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<\/font>**ARES I \/ ORION LIVE UPDATE PAGES**<\/font><\/em><\/p>\n **ARES V \/ Mars Transport Vehicle (MTV) LIVE UPDATE PAGES**<\/font><\/em> <\/p>\n <\/font><\/p>\n Before the award of the multi-billion dollar Orion contract to Lockheed Martin, NASA\u2019s CPAS Project \u2018stood-up to develop an in-house parachute solution,\u2019 alongside those designed by companies associated with the contractors bidding to build the CEV (Crew Exploration Vehicle).<\/font><\/p>\n Following Lockheed Martin\u2019s continuation with developing their parachute system, NASA kept their CPAS option alive, putting it through a trade study, before comparing with Lockheed Martin\u2019s alternative version. However, a \u2018reconciliation period closed without resolution,\u2019 noted the CPAS presentation.<\/font><\/p>\n While the NASA and Lockheed Martin systems stay true to the requirements they are designed for, there are a number of differences between them, from the materials used, to even the number of main parachutes proposed.<\/font><\/p>\n The NASA CPAS system uses a Parallel (both at the same time) Drogue Deployment method, with the three main parachutes extracted by mortar. NASA\u2019s material choice is Vectran\/1.1 oz Nylon Broadcloth. Terminal velocity is rated at 25 ft\/s nominal, 29 ft\/s 1 chute out.<\/font><\/p>\n Spacecraft\/Crew Survivability notes that the system \u2018can go directly to mains independent of drogue performance. Ability to handle skipped reefing stages. \u2018Empty Confluence\u2019.\u2019<\/font><\/p>\n <\/p>\n The Lockheed Martin system uses the Serial (primary w\/ back-up) Drogue Deployment method, with four main parachutes, extracted by the drogue parachutes. M5\/0.7 oz Nylon Broadcloth, is Lockheed Martin\u2019s material of choice, but has the drawback of not being commercially available at present. Terminal velocity is rated at 28.5 ft\/s nominal 35 ft\/s 1 chute out.<\/p>\n <\/font><\/p>\n \u2018Can survive failure of two main with terminal velocity of 42 ft\/sec (assumes landing system, seats and crushing structure). Retro Confluence,\u2019 is listed as Lockheed Martin\u2019s system \u2018Spacecraft\/Crew Survivability.\u2019<\/font><\/p>\n Sources claim the decision on the parachute system that will be baselined into Orion was expected last month, but no official announcement has been made. While that decision is believed to be imminent, NASA\u2019s CPAS presentation points to their own system being the preferred option.<\/font><\/p>\n \u2018Project\/Lockheed Martin moving forward with both configurations. Very clear both Project and LM see advantages of CPAS config,\u2019 noted the NASA CPAS presentation. \u2018Desire better understanding (quantitative) of system-level mass and S&MA effects Project baselined NASA recommended configuration (3-chute) for long-lead development.\u2019<\/font><\/p>\n Actual testing of relating parachute system technology has been on-going since last year, mainly at the US Army ranges in Yuma, Arizona, but there\u2019s a long way to go until the system gains a real test scenario, with the Pad and Ascent Aborts in 2009. <\/font><\/p>\n \u2018Parachute Test Vehicle in development. Pilot drop tests: Jan-Mar \u201907. Drogue drop tests: Mar-Nov \u201907. Single Main drop tests: May-Oct \u201907. Cluster drop tests: Nov \u201907 \u00e2\u20ac\u201c Apr \u201908. Pad Abort-1: Jan \u201909. Ascent Abort-1: May \u201909,\u2019 noted the presentation.<\/font> <\/i><\/em><\/p>\n <\/p>\n <\/font> <\/p>\n Vehicle interfaces for the DAC 1C version of Orion Ares \u2013 Jan 3. Ares I-1R Test Flight Plan (full outline) Presentation. Ares I-1 timeline and modification expanded info. Ares I troubleshooting latest. Ares I Reference Trajectory. Boeing\u2019s STS to Ares \u2013 Lessons Learned Presentation. Latest Ares I and Ares V baseline Configuration image and data. CLV DAC-1C (Changes to CLV Upper Stage). <\/p>\n <\/font><\/p>\n Ares I-1: 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. Constellation news updates. ATK figures on the 5-Seg Booster weight for CLV. CEV-CLV Design Analysis Cycle Review (DAC-2) Presentation. Constellation SRR updates. CLV Stick \u2013 Troubleshooting\/Alternatives\/Updates. New CEV Images (include abort mode). 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\u2026plus more.<\/font><\/p>\n <\/i><\/em><\/p>\n <\/i><\/em><\/em><\/p>\n <\/em> **NASASpaceflight.com Job Opportunities**<\/em><\/font> <\/em><\/font><\/p>\n <\/em><\/font> NASA and Lockheed Martin are moving forward with their respective proposals for the all-important parachute systems for the Orion spacecraft. NASA, which is set to replace the space shuttle in or around 2014 with Orion, has so far failed to decide on a CEV Parachute Assembly System (CPAS). A summary presentation delivered recently to both […]<\/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-41819","post","type-post","status-publish","format-standard","hentry","category-news"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/41819"}],"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=41819"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/41819\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=41819"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=41819"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=41819"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}
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\n<\/font><\/p>\nThe systems have two purposes to fulfil, one being a launch abort scenario, which would require the Orion to be pulled free from the failing Ares I vehicle during an abort, splashing down near the Kennedy Space Center (KSC). The other being the normal re-entry scenario of returning to terra firma at the designated landing site \u2013 which will initially be either Edwards Air Force Base, California, or White Sands, New Mexico.<\/font><\/p>\n
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L2 Resources For Ares I, V and Constellation:
Orion Launch Abort System (LAS) overview presentation \u2013 Jan 16. Major changes to Ares I Upper Stage \u2013 expansive details and data. Ares I\/Orion CxP 72031 Requirements Validation Matrix Information. Saturn Twang Test Video for use with Ares I-1R. CLV Umbilical Trade Matrix XLS. <\/font><\/p>\n
<\/font><\/p>\n90 Minute Video of Constellation all hands meeting. CLV TIM Meeting Information. CLV\/CaLV Infrastructure, Timelines and Information. Escape System Trade Study Presentation.<\/font><\/p>\n
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