-orbit for these two missions are approximately 90 t and 95 t, respectively.<\/p>\n
\u201cIt should be noted that the low lunar vicinity DRM (CIS_LP1_1A_C11B1) is under ESD review for removal.\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/Z53.jpg\" "\\"Z5\\"")
The third option requires two SLS launches, this time around 120 days apart. However, the liftoff mass requires the use of the evolved SLS, pushing such a mission out to at least the late 2020s. See SLS configuration option latest (Block 1, 1A, 2) via L2. <\/p>\n\u201cThe lunar surface mission (DRM IDs: LUN_SOR_1A1A_C11B1, ESD Concept of Operations), which is in the Architecture timeframe, requires two launches, spaced 120 days (TBR) apart, to insert the lunar lander and CPS1 and Orion-MPCV and CPS2 into LLO for a lunar orbit rendezvous (LOR) and landing on the equatorial or polar regions of the Moon. The liftoff masses will be approximately 130 t and 108 t, respectively.\u201d<\/p>\n
No reference is made to the fascinating proposal relating to the Exploration Gateway Platform architecture that not only returns man to the lunar surface \u2013 via the use of only one SLS launch to a reusable Lunar Lander \u2013 but provides a baseline for pathfinders towards an eventual crewed mission to Mars.<\/p>\n
However, internal meeting notes (L2) just this month show this L2 gateway is now under official consideration, with mission options being evaluated at present.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2011\/12\/Z151.jpg\" "\\"Z15\\"")
\u201cNASA Human Architecture Team (HAT): L2 based DRMs being developed,\u201d noted the Strategic Analysis and Integration Division (SAID).<\/p>\nSuch a plan revolves around a deep space platform, known as a gateway, located at Earth-Moon Lagrange (EML) point 1 or 2, after being built from pre-launched hardware, providing the host station for a reusable Lunar Lander \u2013 which would also be launched by the SLS.<\/p>\n
The Gateway would first be constructed at the ISS, mainly using the Node 4\/DHS (Docking Hub System), an orbiter external airlock, an MPLM (Multi-Purpose Logistics Module) habitat module, and an international module.<\/p>\n
Further articles on the Gateway will be forthcoming, along with Part 2 to the ESD DRMs from the ConOps, which cover missions to Near Earth Asteroids, SLS science missions to as far out as Enceladus, and Department Of Defense (DOD) missions.<\/p>\n
Please note following trial run: Clickable GOLD links with (L2) references point directly to cited L2 content. Such content is only available to L2 members (please ensure you are logged in). Clickable BLUE links point to NSF articles and open content.<\/p>\n
Images: Via L2 content, driven by L2\u2032s fast exapanding SLS specific L2 section, which includes, presentations, videos, graphics and internal updates on the SLS and HLV, available on no other site. Other images via NASA.)<\/p>\n
(L2 is \u2013 as it has been for the past several years \u2013 providing full exclusive SLS coverage, available no where else on the internet. To join L2, click here: http:\/\/www.nasaspaceflight.com\/l2\/)<\/p>\n","protected":false},"excerpt":{"rendered":"
With evaluations continuing into NASA\u2019s future crewed exploration aspirations, the foundations behind what should be a definitive roadmap \u2013 otherwise known as Exploration Systems Development (ESD) Design Reference Missions (DRM) \u2013 are starting to come to light, as outlined in the Space Launch System (SLS) Concept Of Operations (Con Ops) document. SLS Mission Ability \u2013 […]<\/p>\n","protected":false},"author":1,"featured_media":29655,"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":[9034,233,625,624],"class_list":["post-40253","post","type-post","status-publish","format-standard","has-post-thumbnail","hentry","category-news","tag-hlv","tag-iss","tag-moon","tag-sls"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40253"}],"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=40253"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40253\/revisions"}],"wp:featuredmedia":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media\/29655"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=40253"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=40253"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=40253"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}