**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><\/font> **<\/em><\/font><\/p>\n **ARES I LIVE UPDATE PAGES**<\/font><\/em><\/p>\n **ORION\/Exploration Vehicles LIVE UPDATE PAGES**<\/em><\/p>\n **ARES V \/ Mars LIVE UPDATE PAGES**<\/font><\/em><\/p>\n **EXPLORATION ALTERNATIVES (DIRECT, EELV) PAGES**<\/u><\/em><\/p>\n Technology News (adsbygoogle = window.adsbygoogle || []).push({});<\/p>\n **ALL NASASpaceflight.com CxP Articles**<\/font><\/p>\n Ares I TO Latest:<\/u><\/em><\/p>\n Thrust Oscillation is not a unique condition in relation to Ares I \u2013 but a recognized characteristic of solid rocket motors \u2013 in Ares I\u2019s case, the five segment first stage.<\/p>\n The problem relates to the crew riding Ares I inside their Orion vehicle \u2013 when pressure oscillations drive resonant modes in the vehicle structure. These oscillations are capable of rendering the astronauts incapacitated, or worse.<\/p>\n Since the condition with Ares I was found last year, a Tiger\/Focus team have been working on down selecting mitigation options. However, the latest documentation shows the main focus remains on \u2018researching\u2019 the condition\u2019s relation to Ares I and associated processes towards mitigation. <\/p>\n \u2018Mitigation Plan: Detailed research (this is research, not mitigation) plan for the TO risk is managed by the MSFC (Marshall Space Flight Center) TOFT (Thrust Oscillation Focus Team),\u2019 noted documentation dated July 10.<\/p>\n \u2018The plan contains multiple parallel tasks, with complicated interdependencies. Plan does not \u2018buy down\u2019 risk because it is research, not mitigation. Assessment of parallel paths on risk level is ongoing and may result in reduced risk as plan is executed.\u2019<\/p>\n The documentation shows 10 elements being worked on research, all of which are 5\u00d74 (likelihood x consequence) \u2018RED\u2019 risks. These 10 \u2018siblings\u2019 are unable to breach 5\u00d74 on the risk matrix, as the parent element \u2013 in this case Thrust Oscillation itself \u2013 is always one level higher, meaning it is currently seen as a full 5\u00d75 risk. <\/p>\n Sources claim 5\u00d75 program risk is only managed by Level 1 Management, due to its risk to the program overall. However, this will have to be reduced as data is gathered to finalize a mitigation option.<\/p>\n Data gathering via actual flight hardware is set to begin with STS-125 \u2013 with sensors believed to have been added to Atlantis\u2019 boosters, though this is still unconfirmed. Three downstream flights will have TO related data gathering DTOs (Detailed Test Objectives) \u2013 as confirmed in mission baseline documentation.<\/p>\n At present, two mitigation options are gaining a large amount of attention (Active Thrusters and the Parasorber concept) \u2013 likely added in combination with a third (Crew Seat Isolators). <\/p>\n<\/p>\n <\/u><\/i><\/b><\/p>\n Liquid Thrusters On A Solid First Stage:<\/p>\n<\/p>\n \u2018Active Pulse Thrusters (RCS TO Damper) \u2013 could provide 10X reduction in TO. Relatively mature thruster design. Self contained. Relatively mature control system,\u2019 noted the first appearance of the concept on TO mitigation documented. <\/p>\n Now matured to an even more elaborate system, the concept calls for four 7,500lb thrust Orbital Maneuvering \u2013 type \u2013 Engines (OME) firing upwards, with another four more firing downwards. <\/p>\n The outcome would be 30,000lbs thrust, in both directions, creating a reduction in what is understood to be around 38,000lbs of Thrust Oscillation related forces, reduced to an acceptable level for the astronauts on board.<\/p>\n The current concerns noted with this system relates to the 1.17m diameter thrusters \u2013 protruding out of the aft skirt \u2013 being impacted by supersonic flows during first stage. Sources note that they could be sheared off during ascent.<\/p>\n The OMEs would also require a large scale redesign to their valve systems to allow for the required reaction and pulsing rate. They would also \u2013 based on their mass alone \u2013 add a major mass impact to Ares I\u2019s payload capability. <\/p>\n \u2018Performance and aft skirt design challenge: (around) 500 lbm (pounds mass) payload impact,\u2019 added documentation on the original APT design \u2013 which has since been refined and likely now heavier. \u2018Trade required for separation and booster deceleration. Add failure modes. Must survive aft skirt environments.\u2019<\/p>\n Added to the impact on Ares I performance \u2013 which is struggling regardless \u2013 additional failure modes would hit Ares I\u2019s LOC\/M (Loss of Crew\/Mission) numbers.<\/p>\n Other options based around the same concept \u2013 though not documented \u2013 speak of various designs, one of which is noted to consist of a larger number of smaller thrusters \u2013 up to 16 to 20 in total \u2013 firing through the worst part of TO concerns (around 11 seconds of first stage flight). <\/p>\n That concept is still undecided on whether the thrusters would fire in either direction, or \u2013 given its small role during over two minutes of first stage flight \u2013 it would be used in tandem with another mitigation option.<\/p>\n Parasorber Concept:<\/u><\/i><\/b><\/p>\n One of the early favorites as a mitigation option has since been refined into what is being called the \u2018Parasorber\u2019. This concept appears to be a progression on the Tuned Mass Absorber (TMA) concept shown in earlier documentation.<\/p>\n \u2018Three main parachute packs (green) with hard covers (blue) connected to MPSS (Main Parachute Support System) via frames (grey),\u2019 outlined the design in one United Space Alliance (USA) presentation. <\/p>\n \u2018Packs are free to travel up and down on linear bearings connecting the frames to the connecting the frames to the MPSS panels (light blue). The frames are suspended by springs as well as damped.\u2019<\/p>\n The concept assumes a 4 inch gap between MPSS panels and Main Parachute pack. However, testing on Ares I-X doesn\u2019t appear viable, as the test vehicle has no such gap in its MPSS design.<\/p>\n \u2018Damper and spring form will be determined by spring and damping constants derived from analysis,\u2019 added the presentation. \u2018Frame form will be determined by predicted loads.\u2019<\/p>\n How far down the line the Parasorber has matured from the TMA is not noted. However, given it is a passive system, the mass impacts will be far less than the other option of an active (powered) system.<\/p>\n It will also have to achieve higher than the previously documented 2x reduction on TO, which was originally classed as a reduction in loads good enough for the health of the astronauts, but not below the limits required for crew performance.<\/p>\n \u2018Tuned Mass Absorber: Use existing mass to counterbalance TO: 2X reduction for passive system, 3X reduction for active system. Payload impact less than other concepts,\u2019 noted the previous TMA documentation.<\/p>\n \u2018Immature design: May create problems for First Stage recovery system. Active control design is immature. Reduces loads to well below human health limit, but not performance limit. Adds failure modes.\u2019 <\/p>\n Crew Seat Isolators:<\/u><\/i><\/b><\/p>\n With the likely addition of Crew Seat Isolators in tandem with any down selected mitigation approach, further gains in reducing the loads will be forthcoming.<\/p>\n Aiding both data collation and how much isolation can be gained, STS-119 \u2013 Discovery\u2019s flight to the International Space Station (ISS) in February 2009 \u2013 is carrying out a special DTO for the Constellation program.<\/p>\n \u2018Constellation Program (CxP) has requested OPO (Orbiter Project Office) to implement a DTO to gather launch vibration data. DTO will be done in conjunction with a DSO to record astronaut visual performance to aid in CxP unimpeded crew performance specification development,\u2019 noted the documentation. <\/p>\n To perform this DTO, three Mission Specialist seats will be outfitted with triaxial accelerometers. After recording data during launch, the accelerometers will be removed and stowed during the post-insertion timeline.<\/p>\n \u2018Astronaut records visual function from middeck locker mounted card and other symptoms during launch profile,\u2019 noted the text byline associated with the graphic.<\/p>\n The Space Shuttle Program (SSP) is currently planning two additional Thrust Oscillation DTOs on STS-127 and STS-128, though the Constellation Program have been quick to send out a memo to disassociate this as a test for Ares, even though it is.<\/p>\n \u2018Removing DTO wording regarding that it\u2019s for Constellation. Will just say that it\u2019s a DTO, what it\u2019s for, who is responsible for funding, and what safety boards the DTO will go through for certification,\u2019 noted the memo, pointing to Constellation avoiding the costs of the DTOs.<\/p>\n No documentation on the Isolators themselves has been created at this time, with data gathering the primary requirement prior to a design for the seats on Orion. <\/p>\n Other non-hardware options are believed to still be under evaluation \u2013 such as the Castletop Inhibitor \u2013 though no mention has been made of these other options for some time now.<\/p>\n 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. <\/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.<\/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 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). <\/i><\/em><\/p>\n 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. <\/p>\n 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). <\/p>\n 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<\/p>\n \u2026.plus much more (L2 Constellation over 190,000mb in size).<\/p>\n","protected":false},"excerpt":{"rendered":" Engineers tackling one of the biggest issues with Ares I, namely Thrust Oscillation, are understood to be currently favoring either adding the \u201cParasorber\u201d concept, or a set of pulsing thrusters \u2013 firing in either direction during first stage flight \u2013 to the aft skirt, along with Crew Seat Isolators. With the July status of the […]<\/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":[],"class_list":["post-41347","post","type-post","status-publish","format-standard","hentry","category-news"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/41347"}],"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=41347"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/41347\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=41347"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=41347"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=41347"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}<\/em><\/font>All of this article is based on documented L2 information. For an overview of how L2 works, <\/em>**click here for sample video**<\/em><\/font><\/p>\n
Also known as \u2018Resonant Burning\u2019 \u2013 described as vortices that shed within the solid rocket motors during combustion due to the shearing of internal flow at propellant discontinuities \u2013 the issue relates to when the frequency of thrust oscillations is coincident with the acoustic modes of the motor cavity. <\/p>\n
Originally noted as Active Pulse Thrusters (ATP) \u2013 see image of ATP left hand side \u2013 this system would lead to a very different appearance of the aft skirt on the bottom of the first stage. <\/p>\n
Based around the Ares I First Stage recovery parachutes, this concept\u2019s main negative points \u2013 as with the TMA \u2013 relate to the added weight that will make recovery of the first stage more difficult \u2013 added to the center of gravity moving farther forward.<\/p>\n
The concept is reasonably simple, with a frame suspension \u2013 consisting of guide rails, springs and a damper system \u2013 mounted on a square frame connected to the MPSS panel. The concept currently shows \u2013 via an animation \u2013 8 inches of travel during first stage flight.<\/p>\n
Graphics associated with the DTO also appear to show that astronauts will carry out an eye sight test \u2013 placed in front of them on the wall of the middeck \u2013 during the ride uphill. <\/p>\n
Selection of L2 Resources For Ares I, V and Constellation: <\/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). <\/p>\n
<\/em>
Orion 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. <\/p>\n