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**The most comprehensive collection of Shuttle, Ares, Orion and ISS related presentations and mission documentation, plus expansive daily processing documentation and updates are <\/em>available to download on L2<\/em> **<\/em><\/p>\n **ARES I LIVE UPDATE PAGES**<\/em><\/p>\n **ORION\/Exploration Vehicles LIVE UPDATE PAGES**<\/em><\/p>\n **ARES V \/ Mars LIVE UPDATE PAGES**<\/em><\/p>\n **EXPLORATION ALTERNATIVES (DIRECT, EELV) PAGES**<\/em><\/p>\n **ALL NASASpaceflight.com CxP Articles**<\/em><\/p>\n Technology News (adsbygoogle = window.adsbygoogle || []).push({});<\/p>\n Orion\u2019s Development Background:<\/em><\/p>\n While the public face of the Constellation Program (CxP) continues to be driven via overly-positive statements on the current state of progress, the reality of their own documentation points to Ares I causing turmoil in Orion\u2019s development over these opening years of the design phase.<\/p>\n Design issues for any new vehicle are to be expected, and correctly represented by the often-used comment of \u2018if there weren\u2019t problems, we wouldn\u2019t need engineers.\u2019 However, Orion\u2019s short life on the drawing board has been an unhappy childhood.<\/p>\n The vast majority of Orion\u2019s design changes have been driven by Ares I\u2019s shortcomings \u2013 via performance and mass issues \u2013 to ably inject the vehicle into orbit. The fact that the Ares I now has several thousand pounds of reserve mass properties negates the suffering it has brought on the vehicle it is designed to serve.<\/p>\n Those penalties Orion had to endure could be seen at the very start of its design process, when the Crew Exploration Vehicle (CEV) reduced in size by 0.5 meters in diameter, soon followed by Orion having its Service Module stripped down in size and mass by around 50 percent.<\/p>\n \u2018Mass savings\u2019 would become one of the most repeated terms surrounding the Orion project.<\/p>\n In July, 2007, NASA sent another set of requirements to Orion\u2019s contractor Lockheed Martin, culling the amount of propellant the vehicle would carry on International Space Station (ISS) missions, in order to bring its weight down.<\/p>\n Efforts to return to land landings are continuing, but only via a reduced airbag system that has smaller mass penalties. Design challenges are also highlighted via the alternative option, and water landings remain baselined.<\/p>\n October, 2007, saw one \u2018final\u2019 major push to deal with mass savings on Orion, to such an extent Ares I would eventually gained several thousand pounds of reserve mass \u2013 something which is now often mentioned in press materials as a sign of how well Ares I development is progressing, without mentioning Orion\u2019s sacrifices.<\/p>\n This latest mass saving process was known as the Zero Base Vehicle (ZBV) effort, as the focus switched to the Lunar version of Orion. During the ZBV process, the vehicle underwent a \u2018scrubbing\u2019 to a minimum weight, ahead of the reapplication of some of the deleted capability.<\/p>\n Already some issues between the Constellation related departments were starting to show, with an All Hands meeting notes referencing the need for \u2018teamwork and chemistry\u2019 as the way forward through the design efforts.<\/p>\n \u2018Failure is an option during development,\u2019 Ares program leader Steve Cook noted at the program-wide All Hands meeting. \u2018We are willing to take calculated risks to further our knowledge.\u2019<\/p>\n \u2018The CEV Project faces some very real challenges and difficult decisions will need to be made,\u2019 Constellation Program\u2019s Bob Armstrong warned, as the vehicle came out of its System Definition Review (SDR) Board meeting, with the most significant issue classed as controlling spacecraft weight to match Ares I performance.<\/p>\n Aiding the process, Orion gained a new \u2018bullet cover\u2019 aerodynamic fairing, to assist Ares I\u2019s first stage performance, while the Launch Abort System (LAS) also received mass savings.<\/p>\n The result of the ZBV process then moved into the \u2018buy back\u2019 phase, where some of the lost capability \u2013 based on critical requirements \u2013 was added back on to Orion. This was carried out by the Orion Vehicle Engineering Integration Working Group (OVEIWG).<\/p>\n Ares I didn\u2019t leave all of the mass and performance problems on Orion\u2019s doorstep, with trade studies initiated on a larger nozzle ratio to increase performance \u2013 now confirmed for the Lunar missions \u2013 added to evaluations into the potential expendability of the first stage, classed as potentially resulting in a 3,000lbs mass saving.<\/p>\n 2008 opened with a motivational speech from legendary Flight Director Gene Kranz, sent in a heavily produced video to the Constellation workforce.<\/p>\n \u2018Our learning curve, as we went through Mercury, Gemini and Apollo was very steep. With Mercury we learned of leaders and leadership \u2013 leaders must have integrity, they are up front, they challenge the team to accomplish their mission,\u2019 Kranz noted.<\/p>\n \u2018We also learned a lot about ourselves with Mercury, as a lot of us came in from aircraft testing, with egos as big as the room we worked in. We had to learn to leave our egos at the door and become a team, so we became one.\u2019<\/p>\n Two major problems would cause headaches within CxP soon after, relating to budget shortfalls for the Constellation Program, and the realization that Thrust Oscillation on the Ares I First Stage required a major mitigation effort \u2013 in order to ensure the safety of the crew riding in Orion.<\/p>\n The shortfall in funding eventually led to the decision to delay a number of key launch milestones by up to a year, with Constellation manager Jeff Hanley pre-empting the official announcement with a note of confidence that the gap between shuttle and Orion would not breach five years \u2013 citing Orion 2\u2019s first manned launch in March 2015, even though the first ISS crew rotation would not happen until a year later on Orion 4.<\/p>\n The funding shortfall also has major impacts on the Upper Stage test schedule, with numerous elements of \u2018required\u2019 testing now gutted out of the schedule. Some major test requirements have now been deferred to when the hardware first flies on Ares I-Y, which is deemed by sources as \u2018increased program success risk\u2019. (article will follow this month, documentation on L2). Thrust Oscillation is created by solid rocket motors, its mitigation process has evolved, via many options, and the engineers have a plan. However, like a Battlestar Galactica plot twist, all is not as straightforward as per recent comments on the post Ares I PDR media briefing.<\/p>\n Had NASA taken the recommended plan to counter TO, Ares I\u2019s PDR would have been delayed \u2013 as confirmed in Lockheed Martin documentation on L2, which claims the requirement of Crew Seat Isolation hardware will reappear via a \u2018Change Request\u2019 (CR) in 2009.<\/p>\n \u2018Option 1 \u2013 Isolation plane at FS\/US + isolation plane at US\/SM + passive Tuned Mass Absorbers (TMA) to aft skirt. Option 2 (SELECTED) \u2013 Isolation plane at FS\/US + passive (now active) TMAs in aft skirt + Orion crew isolation,\u2019 notes the documentation. \u2018Option 3 \u2013 Isolation plane at FS\/US + active RCS counter pulse firing (48 jets). Option 4 \u2013 Isolation plane at FS\/US + active hydraulically powered TMAs in aft skirt.\u2019<\/p>\n Lockheed Martin (Orion) disagreed with NASA\u2019s recommendation, asking NASA to instead move forward without affecting Orion\u00e2\u20ac\u2122s\u2019 design process, given the Crew Seat Isolation design was too immature to be added to the vehicle in time for the PDR\u2019s review of TO.<\/p>\n \u2018NASA recommends that Program pursue Option 2, but with full knowledge of Orion impacts,\u2019 the documentation notes. \u2018Lockheed Martin\u2019s recommendation is to have Ares pursue Ares Thrust Oscillation Mitigation solutions within the Ares Project and not adversely effect Orion\u2019s design.<\/p>\n \u2018Option 2 includes Orion isolating the crew response from 1g to 0.25g (required) and addressing design changes. TO requirement levied results in PDR IMPACT!\u2019<\/p>\n While Constellation managers initially claimed that the third mitigation option of Crew Seat Isolation \u2013 added to the \u2018shock absorbers\u2019 on the aft skirt, and the Isolation plane (dampers) in the interstage \u2013 wasn\u2019t required, the latest media briefing back-tracked slightly, claiming it is still being worked on as a back-up option.<\/p>\n However, the documentation shows that Orion\u2019s mitigation option has simply been deferred, in order to avoid causing a delay to the recent Ares I PDR. It will then return to the table in time for the Delta PDR on Thrust Oscillation in 2009, which by then the Crew Seat Isolation option will have matured enough to be viable as a mitigation option.<\/p>\n \u2018NASA CxP leverages Thrust Oscillation requirements on Orion design, which would result in the following options. Orion accepts the CR (Change Request) resulting in a delay to PDR (eliminates confusion on baseline design and TO assessment studies),\u2019 added Orion documentation.<\/p>\n \u2018SELECTED: Orion proceeds forward with current design to PDR and then a CR is put in place, and a Delta PDR is scheduled to address the TO changes (delays TO work until FY09).\u2019 The Delta PDR has been confirmed for the middle of 2009.<\/p>\n Thanks to the vast array of mass shedding activities noted in the first half of this article, such a mass hit can be easily swallowed by the integrated Ares\/Orion vehicle. However, Lockheed Martin are unhappy with the constant changes to the requirements and the design of Orion that result from such activities.<\/p>\n That frustration has come out via a reaction to an apparent \u2018concern\u2019 NASA has with the quality of Lockheed Martin\u2019s latest filed version of Orion (606C).<\/p>\n \u2018NASA has expressed concerns with 606C model and quality,\u2019 the documentation noted. \u2018Community must understand that there has not been two consecutive deliveries with the same baseline design, because (of) multiple configuration changes (prior to PDR on a non-consistent design).\u2019<\/p>\n This may also be responsible for the delay in Orion\u2019s own PDR, which was due in November. Managers have since confirmed that the PDR has been delayed \u2013 though sources not the delay could be as wide-reaching as between six months and even a year.<\/p>\n The primary reason is understood to be the requirement of an additional DAC (Design Analysis Cycle).<\/p>\n L2 Members: Refer to TAG keywords \u2018Ares I\u2019 \u2018Orion\u2019 and \u2018TO\u2019 for updates and expansive presentations. All quotes in the article above are from L2 content.<\/em><\/p>\n Ares I-X Full Vehicle Design Slides. Upper Stage Testing Changes and Impacts Presentations. Orion position on Ares and TO. Ares I TO Mitigation Plans and Notes. Ares V Frabrication Hardware Presentations and Photos. Ares V Point of Departure Presentation. Orion WEST in NBL Hi Res and Notes. 8th Floor News Updates. Ares V Alternative Engine Arrangement Presentation. Hi Res CxP Logos. Full (and very expansive) set of presentations on Ares\/Orion mass and status report. Ares I \u2018Parasorber\u2019 TO migitation hardware presentation and animation. Ares I TO Risk Slides. Ares I Risk Status. <\/em><\/p>\n Hi Res Images of Ares I FS Parachute Test Vehicle (JDTV). 20mb of new Lunar Images of Chariot, Athlete and Lunar Crane. Ares I KSC Processing Master Book \u2013 184 pages.<\/em> Changes for Ares I-X (Images). PRCB Transition Presentation (Shuttle to Ares). Ares V (5.5\/6xRS-68) Presentation (and more). Orion Parachute Vehicle Images. Latest Risk Matrix for Ares. SI Unit Directive Document. CxP PMR08 Manifest. PDR and associated notes from CPCB meeting. Orion Parachute Test Vehicle (PTV) Photographs. <\/em><\/p>\n 110mb worth of Ares I-X Weekly Test Presentations (Ares I-X, J2-X etc. up to end of April) The Orion LIDS (Low Impact Docking System) Section (Images, Videos, Engineering Notes). Hi Res Images of Ares I in the VAB. Ares I-X Integrated Milestone Charts. Ares I Thrust Oscillation Focus Team Status Presentations (over 50mb \u2013 includes DTO on Shuttle missions), Ares I-X Global Buckling Status Presentation, Ares I \u2013 Launch Pad Stabilization and Damping Presentation, Ares I: Purge\/Vent\/Drain and Vehicle Access Presentation.<\/em><\/p>\n Ares Tilt Up Umbilical Arm (TUUA) Test \u2013 Video, Ares\/Orion Comm and Tracking Presentation, Ares I Nozzle Extension Update Presentation, Ares\/Orion Integrated Stack TIM Summary (Major Issues) Presentation, Orion Land vs Water Landing Update + Crew Survival (post 36 hrs) Presentations.<\/em><\/p>\n Orion Rendezvous with the ISS CGI Video, plus AERCam Inspections. Ares I Thurst Oscillation Update Section. Images of completed PA-1 boilerplate Command Module at LaRC. CxP Planning for Architecture Closure \u2013 Feb 19. Ares V Overview Presentations. Other Major CxP Updates for Feb (List restricted to L2). Lunar Habitat Assembly. PRCB Presentations on hardware and infrastruction transition (from Palmdale to MLP Park) \u2018Follow live\u2019 Lightning Towers Construction images. Latest Mobile Launcher details. Orion\/Ares I\/Delta IV Heavy NEO Feasibility Study (Video). Constellation EVA Study Presentation. Superb Gene Kranz address to CxP workforce (Apollo to Orion feature) video. MOD \u2018LEO to Mars\u2019 presentations.<\/em><\/p>\n Superb Ares I Launch Ascent, Pad Abort Test CGI Videos (three). Integrated Stack (IS) Technical Interchange Meeting (TIM) notes \u2013 Nov 6 to Nov 15. The full \u20188th Floor News\u2019 \u2013 Constellation Update (performance issues) \u2013 Nov 5. Ares I Mobile Launcher PMR.<\/p>\n <\/em>Presentation of Ares\/Orion impacts relating to Shuttle manifest acceleration. Ares I Interstage diagrams. Ares V Super Crawler. Ares I Launch Pad images (ML etc.) Hi Res images of Ares I-X Upper Stage. Orion 606-7 Data Updates. Updates Constellation launch schedule through to Orion 15. Orion Seat test photos. New ML Graphic and info. New Ares V graphic and baseline data. Large collection of hi res Orion paracute drop tests. SIX Part Series of Ares I Upper Stage Graphical Overviews. DAC-1C DDD Vast Slides on Vehicle Design. ATK First Stage Presentation. 39B Lightning Towers Slides. DAC-1C Departure points to DAC-2 Upper Stage Graphcs (Many Changes).<\/em><\/p>\n <\/em>Orion\/CEV Display Layout Presentation (40 pages). ATK figures on the 5-Seg Booster weight for CLV. Weather Shield (Rain Shield) for Orion on the pad. New Super hi-res images of Ares I. ATK Cutaway graphics of Ares I \u2013 perspective and axonometric. Ares I\/Orion CxP 72031 Requirements Validation Matrix Information. CEV Paracute Assembly System (CPAS) Presentation.<\/em><\/p>\n <\/em>Orion Launch Abort System (LAS) overview presentation. Changes to Ares I Upper Stage \u2013 expansive details and data. Ares I\/Orion CxP 72031 Requirements Validation Matrix Information. CLV Umbilical Trade Matrix XLS. Vehicle interfaces for the DAC 1C version of Orion Ares. Ares I-X Test Flight Plan (full outline) Presentation. Ares I-X timeline and modification expanded info. Ares I Reference Trajectory. Boeing\u2019s STS to Ares \u2013 Lessons Learned Presentation. CLV DAC-1C (Changes to CLV Upper Stage).<\/em><\/p>\n <\/em> <\/em><\/em><\/p>\n <\/em><\/em><\/em>90 Minute Video of Constellation all hands meeting. Escape System Trade Study Presentation. CEV-CLV Design Analysis Cycle Review (DAC-2) Presentation. Flight Design and Dynamics Division CEV update. CLV Mono-propellant RCS system. CEV pressurisation system review. CLV\/CEV Configuration Images. The 2\u00d73 Seg SRB Crew Launch Vehicle Option Presentation\u2026<\/em><\/p>\n <\/em>\u2026.plus much more (L2 Constellation over 220gb in size).<\/em><\/p>\n","protected":false},"excerpt":{"rendered":" Lockheed Martin\u2019s design efforts on the Orion vehicle are being hindered by Ares I driven requirements, documented notes claim, with concerns ranging from the constant design changes, to Thrust Oscillation (TO) mitigation requirements. With Crew Seat Isolation efforts deferred until next year \u2013 in order not to delay the recent Ares I PDR (Preliminary Design […]<\/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":[9198,9244,8184],"class_list":["post-41310","post","type-post","status-publish","format-standard","hentry","category-news","tag-ares","tag-cev","tag-sls-orion"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/41310"}],"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=41310"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/41310\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=41310"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=41310"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=41310"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}<\/em>All of this article is based on documented L2 information. For an overview of how L2 works, <\/em>**click here for sample video**<\/em><\/p>\n
A month later, the fallout on Orion continued with the decision to move to water landings, due to the requirement to lose yet more mass from the vehicle \u2013 this time the airbag landing system \u2013 a move first denied, but now confirmed as implemented.<\/p>\n
A separate effort \u2013 now under a special \u2018management\u2019 budget \u2013 is continuing on the MLAS (Max Launch Abort System), although this is now known to be based around a Human Rated Ares V back-up option, with MLAS being the only LAS system that would fit inside the Vehicle Assembly Building (VAB) due to the height of Ares V.<\/p>\n
\nThrust Oscillation and an unhappy Orion:<\/em><\/p>\nAs to the design of the Crew Seat Isolation hardware, three possible approaches are open to engineers: \u2018Isolation of individual seats (via springs or flexures). Isolation of entire seat pallet. \u2018Clean Sheet\u2019 Active CIAS Pallet Isolation design. Isolation system mass about 200 lb for both passive approaches and upwards of 500 lbs for an active system.\u2019<\/p>\n
Selection of L2 Resources For Ares I, V and Constellation (some not listed):<\/em><\/p>\n
Altair Overview Presentation. Ares I Risks and Status. Ares I-X Booster Recovery Images and Video. Ares I-X Pad Images. Ares I-Y Mission Overview Video (50mb \u2013 Superb). Orion Lunar Transit CGI Video. (Several more videos, including first video of Orion splashdown). <\/em><\/p>\n
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\nOrion 607 Overview Presentation (Jan 08), Constellation Program Status\/Budget and new Manifest to Orion 20 Presentation (Jan, 08). Michoud Transition to Ares I\/V (Jan 17, 08). Several MLAS (Max Launch Abort System) Presentations. Over 60 Hi Res Images of Orion Mock-up at JSC (Hatch, Seats, Flight Deck) \u2013 December. <\/em><\/p>\n\u2018Proposed\u2019 Ares I SRBSF (Mini VAB) and graphic. LSAM (LDAC-1) Video and Images. Several Constellation All Hands Videos and Presentations. Ares I Pad Rollercoaster (Old and New presentation and slides \u2013 the very cool \u2018CGI ride on the Ares pad coaster\u2019 video. Ares I VAB \u2018In-Line\u2019 Stacking presentation slides.<\/em><\/p>\n
Ares I-X: Four Seg+Dummy \u2018Tuna Can\u2019 stage. Ascent Developmental Flight Test Presentation. CLV Pad 39B Handover Info and Latest. New images of CLV on top of new MLP and LUT. Lockheed Martin CEV\/Orion Updates. ATK figures on the 5-Seg Booster weight for CLV.
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