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Ironically, the main threat to the schedule target may be due to problems unrelated to Orion or the SLS. This is due to the law of then 2010 Authorization Act, which requires SLS and Orion to provide a back-up role for the International Space Station (ISS), in the event of major disruption in the Commercial Crew arena.<\/p>\n
This would be an undesirable situation for all concerned, not least because the 70mt SLS and BEO Orion would be vastly overpowered \u2013 and economically overpriced \u2013 for the role of lofting astronauts to the orbital outpost in Low Earth Orbit. At the same time, it would mean the Commercial Crew partners would have failed to achieve their designated role several years after the initial target of 2015.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z1031.jpg\" "\\"Z103\\"")
A worst case scenario \u2013 where both commercial crew and SLS\/Orion were unavailable \u2013 would result in NASA continuing to pay the Russians for ferrying up US astronauts to the ISS on the Soyuz.<\/p>\nWhile budget concerns have raised fears the return of a US domestic crew launch capability may not be ready until 2017, Bill Gerstenmaier, Associate Administrator for Human Exploration and Operations, insisted no plans were being made at this time to use Orion in such a back up role at this stage.<\/p>\n
Spaceflight
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Should the future transpire as planned, commercial companies \u2013 under contract to NASA \u2013 will have taken over the role of the Russian Soyuz for US astronauts, allowing NASA to press on with the return to the exploration of deep space.<\/p>\n
While Orion will gain an important test via the Exploration Flight Test (EFT-1) in early 2014 \u2013 a major milestone for the heatshield\/Thermal Protection System (TPS) via an entry profile that will match a return from deep space \u2013 this mission will be launched via a Delta IV Heavy (D-IVH).<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z325.jpg\" "\\"Z3\\"")
Three years later, the first SLS will be assembled in the Vehicle Assembly Building (VAB) at the Kennedy Space Center (KSC) \u2013 with the \u201cfull capability\u201d Orion MPCV integrated atop of the HLV, prior to being rolled out on the Mobile Launcher to Pad 39B.<\/p>\nThe 318 feet, 70mt SLS will feature two of ATK\u2019s five segment Solid Rocket Boosters (SRBs), four RS-25Ds donated from the Space Shuttle Program (SSP), a core built by Boeing at the Michoud Assembly Facility (MAF), an avionics suite\/instrument unit, a kick stage \u2013 or Interim Cryogenic Propulsion System (ICPS) mated to the Orion, with the Spacecraft and Payload Adapter and Fairing being topped off by a Launch Abort System (LAS).<\/p>\n
Teams are likely to mirror a real human mission, with the same Launch Commit Criteria (LCC) and Firing Room procedures, along with a closeout crew at the pad. The countdown and procedures for launching the SLS are covered in the specific SLS Concept of Operations article recently published on this site.<\/p>\n
While the EM-1 overview is currently classed as notional, the recent SLS Master Presentation (E.5) \u2013 available on L2 (L2 Link to Presentation) provided a good insight into the basic mission plan, which is titled \u201cNotional Mission for Orion First Flight in 2017: Uncrewed Beyond-Earth Orbit (BEO) Demonstration.\u201d<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z419.jpg\" "\\"Z4\\"")
The outline takes over once SLS has launched Orion into an high-apogee orbit of 975 nmi at the insertion point, following Main Engine Cut Off (MECO) of the four Pratt & Whitney Rocketdyne RS-25Ds \u2013 four engines that will be potentially (depending on their selection) providing their swansong after providing assistance during Space Shuttle launches.<\/p>\nThey will be destroyed when the core stage re-enters and splashes down in a pre-determined disposal corridor.<\/p>\n
\u201cNotional Mission Event Sequence:\u202f1) SLS lofts Orion to high-apogee orbit, while meeting core disposal constraints,\u201d noted the EM-1 overview.<\/p>\n
With Orion \u2013 and its kick stage\/ICPS \u2013 in space, a Trans Lunar Injection (TLI) burn(s) needs to be conducted, to send Orion on a path towards the Moon.<\/p>\n
For SLS\/HLV Articles, click here: http:\/\/www.nasaspaceflight.com\/tag\/hlv\/<\/p>\n
The eventual Upper Stage of choice \u2013 which will sport J-2X engines \u2013 will not be used on this mission. Instead, the role of the kick stage\/ICPS will most likely be conducted by a Delta Cryogenic Second Stage (DCSS) \u2013 following on from its role during the EFT-1 mission.<\/p>\n
Draft versions of the EM-1 mission outline named this as the stage of choice for the mission. However, the more recent SLS presentation simply classes the kick stage as \u201cTBD\u201d (To Be Decided). After all, with the mission over five years away, a different stage could be chosen if SLS teams so wish.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/A118.jpg\" "\\"A118\\"")
The options for a stage that could perform a role are plentiful, as seen during the Sidemount HLV evaluations \u2013 as much as the DCSS is still considered the favorite.<\/p>\n\u201cHLV could utilize existing stages such as the Delta IV or Atlas V upper stages,\u201d noted the 726 page Sidemount HLV presentation \u2013 (available on L2 \u2013 Link to Presentation). \u201cSuch stages could support demonstration missions such as a lunar swing-by Orion test mission.\u201d<\/p>\n
NASA managers have also released details of the requirement for the ICPS via an acquisition synopsis, which in turn provides additional details on the TLI burn requirements for the Orion heading to the Moon.<\/p>\n
\u201cThe early flights of the SLS architecture will require the use of an ICPS to ensure the placement of the Orion on the required trajectory. In order to support the flight schedule, the initial ICPS flight unit must be delivered to KSC no later than late in the fourth quarter of the 2016 government fiscal year (GFY),\u201d noted the synopsis.<\/p>\n
\u201cRequirements: Human Rated or Human Ratable for Space Systems. Burns (accelerating Orion\/MPCV) following placement of ICPS and MPCV at insertion point by SLS. Three engine ignitions to achieve greater than 3050 m\/s delta-V. ICPS Lift Capability total weight of 24224 kg (53404 lbs). ICPS Mass less than 71400 lbs.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z517.jpg\" "\\"Z5\\"")
\u201cPerform a separation event. Three-axis attitude control after SLS insertion and prior to separation from MPCV. Constraints: Axial acceleration, during stage burns, not to exceed 2g. Support MPCV free lunar return missions. Support MPCV High Lunar Orbit (HLO) missions.\u201d<\/p>\nBased on the above requirements, the winning ICPS\/Kick Stage may perform around three TLI burns to achieve the goal of sending Orion on its way to the Moon \u2013 given one burn would not provide the required delta-V. It was also listed that the typical duration of ballistic phases between burns will be 50-270 minutes between the first and second burn, while it has not yet been decided how long a duration is required between the second and third burn.<\/p>\n
It will also provide its own disposal burn once separated from Orion \u2013 listed at <50 m\/s delta-V \u2013 to safely dispose of stage.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z617.jpg\" "\\"Z6\\"")
\u201c2) Kick-stage (TBD) performs burn to raise perigee to safe height. 3)\u202f Kick-stage (TBD) performs TLI burn,\u201d continued the EM-1 overview, as Orion \u2013 which would separate from the stage soon after the TLI burn \u2013 takes aim on the Moon. \u201c4)\u202f 3-5 day transit time. 5)\u202f Lunar flyby. 6)\u202f 3-5 day transit time.\u201d<\/p>\nAs noted above, the length of the mission will be determined by the transit time, as Orion arrives at the Moon, transits around the far side at a High Lunar Orbit (HLO), and heads back to Earth on a Free Return Trajectory.<\/p>\n
\u201cOrion BEO configuration: Lunar-capable heat shield. Two-tank service module and propulsion offload for lower mass. Kick-stage motor (TBD) provides trans-lunar injection (TLI). Orion mission duration: 7-10 days,\u201d added the overview.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z931.jpg\" "\\"Z93\\"")
With Earth beginning to grow in size in the window, the spacecraft will prepare to head towards what would be the second test of the heatsheild \u2013 following EFT-1 \u2013 except this time the return will be from deep space for real. This return is a major part of the top level objectives for the mission.<\/p>\n\u201cTop-Level Objectives:\u202fDemonstrate spacecraft systems performance to verify for safe crewed flight. High-speed entry (~11 km\/s). Thermal Protection System performance,\u201d added the EM-1 overview.<\/p>\n
For Orion\u2019s Thermal Protection System Advanced Development Project considered eight different materials, NASA downselected to an Avcoat and Phenolic Impregnated Carbon Ablator \u2013 with a technical name of AVCO 5026-39 HCG (Filled Epoxy Novalac in Fiberglass-Phenolic Honeycomb).- meaning the business end of Orion\u2019s heatshield will be similar to that used by the Apollo spacecraft.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z710.jpg\" "\\"Z7\\"")
The backshell, however, will have several hundred tiles, exotically named as TUFI coated AETB-8 tiles, bonded to 10 panels of composite laminate facesheets on a titanium honeycomb core.<\/p>\nOriginally, the baseline for the backshell was a SLA-561V material with plasma sprayed aluminum coating for on-orbit thermal control. However, the AETB-8 tiles provide more mass-efficient MMOD (Micro-Meteoroid Orbital Debris) protection. As such, panel tile thickness, substrate facesheet thickness, and core density are tailored for thermal and structural load, and MMOD requirements.<\/p>\n
The tiles will be mechanically attached to the pressure vessel with thermal isolating brackets along their edges, a process which has already been practised on an entire C panel for the Orion Ground Test Article (GTA). The first EFT-1 tile has already been manufactured. These same tiles will be added to the Orion set to conduct EM-1.<\/p>\n
Protecting Orion through the re-entry phase of the mission, the spacecraft will bleed off energy, prior to the deployment of the drogue chutes, which will slow the vehicle down to a velocity and attitude acceptable for their release.<\/p>\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2012\/02\/Z86.jpg\" "\\"Z8\\"")
The three main parachutes will then deploy, slowing Orion down towards its splashdown in the Pacific, where support crews will race to the vehicle by boat and helicopter.<\/p>\nThe Orion will be recovered and shipped back to land, allowing for inspections to be carried out on how the spacecraft performed during its mission.<\/p>\n
Opening inspections are likely to take place on the vessel returning Orion back to port, followed by further inspections once a crane has placed the spacecraft on solid ground at the port.<\/p>\n
All of the mission data will be feed into a post-flight review \u2013 likely to be similar to the In Flight Anomaly (IFA) review conducted by NASA after shuttle missions \u2013 which will likely be part of a subsequent qualification period, allowing SLS and Orion teams to provide the approval required to allow human crews to fly on the launch vehicle and spacecraft.<\/p>\n
The following mission \u2013 SLS-2\/EM-2 \u2013 is set to take place \u201cas early as\u201d 2019 and would be a mirror of EM-1 \u2013 except this time with a crew of up to four astronauts.<\/p>\n
*Watch this amazing video released by NASA today \u2013 WE ARE THE EXPLORERS*<\/p>\n
(Images: Via L2 content from L2\u2019s 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 ULA, NASA)<\/p>\n
(L2 is \u2013 as it has been for the past several years \u2013 providing full exclusive SLS coverage. To join L2, click here: http:\/\/www.nasaspaceflight.com\/l2\/)<\/p>\n","protected":false},"excerpt":{"rendered":"
The debut of the Space Launch System (SLS) will send the Orion (MPCV) on a 7-10 day mission to the Moon, with an aim to qualify the Heavy Lift Launch Vehicle (HLV) and Beyond Earth Orbit (BEO) Orion to carry humans into deep space. Exploration Mission 1 (EM-1) involves sending Orion around the far side […]<\/p>\n","protected":false},"author":1,"featured_media":30475,"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":[3718,9034,2222,625,640,624],"class_list":["post-40190","post","type-post","status-publish","format-standard","has-post-thumbnail","hentry","category-news","tag-em-1","tag-hlv","tag-icps","tag-moon","tag-orion","tag-sls"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40190"}],"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=40190"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/40190\/revisions"}],"wp:featuredmedia":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media\/30475"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=40190"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=40190"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=40190"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}