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National Advanced Leadership Course

by: Missouri McClure

National Advanced Leadership Course MS 489

Marketplace > University of Idaho > Military Science > MS 489 > National Advanced Leadership Course
Missouri McClure
GPA 3.98


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Class Notes
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This 21 page Class Notes was uploaded by Missouri McClure on Friday October 23, 2015. The Class Notes belongs to MS 489 at University of Idaho taught by Staff in Fall. Since its upload, it has received 29 views. For similar materials see /class/227895/ms-489-university-of-idaho in Military Science at University of Idaho.

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Date Created: 10/23/15
Development of Inflatable Entry Systems Technologies Charles J Player NASA Langley Research Center Exploration Systems Engineering Branch CharlesJPla er nasa ov 7578647785 3711 International Planetary Probe Workshop Anavyaaoa Attica stem June 27 a July 1 2005 e Acknowledgements Coauthors IATD Neil Cheatwood JSC Jim Corliss Claude Graves PI IRVE Chris Madsen PM LaRC ARC Steve Hughes Don Ellerby PM Brett Starr WFF Mike Lindell Libby West PM Ryan Stephan Charlie Hyde Robert Dillman Neal Hass WFF Libby West PM ILC Dover 3rd internatronai Planetary Probe Workshop Anavyaaoa Attrca Greece June 27 a July 1 2005 Overview Why an Inflatable Aeroshell Current LaRC Inflatable Aeroshell Projects IRVE IATD Proposed Inflatable Aeroshell Projects Analysis amp Capabilities Development Overall Technology Development Plan 3rd imernazronai Pianezary Probe Workshop Anavyssos Amos Greece June 27 7 July 1 2005 Why an Inflatable Aeroshell Advantages over rigid aeroshell DeflatedStowed the aeroshell is a small modular component thereby allowing Increased payload volume fraction in the launch vehicle shroud Access to the payload afterthe launch vehicle integration System duplication between the cruise stage and entry vehicle Delivery of more payload mass to the surface Inflated the aeroshell can achieve sizes much largerthan those attainable by rigid aeroshells allowin Rapid highaltitude deceleration for access to high altitude landing sites A less hazardous thermal environment for the total entry system Technical Challenges Flexible Structure Unpredictable drag performance Aero structural dynamic instability Durability Reliability Aerothermal heating 3rd internatronai Planetary Probe Workshop Anavyaaoa Attrca Greece June 27 a July 1 2005 altitude km Direct Ballistic Entry 6kms 2200kg Entry Mass 13N 270 longitude landing site g u I 7 492m dial15m nose radius l 150m dia 658m nose radius 15m In atable 70deg SphereCone 4572m dia 150mdia I 0 5 10 15 20 25 30 35 40 45 50 3 heat rate Wcm2 E x so 2 E 40 2O 4572m Rigid 70deg SphereCone c t 39 D 5 10 15 20 25 30 35 Mach Number 3rd International Planetary Probe Workshop Anavyssos Attica Greece June 27 July 1 2005 MIAS IRDT Hypercone Mars In atable Aeroshell System MIAS J SC funded activity with several international partners Requirements amp concept development for Mars aeroassist entry vehicles In atable Reentry and Descent Technology IRDT Flight Test program of aeroshell developed by Lavochkin for Mars96 Vertigo Inc Hypercone Supersonic decelerator technology feasibility analysis 3rd International Planetary Probe Workshop Anavyssos Attica Greece June 27 July 1 2005 Current LaRC Inflatable Aeroshell Projects Inflatable Reentry Vehicle Experiment IRVE Collaboration between LaRC and WFF Started in 2003 Flight Demonstration in December 2005 Packaging efficiency Exoatmospheric Deployment and Inflation Structural integrity and aerodynamic stability throughout the flight Inflatable Aeroshell and Thermal Protection System Development IATD JSC led ESRampT Project Started January 2005 Demonstrate inflatable aeroshell technology specifically for VSE applications Application Trade Study phase Three Flight Demonstrations 37d lntetnattona Planetary Probe Workshop Anavyaaoa Atttca Greece June 27 a July 1 2005 IRVE Reentry Vehicle Launch Vehicle Interface In ation System N2 bottle amp plumbing Centerbody Structure EIecironics Assembly In atable Aeroshell Rigid Nose Cap Mass 101 Bkg Anaw n A ir GreeceJune27Juy12aas IRVE Aeroshell Construction 3 D m dlameter u 15 mradlus 7 places Volume 3 RES Lralnt TF39S Volume 2 lnflatable bladder 5le e spars Volume 1 3rd lnlemallona Planelary Probe Workshop Ana lyssos Amca Greece June 27 7 AW 7 2005 Inflatable Ply LayUp E AFTSTRUCTURALEAG 2D Mpag GM NFLATAELE BLADDER a upsm THERMOCOUPLE FORWARDSTR39UCTURALEAG LOCAWON FORWARD THERMAL PROTEW ON WE THERMOCOUPLE LOCAWON FLOW 37d Wemanona Panezary Probe Workshop Anavyssos Amos Grew June 27 7 July 1 2005 Separate Booster and Fairing From RV and TM 60s IRVE Flight Test Timeline RV separation from TM 64s 78 km i j RV begins broadcast of data after separation Coast to 72 km 60s 2nd stage burnout 40 seconds 2nd stage ignition 15 seconds Launch on TerrierOrion From Wallops Island In ation begins at 250s 17 RV completes inflation prior to Reentry 125 kilometers Atmospheric Interface RV passes through pressure pulse at 46 kilometers Flight Experiment concluded just after vehicle has passed quot T3705 or MaX dynamic pressure Alt lt 46 km WFF provides launch operations telemetry acquisition and radar track of flight RV impacts water at 165 ms v T1256S 3111 International Planetaly Probe Workshop Anavyssos Attica Greece June 27 July 1 2005 IRVE Data Products lnFlight Measurements Attitude Deceleration Video of inflation Aeroshell dynamics lndepth and surface temperature measurements Inflation system performance measurements Data Products AoA History Drag History Inflation History RV Trajectory Thrudepth Temperature History Surface Temperature History System Health amp Status History q tWcm 9 a A w m Temperature Distribution Photog rammetric Structural Analysis j Angle of Attack Trajectory Drag History Gillideg SphemCm atlulz Thermal Gradient 3rd International Planetan Probe Workshop Anavyssos Attica Greece June 27 July 1 2005 IATD Application Trade Studies Mission Specific Applications ISS Downmass TransLunar Injection Stage Return Aerocapture Lunar Return Aerocapture Crew Exploration Vehicle Abort Mars Entry Robotic and Human Precursor Missions TransMartian Injection Stage Return Aerocapture Mars Return Trajectory Trades Output a family of trajectories that meet mission requirements parameterized by LD amp AeroAerothermal Analyses Out ut Normalized heating and pressure distribution over a trade space of multiple aeroshell geometries and CDA combinations Aeroshell Structure and Configurations Characterize inflatable aeroshell subsystems ie inflation system ply lay up bladder material properties etc per aeroshell geometry and mission environment 3rd imemazronai Planetary Probe Workshop Anavyssos Attica Greece June 27 7 July 1 2005 IATD Application Trade Studies Mission Requirements Famiiy or Traiectories per Expioration mission Trajectory Tra s Aeroshell Concept AeroAerothermal Aeroshell Structure and Configurations eating and Pressure Distributions per Geometry oyer a range or entry conditio Required materiai strengtn per contiguration amp geometry ri ps t Estaoiisn Design parameters tor aerosneiis 37d internetionei Planetary Probe Workshop Aneyyssos Attica Greece June 27 a July 1 2005 IATD Flight Tests Flight Test 1 Objectives Demonstrate Lift Generation Demonstrate survivability at a more challenging reentry environmen Flight Test 2 amp 3 Objectives Demonstrate scalability to an 812 meter aeroshell Demonstrate Controllability Demonstrate survivability at a more challenging reentry environmen Mission Supporting Technologies Gas Generator inflation systems AngleofAttack Control andor Roll Modulation Techniques Development Supporting Technologies TalusOriole sounding rocket 3rd imernaironai Pianezary Probe Workshop Anavyssos Attica Greece June 27 7 July 1 2005 Proposed Inflatable Aeroshell Projects IRVE LaRC and WFF are currently in discussions over a followon flightto IRVE Flight on a TalusOriole Sounding Rocket Demonstrate an 810 meter aeroshell on a ballistic trajectory Provide an independent path fortechnology development TRL 7 Flight Test Secondary payload on geosatellite launch Reentry Vehicle deployed into a GTO orbit Entry velocity approximately 10 kms 4meteraeroshell Entry conditions are mission relevantfor ISS Downmass and Lunar Return missions 3711 international Pianezary Probe Womenop Anavyssoe Amos Greece June 27 7 July 1 2005 Development of Analysis amp Prediction Capabilities Flight tests serve as demonstrations of the technology s capabilities Flight tests serve as a test bed to validate the tools and methodologies used to design each flight test article Modeling and Analysis Capabilities Required Aero and Radiative heating prediction Structural response prediction Aftbody heating Dynamic stability prediction Controllability Scalability 37d inzemanona Planetary Probe Workshop Anavyssos Amos Greece June 27 7 July 1 2005 Overall Technology Development Process TRLZ RL3 TRL6 2008 371 lmemanonal Planetary Probe Workshop Anavyssos Amos Greece June 27 7 July 1 2005 Summary Key to Technology Development is Risk Reduction Suf cient technical risk reduction for mission implementation Demonstrated Technology Performance Demonstrated Design Techniques Demonstrated Fabrication Techniques Technology development process risk reduction Continued promotion of the technology Technical risk mitigation plan fortechnologies that supportthe technology development process Multiple technology development paths options 3rd imernazronai Pianezary Probe Workshop Anavyssos Amos Greece June 27 7 July 1 2005 Contact Information Charles Chuck J Player NASA LaRC MS 489 1 N Dryden St Hampton Virginia US 23681 CharlesJPlayernasagov Dr F McNeil Cheatwood NASA LaRC MS 176 3W Reid St Hampton Virginia US 23681 FMCheatwoodnasagov James Jim Corliss NASA LaRC MS 176 3W Reid St Hampton Virginia US 23681 JamesMCorIissnasagov 3rd imemazronai Pianezary Probe Workshop Anavyssos Amos Groom June 27 7 July 1 2005 Questions 3711 Wemanona Panezary Probe Workshop Anavyssos Amos Grew June 27 7 July 1 2005


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