Subsonic Parachutes for Future Mars Missions
|
|
- Ronald Ferguson
- 5 years ago
- Views:
Transcription
1 Subsonic Parachutes for Future Mars Missions John C. Underwood, Arrun Saunders, Steven B. Rogers, J. Stephen Lingard Vorticity Ltd Lionel Marraffa, Luca Ferracina European Space Agency 1
2 Mars Parachutes - History 1960 s & 1970 s PEPP Disk-Gap-Band Ringsail Cruciform DGB Selected for Viking 1976: Viking Landers: DGB 1997: Mars Pathfinder: DGB 2001: Mars Polar Lander: DGB 2003: Beagle2: DGB / Polyconical 200x: Mars Exploration Rovers: DGB 2013: Mars Science Laboratory: DGB 2
3 Disk-Gap-Band Good supersonic inflation Fair drag coefficient Stability depends on geom. porosity Large inflation force Several variants Viking Original. 12.5% porosity, stable at about 15, high drag coefficient Huygens Double gap. 22.4% porosity, stable at <8, lower drag coefficient Mars Pathfinder Double band. <12.5% porosity, relatively stable, low drag coefficient Mars Exploration Rover Compromise between MPF and Viking 3
4 Way forward Ideal parachute Reliable inflation Good drag coefficient Stable Low inflation force Candidates DGB Ringslot Gliding parachutes 4
5 High altitude tests Gliding parachute / Low density atmosphere Cone or glide? Drive slots? Cluster? Low glide is best! 5
6 Candidate design Disk Gap Band (23% porosity) High inflation force Good drag coefficient Stable Reliable inflation Ringslot (23% porosity) Low inflation peak Good drag coefficient Stable Less reliable inflation Disk-Gap-Band-Gap-Band Inflation force from Ringslot Porosity near skirt Inflation reliability from DGB Low porosity in crown 6
7 Research Plan Wind tunnel tests Aerodynamic coefficient measurement Inflation force profile measurement High altitude drop tests Inflation at Mach 0.8 Performance in low density atmosphere Low altitude drop test Full-scale inflation CFD / FSI for test correlation and extrapolation 7
8 Wind tunnel tests 9x9 Wind tunnel at NRC, Ottawa Up to 50 m/s Two test rigs Forced incidence and deployment Load cell Flying parachute location Upstream strut with streamlined fairing Downstream strut Rotating floor panel 8
9 Seven parachute types DGBGB Two variants Huygens DGB Viking DGB EXPERT Cruciform Cruciform with inserts Triconical 9
10 Incidence Tests 10
11 Inflation Tests 11
12 Force coefficient Outcomes Good quality aerodynamic databases for 7 types Huygens / Viking Improvement on existing knowledge Cruciforms / Triconical / DGBGB New data Good quality inflation & free-flight data for 6 types 1.2 Dimensionless inflation profiles - Huygens Dimensionless Time 12
13 High Altitude Drop Tests 6 kg Drop Test Vehicles 28 km Drop Altitude Free-fall to Mach 0.8 Parachute deployed by spring drogue Instrumentation Low speed camera High speed camera Accelerometer / Rate Gyro GPS Pitot & Ambient pressures Temperature 13
14 High altitude drop tests One flight complete Good inflation data at Mach 0.8 Good drag data during descent 14
15 Low Altitude Drop Test 150 kg Test Vehicle Helicopter Drop Programmer parachute 2.59m DGB Accelerates to constant velocity Release programmer Deploys test parachute 8.0 m DGBGB Instrumentation GPS Accelerometers Rate gyros Barometer Pitot-static probe 15
16 Parachute PIV Assessment of PIV applied to parachutes Flow visualisation to validate CFD 16
17 CFD / FSI Test matching Validation of CFD / FSI model Extrapolation to untestable conditions High Mach number tests at incidence Mars atmosphere 17
18 Conclusions Good aerodynamic database for 7 typical parachute types Demonstrated wind tunnel test technique Useful for any future missions Demonstrated low cost test technique for high altitude, sub-scale tests Enhanced understanding of parachutes for Mars use Applications so far Contribution to Huygens post-flight analysis Validation data for ExoMars 2016 parachute system 18
Deployment and Drop Test for Inflatable Aeroshell for Atmospheric Entry Capsule with using Large Scientific Balloon
, Germany Deployment and Drop Test for Inflatable Aeroshell for Atmospheric Entry Capsule with using Large Scientific Balloon Kazuhiko Yamada, Takashi Abe (JAXA/ISAS) Kojiro Suzuki, Naohiko Honma, Yasunori
More informationCoupled Aero-Structural Modelling and Optimisation of Deployable Mars Aero-Decelerators
Coupled Aero-Structural Modelling and Optimisation of Deployable Mars Aero-Decelerators Lisa Peacocke, Paul Bruce and Matthew Santer International Planetary Probe Workshop 11-15 June 2018 Boulder, CO,
More informationEntry, Descent, and Landing Technology Concept Trade Study for Increasing Payload Mass to the Surface of Mars
Entry, Descent, and Landing Technology Concept Trade Study for Increasing Payload Mass to the Surface of Mars Juan R. Cruz, Alicia D. Cianciolo, Richard W. Powell, Lisa C. Simonsen NASA Langley Research
More informationReentry Demonstration Plan of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket
AIAA ADS Conference 2011 in Dublin 1 Reentry Demonstration Plan of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket Kazuhiko Yamada, Takashi Abe (JAXA/ISAS) Kojiro Suzuki
More informationDeployment and Flight Test of Inflatable Membrane Aeroshell using Large Scientific Balloon
1 Deployment and Flight Test of Inflatable Membrane Aeroshell using Large Scientific Balloon Kazuhiko Yamada, Takashi Abe (JAXA/ISAS) Kojiro Suzuki, Naohiko Honma, Yasunori Nagata, Masashi Koyama (The
More informationVenus Entry Options Venus Upper Atmosphere Investigations Science and Technical Interchange Meeting (STIM)
Venus Entry Options Venus Upper Atmosphere Investigations Science and Technical Interchange Meeting (STIM) January 24, 2013 at the Ohio Aerospace Institute Peter Gage, Gary Allen, Dinesh Prabhu, Ethiraj
More informationOn the feasibility of a fast track return to Mars
On the feasibility of a fast track return to Mars Mars Lander(s) 2011 Mars Demonstration Landers (MDL) Page 1 Technology Demonstrators SMART 1 SMART 2 LISA PF Solar Electric Propulsion Drag Free Control
More informationChallenges of Designing the MarsNEXT Network
Challenges of Designing the MarsNEXT Network IPPW-6, Atlanta, June 26 th, 2008 Kelly Geelen kelly.geelen@astrium.eads.net Outline Background Mission Synopsis Science Objectives and Payload Suite Entry,
More informationCHANGING ENTRY, DESCENT, AND LANDING PARADIGMS FOR HUMAN MARS LANDER
National Aeronautics and Space Administration CHANGING ENTRY, DESCENT, AND LANDING PARADIGMS FOR HUMAN MARS LANDER Alicia Dwyer Cianciolo NASA Langley Research Center 2018 International Planetary Probe
More informationAuburn University Student Launch. PDR Presentation November 16, 2015
Auburn University Student Launch PDR Presentation November 16, 2015 Project Aquila Vehicle Dimensions Total Length of 69.125 inches Inner Diameter of 5 inches Outer Diameter of 5.25 inches Estimated mass
More informationA combined Exobiology and Geophysics Mission to Mars
A combined Exobiology and Geophysics Mission to Mars 2009 Colin Pillinger (OU) Mark Sims (Leicester) T. Spohn, L. Richter (DLR Germany) S. Hurst, R. Slade, S. Kemble (EADS Astrium) D. Northey, P. Taylor,
More informationENGINE STARTING PERFORMANCE EVALUATION AT STATIC STATE CONDITIONS USING SUPERSONIC AIR INTAKE
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES STARTING PERFORMANCE EVALUATION AT STATIC STATE CONDITIONS USING SUPERSONIC AIR INTAKE Author1* Takashi Nishikido Author2* Iwao Murata Author3**
More informationJordan High School Rocketry Team. A Roll Stabilized Video Platform and Inflatable Location Device
Jordan High School Rocketry Team A Roll Stabilized Video Platform and Inflatable Location Device Mission Success Criteria No damage done to any person or property. The recovery system deploys as expected.
More informationLong-Range Rovers for Mars Exploration and Sample Return
2001-01-2138 Long-Range Rovers for Mars Exploration and Sample Return Joe C. Parrish NASA Headquarters ABSTRACT This paper discusses long-range rovers to be flown as part of NASA s newly reformulated Mars
More informationHypersonic Wind Tunnel Test of Flare-type Membrane Aeroshell for Atmospheric Entry Capsule
Hypersonic Wind Tunnel Test of Flare-type Membrane Aeroshell for Atmospheric Entry Capsule Kazuhiko Yamada (JAXA) Masashi Koyama (The University of Tokyo) Yusuke Kimura (Aoyama Gakuin University) Kojiro
More informationLOW DENSITY SUPERSONIC DECELERATOR. Jacob J. Matutino Department of Computer Science University of Hawai i at Mānoa Honolulu, HI ABSTRACT
LOW DENSITY SUPERSONIC DECELERATOR Jacob J. Matutino Department of Computer Science University of Hawai i at Mānoa Honolulu, HI 96822 ABSTRACT The Low Density Supersonic Decelerator (LDSD) project s purpose
More informationARCHIVE COPY DO NOT LOAN. July lift *«*
1 AEDC-TR-72-78 ARCHIVE COPY DO NOT LOAN AERODYNAMIC CHARACTERISTICS OF DISK-GAP-BAND PARACHUTES IN THE WAKE OF VIKING ENTRY FOREBODIES AT MACH NUMBERS FROM 0.2 TO 2.6 David E. A. Reichenau ARO, Inc. s.
More informationNASA - USLI Presentation 1/23/2013. University of Minnesota: USLI CDR 1
NASA - USLI Presentation 1/23/2013 2013 USLI CDR 1 Final design Key features Final motor choice Flight profile Stability Mass Drift Parachute Kinetic Energy Staged recovery Payload Integration Interface
More informationDevelopment of an Extended Range, Large Caliber, Modular Payload Projectile
1 Development of an Extended Range, Large Caliber, Modular Payload Projectile April 12th, 2011 Miami, Florida, USA 46 th Annual Gun & Missile Systems Conference & Exhibition Speaker: Pierre-Antoine Rainville
More informationA high-glide ram-air parachute for 6,000 kg payloads, tested with the FASTWing CL test-vehicle.
20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar 4-7 May 2009, Seattle, Washington AIAA 2009-2933 A high-glide ram-air parachute for 6,000 kg payloads, tested with the FASTWing
More informationPropeller blade shapes
31 1 Propeller blade shapes and Propeller Tutorials 2 Typical Propeller Blade Shape 3 M Flight M. No. Transonic Propeller Airfoil 4 Modern 8-bladed propeller with transonic airfoils near the tip and swept
More informationGeorgia Tech NASA Critical Design Review Teleconference Presented By: Georgia Tech Team ARES
Georgia Tech NASA Critical Design Review Teleconference Presented By: Georgia Tech Team ARES 1 Agenda 1. Team Overview (1 Min) 2. 3. 4. 5. 6. 7. Changes Since Proposal (1 Min) Educational Outreach (1 Min)
More informationLOW DENSITY SUPERSONIC DECELERATOR. Kolby Javinar Department of Electrical Engineering University of Hawai i at Mānoa Honolulu, HI ABSTRACT
LOW DENSITY SUPERSONIC DECELERATOR Kolby Javinar Department of Electrical Engineering University of Hawai i at Mānoa Honolulu, HI 96822 ABSTRACT During the summer of 2014, NASA planned on testing two new
More informationY. Lemmens, T. Benoit, J. de Boer, T. Olbrechts LMS, A Siemens Business. Real-time Mechanism and System Simulation To Support Flight Simulators
Y. Lemmens, T. Benoit, J. de Boer, T. Olbrechts LMS, A Siemens Business Real-time Mechanism and System Simulation To Support Flight Simulators Smarter decisions, better products. Contents Introduction
More informationAircraft Pollution Monitoring Project
National Institute for Aerospace Research Elie Carafoli INCAS Bucharest Aircraft Pollution Monitoring Project Authors: Andreea BOSCORNEA Violeta Andreea ANASTASE Sorin Nicolae VAJAIAC London, 4 th November
More information2.6. Air Flow Control Valve Type PRD
2.6. Air Flow Control Valve Type PRD Page 1/10 Air Flow Control Valve, Type PRD Page 2/10 Air Flow Control Valve Type PRD Description and Design The PRD remains the air valve of choice for critical heating,
More informationFLIGHT READINESS REVIEW TEAM OPTICS
FLIGHT READINESS REVIEW TEAM OPTICS LAUNCH VEHICLE AND PAYLOAD DESIGN AND DIMENSIONS Vehicle Diameter 4 Upper Airframe Length 40 Lower Airframe Length 46 Coupler Band Length 1.5 Coupler Length 12 Nose
More informationAWIATOR Project Perspectives:
No SBVGs With SBVGs AWIATOR Project Perspectives: Passive Flow Control on Civil Aircraft Flaps using Sub-Boundary Layer Vortex Generators David Sawyers Aerodynamics R&T Co-ordinator Airbus UK Limited KATnet
More informationFlight and Terminal Ballistic Performance Demonstration of a Gun-Launched Medium Caliber Ramjet Propelled Air Defense Projectile
Flight and Terminal Ballistic Performance Demonstration of a Gun-Launched Medium Caliber Ramjet Propelled Air Defense Projectile Ronald Veraar and Eelko v. Meerten (TNO) Guido Giusti (RWMS) Contents Solid
More informationAerodynamic Drag Assessment
Aerodynamic Drag Assessment Computer Fluid Dynamics (CFD) analysis was used in the ULSAB-AVC Program to evaluate the aerodynamic concept from the very beginning of vehicle concepts. 11.1 BACKGROUND A vehicle
More informationPre-Launch Procedures
Pre-Launch Procedures Integration and test phase This phase of operations takes place about 3 months before launch, at the TsSKB-Progress factory in Samara, where Foton and its launch vehicle are built.
More informationA study on aerodynamic drag of a semi-trailer truck
Available online at www.sciencedirect.com Procedia Engineering 56 (013 ) 01 05 5 th BSME International Conference on Thermal Engineering A study on aerodynamic drag of a semi-trailer truck Harun Chowdhury*,
More information17/11/2016. Turbomachinery & Heat Transfer Laboratory Faculty of Aerospace Engineering Technion Israel Institute of Technology, Israel
17/11/2016 Turbomachinery & Heat Transfer Laboratory Faculty of Aerospace Engineering Technion Israel Institute of Technology, Israel 1 Motivation New challenges rise due to increase in demands from small
More informationThe European Lunar Lander Mission
The European Lunar Lander Mission Alain Pradier ASTRA Noordwijk, 12 th April 2011 European Space Agency Objectives Programme Objective PREPARATION FOR FUTURE HUMAN EXPLORATION Lunar Lander Mission Objective
More informationK. P. J. Reddy Department of Aerospace Engineering Indian Institute of Science Bangalore , India.
16 th Australasian Fluid Mechanics Conference Crown Plaza, Gold Coast, Australia 2-7 December 2007 Hypersonic Flight and Ground Testing Activities in India K. P. J. Reddy Department of Aerospace Engineering
More informationAerodynamic Testing of the A400M at ARA. Ian Burns and Bryan Millard
Aerodynamic Testing of the A400M at ARA by Ian Burns and Bryan Millard Aircraft Research Association Bedford, England Independent non-profit distributing research and development organisation Set up in
More informationFLIGHT TEST RESULTS AT TRANSONIC REGION ON SUPERSONIC EXPERIMENTAL AIRPLANE (NEXST-1)
26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES FLIGHT TEST RESULTS AT TRANSONIC REGION ON SUPERSONIC EXPERIMENTAL AIRPLANE (NEXST-1) Dong-Youn Kwak*, Hiroaki ISHIKAWA**, Kenji YOSHIDA* *Japan
More informationCase Study: ParaShield
Case Study: ParaShield Origin of ParaShield Concept ParaShield Flight Test Wind Tunnel Testing Future Applications U N I V E R S I T Y O F MARYLAND 2012 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu
More informationMoon Exploration Lunar Polar Sample Return ESA Thematic information day BELSPO, 3 July 2012
Moon Exploration Lunar Polar Sample Return ESA Thematic information day BELSPO, 3 July 2012 Human Spaceflight and Operations (HSO)) 1 Introduction Moon Exploration has a very high priority in Roscosmos
More informationNASA s Student Launch Initiative :
NASA s Student Launch Initiative : Critical Design Review Payload: Fragile Material Protection 1 Agenda 1. Design Overview 2. Payload 3. Recovery 4. 5. I. Sub-Scale Predictions II. Sub-Scale Test III.
More informationGeneral Dynamics F-16 Fighting Falcon
General Dynamics F-16 Fighting Falcon http://www.globalsecurity.org/military/systems/aircraft/images/f-16c-19990601-f-0073c-007.jpg Adam Entsminger David Gallagher Will Graf AOE 4124 4/21/04 1 Outline
More informationDYNAMIC SIMULATION OF MARS-03 ENTRY, DESCENT AND LANDING SYSTEM
DYNAMIC SIMULATION OF MARS-03 ENTRY, DESCENT AND LANDING SYSTEM Chia-Yen Peng and Walter Tsuha Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive Pasadena, CA 91109 ABSTRACT.
More informationCritical Design Review
Critical Design Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1 Overview Illinois Space Society 2 Launch Vehicle Summary Javier Brown Illinois Space
More informationPreface. Acknowledgments. List of Tables. Nomenclature: organizations. Nomenclature: acronyms. Nomenclature: main symbols. Nomenclature: Greek symbols
Contents Preface Acknowledgments List of Tables Nomenclature: organizations Nomenclature: acronyms Nomenclature: main symbols Nomenclature: Greek symbols Nomenclature: subscripts/superscripts Supplements
More informationProject NOVA
Project NOVA 2017-2018 Our Mission Design a Rocket Capable of: Apogee of 5280 ft Deploying an autonomous Rover Vehicle REILLY B. Vehicle Dimensions Total Length of 108 inches Inner Diameter of 6 inches
More informationKeywords: Supersonic Transport, Sonic Boom, Low Boom Demonstration
Blucher Mechanical Engineering Proceedings May 2014, vol. 1, num. 1 www.proceedings.blucher.com.br/evento/10wccm LOW-SONIC-BOOM CONCEPT DEMONSTRATION IN SILENT SUPERSONIC RESEARCH PROGRAM AT JAXA Yoshikazu
More informationReachMars 2024 A Candidate Large-Scale Technology Demonstration Mission as a Precursor to Human Mars Exploration
ReachMars 2024 A Candidate Large-Scale Technology Demonstration Mission as a Precursor to Human Mars Exploration 1 October 2014 Toronto, Canada Mark Schaffer Senior Aerospace Engineer, Advanced Concepts
More informationMission to Mars: Project Based Learning Previous, Current, and Future Missions to Mars Dr. Anthony Petrosino, Department of Curriculum and Instruction, College of Education, University of Texas at Austin
More informationThe following slideshow and talk were presented at the Uber Elevate Summit on April 25 th, The text included here is an approximate transcript
The following slideshow and talk were presented at the Uber Elevate Summit on April 25 th, 2017. The text included here is an approximate transcript of the speech given by Jay Carter, founder and CEO of
More informationFlight Readiness Review
Flight Readiness Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1 Overview Illinois Space Society 2 Launch Vehicle Summary Javier Brown Illinois
More informationSILENT SUPERSONIC TECHNOLOGY DEMONSTRATION PROGRAM
25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES SILENT SUPERSONIC TECHNOLOGY DEMONSTRATION PROGRAM Akira Murakami* *Japan Aerospace Exploration Agency Keywords: Supersonic, Flight experiment,
More informationAnalysis of Aerodynamic Performance of Tesla Model S by CFD
3rd Annual International Conference on Electronics, Electrical Engineering and Information Science (EEEIS 2017) Analysis of Aerodynamic Performance of Tesla Model S by CFD Qi-Liang WANG1, Zheng WU2, Xian-Liang
More informationGerman Aerospace Center Flight Operations
German Aerospace Center Flight Operations Introduction DLR is Germany s aerospace research center and space agency with about 4700 employees in 31 research institutes distributed over 8 main research centers
More informationSpaceLoft XL Sub-Orbital Launch Vehicle
SpaceLoft XL Sub-Orbital Launch Vehicle The SpaceLoft XL is UP Aerospace s workhorse space launch vehicle -- ideal for significant-size payloads and multiple, simultaneous-customer operations. SpaceLoft
More informationIcing Wind Tunnel tests in the framework of a Wing Ice Protection system certification process
Icing Wind Tunnel tests in the framework of a Wing Ice Protection system certification process AirTN-NextGen Workshop on Virtual testing, towards virtual certification Amsterdam (NL), May 25, 2016 Use
More informationModeling, Structural & CFD Analysis and Optimization of UAV
Modeling, Structural & CFD Analysis and Optimization of UAV Dr Lazaros Tsioraklidis Department of Unified Engineering InterFEA Engineering, Tantalou 7 Thessaloniki GREECE Next Generation tools for UAV
More informationStatement of Work Requirements Verification Table - Addendum
Statement of Work Requirements Verification Table - Addendum Vehicle Requirements Requirement Success Criteria Verification 1.1 No specific design requirement exists for the altitude. The altitude is a
More informationOverview. Mission Overview Payload and Subsystems Rocket and Subsystems Management
MIT ROCKET TEAM Overview Mission Overview Payload and Subsystems Rocket and Subsystems Management Purpose and Mission Statement Our Mission: Use a rocket to rapidly deploy a UAV capable of completing search
More informationBeyond current EDL Technologies on Mars: Evaluation of ARMADA Concepts
Beyond current EDL Technologies on Mars: Evaluation of ARMADA Concepts Cadenas, R (1) ; Peters, T (1) ; Graziano, M (1) ; Modenini, D (2) ; Saggiani, GM (2) ; Tortora, PP(2) ; Kervendal, E (3) ;Kohler,
More informationNASA USLI PRELIMINARY DESIGN REVIEW. University of California, Davis SpaceED Rockets Team
NASA USLI 2012-13 PRELIMINARY DESIGN REVIEW University of California, Davis SpaceED Rockets Team OUTLINE School Information Launch Vehicle Summary Motor Selection Mission Performance and Predictions Structures
More informationPreliminary Design Review. California State University, Long Beach USLI November 13th, 2017
Preliminary Design Review California State University, Long Beach USLI November 13th, 2017 System Overview Launch Vehicle Dimensions Total Length 108in Airframe OD 6.17in. ID 6.00in. Couplers OD 5.998in.
More informationCuriosity lands on Mars
Curiosity lands on Mars Early Monday morning (August 6, 2012), the Mars rover named Curiosity successfully landed on the surface of Mars. The rover launched on November 26 th, 2011 and traveled for 8 ½
More informationFlight Readiness Review Addendum: Full-Scale Re-Flight. Roll Induction and Counter Roll NASA University Student Launch.
Flight Readiness Review Addendum: Full-Scale Re-Flight Roll Induction and Counter Roll 2016-2017 NASA University Student Launch 27 March 2017 Propulsion Research Center, 301 Sparkman Dr. NW, Huntsville
More informationResearch in Internal and External Aerodynamics for the Next Generation of Effcient Aircraft
Research in Internal and External Aerodynamics for the Next Generation of Effcient Aircraft Huu Duc Vo Associate Professor Department of Mechanical Engineering École Polytechnique de Montréal 2017 National
More informationA FLYING EJECTION SEAT. By R. H. Hollrock* and J. J. Barzda* ABSTRACT
ijt'9y%., A FLYING EJECTION SEAT By R. H. Hollrock* and J. J. Barzda* ABSTRACT To increase aircrewmen's chances for safe rescue in combat zones, the armed forces are investigating advanced escape and rescue
More informationSupersonic Combustion Experimental Investigation at T2 Hypersonic Shock Tunnel
Supersonic Combustion Experimental Investigation at T2 Hypersonic Shock Tunnel D. Romanelli Pinto, T.V.C. Marcos, R.L.M. Alcaide, A.C. Oliveira, J.B. Chanes Jr., P.G.P. Toro, and M.A.S. Minucci 1 Introduction
More informationStructural Strength of Flare-type Membrane Aeroshell Supported by Inflatable Torus against Aerodynamic Force
Structural Strength of Flare-type Membrane Aeroshell Supported by Inflatable Torus against Aerodynamic Force Kazuhiko Yamada (JAXA/ISAS) Takuya Sonoda (Tokai University) Kyoichi Nakashino (Tokai University)
More informationWind Tunnel Measurement Of Aerodynamic Characteristics Of A Generic Eurocopter Helicopter
Wind Tunnel Measurement Of Aerodynamic Characteristics Of A Generic Eurocopter Helicopter by Engr. Assoc. Prof. Dr Shuhaimi Mansor, MIEM, P. Eng. Experimental aerodynamic studies on a generic model of
More informationPrimary control surface design for BWB aircraft
Primary control surface design for BWB aircraft 4 th Symposium on Collaboration in Aircraft Design 2014 Dr. ir. Mark Voskuijl, ir. Stephen M. Waters, ir. Crispijn Huijts Challenge Multiple redundant control
More informationOPTIMAL MISSION ANALYSIS ACCOUNTING FOR ENGINE AGING AND EMISSIONS
OPTIMAL MISSION ANALYSIS ACCOUNTING FOR ENGINE AGING AND EMISSIONS M. Kelaidis, N. Aretakis, A. Tsalavoutas, K. Mathioudakis Laboratory of Thermal Turbomachines National Technical University of Athens
More informationSSC Swedish Space Corporation
SSC Swedish Space Corporation Platforms for in-flight tests Gunnar Florin, SSC Presentation outline SSC and Esrange Space Center Mission case: Sounding rocket platform, dedicated to drop tests Satellite
More informationRocketry, the student way
Rocketry, the student way Overview Student organization Based at TU Delft About 90 members > 100 rockets flown Design, Construction, Test, Launch All done by students Goal Design, build, and fly rockets
More informationOMOTENASHI. (Outstanding MOon exploration TEchnologies demonstrated by NAno Semi-Hard Impactor)
SLS EM-1 secondary payload OMOTENASHI (Outstanding MOon exploration TEchnologies demonstrated by NAno Semi-Hard Impactor) The smallest moon lander launched by the most powerful rocket in the world * Omotenashi
More informationAn Update on SKYLON. Alan Bond Managing Director & Chief Engineer Reaction Engines Ltd. REACTION ENGINES LTD
An Update on SKYLON Alan Bond Managing Director & Chief Engineer Reaction Engines Ltd. SKYLON Operations 2 SKYLON 1990 The SKYLON spaceplane the phoenix of HOTOL 1951 Skylon Sculpture Festival of Britain
More informationGround Effect and Turbulence Simulation at the Pininfarina Wind Tunnel. Giuseppe Carlino Aerodynamic and Aeroacoustic Research Center
Ground Effect and Turbulence Simulation at the Pininfarina Wind Tunnel Giuseppe Carlino Aerodynamic and Aeroacoustic Research Center The Aerodynamic and Aeroacoustic Research Center The Full Scale Automotive
More informationMars Aerocapture/Aerobraking Aeroshell Configurations by Abraham Chavez
Mars Aerocapture/Aerobraking Aeroshell Configurations by Abraham Chavez This presentation provides a review of those studies and a starting point for considering Aerocapture/Aerobraking technology as a
More informationPresentation Outline. # Title
FRR Presentation 1 Presentation Outline # Title 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 Team Introduction Mission Summary Vehicle Overview Vehicle Dimensions Upper Body Section Elliptical
More informationGIT LIT NASA STUDENT LAUNCH PRELIMINARY DESIGN REVIEW NOVEMBER 13TH, 2017
GIT LIT 07-08 NASA STUDENT LAUNCH PRELIMINARY DESIGN REVIEW NOVEMBER TH, 07 AGENDA. Team Overview (5 Min). Educational Outreach ( Min). Safety ( Min) 4. Project Budget ( Min) 5. Launch Vehicle (0 min)
More informationEuropean Lunar Lander: System Engineering Approach
human spaceflight & operations European Lunar Lander: System Engineering Approach SECESA, 17 Oct. 2012 ESA Lunar Lander Office European Lunar Lander Mission Objectives: Preparing for Future Exploration
More informationPresentation 3 Vehicle Systems - Phoenix
Presentation 3 Vehicle Systems - Phoenix 1 Outline Structures Nosecone Body tubes Bulkheads Fins Tailcone Recovery System Layout Testing Propulsion Ox Tank Plumbing Injector Chamber Nozzle Testing Hydrostatic
More informationTHE SIMULATION OF ONE SIDE OF TETRAHEDRON AIRBAGS IMPACT ATTENUATION SYSTEM
THE SIMULATION OF ONE SIDE OF TETRAHEDRON AIRBAGS IMPACT ATTENUATION SYSTEM Zhuo Wu (1) (1) Beijing Institution of Space Mechanics and Electrics, PB-9201-3, Beijing, China, Email:wuzhuo82@gmail.com ABSTRACT
More informationTransport Canada s ecotechnology for Vehicles (etv) Program
Transport Canada s ecotechnology for Vehicles (etv) Program Task Force on Vehicle Weights and Dimensions Policy November 20, 2013 RDIMS # 8902239 PURPOSE The objective of this presentation is to provide
More informationExternal Aerodynamics: Lift of airship created only by buoyancy which doesn t need lift generating surface like an airfoil or a wing
5.1 AERODYNAMICS: The HAA aerodynamic regime could broadly be categorized into External and Internal Aerodynamics. The External Aerodynamics deals with the Shape of airship and the internal aerodynamics
More informationCable Dragging Horizontal Takeoff Spacecraft Air Launch System
Cable Dragging Horizontal Takeoff Spacecraft Air Launch System Author: Zhixian Lin December 31, 2017 i Contents Abstract...ii 1. Cable Dragging Horizontal Takeoff Spacecraft Air Launch System... 1 2. The
More informationEXOMARS MSA. TEST HDRM DEVELOPMENT FOR SEPARATION PERFORMANCE VERIFICATION
EXOMARS MSA. TEST HDRM DEVELOPMENT FOR SEPARATION PERFORMANCE VERIFICATION L. Caldirola (1), B. Schmid (1), M. Cattaneo (1), A. Schiaffini (1) (1) RUAG Schweiz AG, RUAG Space, Schaffhauserstrasse 8, 82
More informationAn Overview of EDL Investments in the NASA Fundamental Aeronautics Program Interplanetary Probe Workshop 6
An Overview of EDL Investments in the NASA Fundamental Aeronautics Program Interplanetary Probe Workshop 6 Juan J. Alonso NASA Fundamental Aeronautics Program June 23, 2008 Aeronautics Programs Fundamental
More informationEvolution of MDO at Bombardier Aerospace
Evolution of MDO at Bombardier Aerospace 6 th Research Consortium for Multidisciplinary System Design Workshop Ann Arbor, Michigan July 26 th - 27 th, 2011 Pat Piperni MDO Project Manager Bombardier Aerospace
More informationBY HOEYCOMB AEROSPACE TECHNOLOGIES. HC-330 HYBRID-POWERED ALL- ELECTRICITY DRIVEN four-rotor UAV
BY HOEYCOMB AEROSPACE TECHNOLOGIES HC-330 HYBRID-POWERED ALL- ELECTRICITY DRIVEN four-rotor UAV Content SYSTEM SPECIFICATI- ON TYPICAL USING PROCESS OVERVIEW SUBSYSTEM SPECIFICATI- ON 1 OVERVIEW System
More informationLunette: A Global Network of Small Lunar Landers
Lunette: A Global Network of Small Lunar Landers Leon Alkalai and John O. Elliott Jet Propulsion Laboratory California Institute of Technology LEAG/ILEWG 2008 October 30, 2008 Baseline Mission Initial
More informationFrom MARS To MOON. V. Giorgio Director of Italian Programs. Sorrento, October, All rights reserved, 2007, Thales Alenia Space
From MARS To MOON Sorrento, October, 2007 V. Giorgio Director of Italian Programs Page 2 Objectives of this presentation is to provide the Lunar Exploration Community with some information and status of
More informationSTAR European Conference 2010 AERODYNAMICS DEVELOPMENTS ON A LE MANS PROTOTYPE ORECA 01 LMP1
STAR European Conference 2010 AERODYNAMICS DEVELOPMENTS ON A LE MANS PROTOTYPE ORECA 01 LMP1 PRESENTATION 1. ORECA Presentation 2. Why we use CFD? 2009 Aero Development 2010 Aero Development 3. Methodology
More informationDRAG CHARACTERISTICS AND SUITABILITY OF TEE-FOOT LON$ PARACHUSI-ETC (U) NAY 61 c T calzanwo UNCLASSFIED
-' AD-AIll 718 NAVAL AIR DEVELAPMENT CENTER WARMINSTER PA P/f 20/4 DRAG CHARACTERISTICS AND SUITABILITY OF TEE-FOOT LON$ PARACHUSI-ETC (U) NAY 61 c T calzanwo UNCLASSFIED N Hil '~132 111122 1111 " ----
More informationPreliminary Design of a LSA Aircraft Using Wind Tunnel Tests
Preliminary Design of a LSA Aircraft Using Wind Tunnel Tests Norbert ANGI*,1, Angel HUMINIC 1 *Corresponding author 1 Aerodynamics Laboratory, Transilvania University of Brasov, 29 Bulevardul Eroilor,
More informationCFD ANALYSIS FOR UAV OF FLYING WING
SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE-AFASES 2016 CFD ANALYSIS FOR UAV OF FLYING WING Dumitru PEPELEA, Marius Gabriel COJOCARU, Adrian TOADER, Mihai Leonida NICULESCU National Aerospace Research,
More informationAuburn University. Project Wall-Eagle FRR
Auburn University Project Wall-Eagle FRR Rocket Design Rocket Model Mass Estimates Booster Section Mass(lb.) Estimated Upper Section Mass(lb.) Actual Component Mass(lb.) Estimated Mass(lb.) Actual Component
More informationLunar Science and Infrastructure with the Future Lunar Lander
ICEUM9 Sorrento Lunar Science and Infrastructure with the Future Lunar Lander Session 9: Next steps for Robotic Landers, Rovers and Outposts ICEUM9 Sorrento, Oct. 26, 2007 Hansjürgen Günther 26/10/2007
More informationL 298/70 Official Journal of the European Union
L 298/70 Official Journal of the European Union 16.11.2011 MODULE 12. HELICOPTER AERODYNAMICS, STRUCTURES AND SYSTEMS 12.1 Theory of Flight Rotary Wing Aerodynamics 1 2 Terminology; Effects of gyroscopic
More informationTELFONA, Contribution to Laminar Wing Development for Future Transport Aircraft. K. H. Horstmann Aeronautical Days, Vienna, 19 th -21 st June 2006
TELFONA, Contribution to Laminar Wing Development for Future Transport Aircraft K. H. Horstmann Aeronautical Days, Vienna, 19 th -21 st June 2006 Content Motivation Determination of transition Objectives
More informationObservation of Flame Stabilized at a Hydrogen-Turbojet-Engine Injector Installed into a Lab-Scale Combustion Wind Tunnel
Trans. JSASS Aerospace Tech. Japan Vol. 1, No. ists28, pp. Pa_19-Pa_24, 212 Original Paper Observation of Flame Stabilized at a Hydrogen-Turbojet-Engine Injector Installed into a Lab-Scale Combustion Wind
More informationBrief overview of lunar surface environment Examples of rover types and designs Steering systems Static and dynamic stability
Brief overview of lunar surface environment Examples of rover types and designs Steering systems Static and dynamic stability 2007 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu Lunar
More information