MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT. Nazlıcan KARACA
|
|
- Cecil Ward
- 5 years ago
- Views:
Transcription
1 ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT Nazlıcan KARACA Department of Aerospace Engineering Thesis Advisor: Yrd. Doç. Dr. Melike NİKBAY May
2
3 ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT Nazlıcan KARACA Department of Aerospace Engineering Thesis Advisor: Yrd. Doç. Dr. Melike NİKBAY JUNE 2018
4
5 Nazlıcan KARACA, student of ITU Faculty of Aeronautics and Astronautics student ID , successfully defended the graduation entitled MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY, which he prepared after fulfilling the requirements specified in the associated legislations, before the jury whose signatures are below. Thesis Advisor : Yrd. Doç. Dr. Melike NİKBAY... Istanbul Technical University Jury Members : Prof.Dr. A. Rüstem ASLAN... Istanbul Technical University Dr.Öğr.Üye. K. Bülent YÜCEİL... Istanbul Technical University Date of Submission : 28 May 2018 Date of Defense : 12 June 2018
6
7 FOREWORD With the exponential improvements on technology, every part of the spacecrafts and rockets are aim to be re-used, for both financial reasons and convenience. This aim makes the analysis of re-entry vehicles highly important and crucial for the future of the space industry. On this paper, I am investigating and re-simulating the project, SMAAC (Sounding Rocket Experiment of Membrane Aeroshell for Atmospheric- Entry Capsule). June 2018 Nazlıcan KARACA
8 TABLE OF CONTENTS Page FOREWORD... 7 TABLE OF CONTENTS... 8 SYMBOLS LIST OF FIGURES SUMMARY INTRODUCTION Purpose of thesis... 14
9
10 ABBREVIATIONS ATM B CONV SOLAR T : Atmosphere : Background : Convection : Solar : Turbulent : Freestream
11 SYMBOLS
12 LIST OF FIGURES Page Figure 1.1. Photographs of the SMAAC[1]... Hata! Yer işareti tanımlanmamış. Figure 1.2. MAAC configuration and mounting positions of thermocouples (all dimensions are in millimeters). [1]... 2
13 MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY SUMMARY A SMAAC (Sounding Rocket Experiment of Membrane Aeroshell for Atmospheric-Entry Capsule) project is investigated and re-simulated in this paper. Simulation and real trial values have been compared. The tested values have been obtained from the Takahashi,2015 paper [1]. Test values have obtained by a demonstartion flight of an advanced reentry vehicle which was carried out by a Japan Aerospace Exploration Agency S sounding rocket. The reason for researches of inflatable and flexible aeroshell is its low ballistic coefficient which results on the reduction in aerodynamic heating and deceleration at high altitude. Measurements of temperatures were taken both from the backside of the flexible aeroshell and inside of the capsule by thermocouples at a good many of times during its flight back into atmosphere. The results from those measurements investigated and a thermal history has been constituted. Also a numerical prediction in which a flow field simulation which consisted of both laminar and turbulent flow and deformation of the flexible aeroshell considered, of the heating was conducted and the results from these have been combined. With the knowledge from these steps a thermal module composed.
14 1 INTRODUCTION 1.1 Purpose of thesis Inflatable aeroshels have a high importance among the space industry. National Aeronautics and Space Administration (NASA), the European Space Agency (ESA), and the Japan Aerospace Exploration Agency (JAXA) are working to improve this project. Figure 1 Photographs of the SMAAC Figure 1 shows a photograph of the SMAAC before the flight experiment. In the demonstration flight, the reentry vehicle (a capsule with an inflatable aeroshell) was separated from the rocket at an altitude of 111 km and started to re-enter from an altitude of about 150 km. The vehicle achieved a maximum velocity of 1320 m s,mach number of 4.5, and dynamic pressure of 500 Pa according to [2].
15 Figure 2 MAAC configuration and mounting positions of thermocouples (all dimensions are in millimeters).
16 2 CONCLUSION
17 REFERENCES [1] Takahashi,2015, Aerodynamic Heating Around Flare-Type Membrane Inflatable Vehicle in Suborbital Reentry Demonstration Flight [2] Yamada,K.,Nagata,Y., Abe,T.,Suzuki,K.,Imamura,O.,andAkita,D., Suborbital Reentry Demonstration of Inflatable Flare-Type Thin- Membrane Aeroshell Using a Sounding Rocket, Journal of Spacecraftand Rockets,Vol. 52, No. 1, 2015, pp doi: /1.A32807
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 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 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 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 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 informationHypersonic Wind Tunnel Test of a Flare-type Membrane Aeroshell for Atmospheric Entry Capsules
Trans. JSASS Aerospace Tech. Japan Vol. 8, No. ists27, pp. Pe_27-Pe_32, 2010 Original Paper Hypersonic Wind Tunnel Test of a Flare-type Membrane Aeroshell for Atmospheric Entry Capsules By Kazuhiko YAMADA
More informationCOMPUTATIONAL ANALYSIS OF TWO DIMENSIONAL FLOWS ON A CONVERTIBLE CAR ROOF ABDULLAH B. MUHAMAD NAWI
COMPUTATIONAL ANALYSIS OF TWO DIMENSIONAL FLOWS ON A CONVERTIBLE CAR ROOF ABDULLAH B. MUHAMAD NAWI Report submitted in partial of the requirements for the award of the degree of Bachelor of Mechanical
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 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 informationSTUDY OF EFFECTS OF FUEL INJECTION PRESSURE ON PERFORMANCE FOR DIESEL ENGINE AHMAD MUIZZ BIN ISHAK
STUDY OF EFFECTS OF FUEL INJECTION PRESSURE ON PERFORMANCE FOR DIESEL ENGINE AHMAD MUIZZ BIN ISHAK Thesis submitted in fulfilment of the requirements for the award of the Bachelor of Mechanical Engineering
More informationD-SEND#2 - FLIGHT TESTS FOR LOW SONIC BOOM DESIGN TECHNOLOGY
ICAS 2016 25-30 September, Daejeon, KOREA D-SEND#2 - FLIGHT TESTS FOR LOW SONIC BOOM DESIGN TECHNOLOGY Kenji Yoshida Masahisa Honda Aeronautical Technology Directorate Japan Aerospace Exploration Agency
More informationHeat Shield Design Project
Name Class Period Heat Shield Design Project The heat shield is such a critical piece, not just for the Orion mission, but for our plans to send humans into deep space. Final Points Earned Class Participation/Effort
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 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 informationTENSEGRITY HEAT SHIELD FOR ATMOSPHERIC ENTRY THROUGH CELESTIAL BODIES
Proceedings of the ASME 2016 International Design Engineering Technical Conferences & Computers and Information in Engineering Conference IDETC/CIE 2016 August 21-August 24, 2016, Charlotte, NC, USA IDETC2016-60086
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 information[Rao, 4(7): July, 2015] ISSN: (I2OR), Publication Impact Factor: 3.785
IJESRT INTERNATIONAL JOURNAL OF ENGINEERING SCIENCES & RESEARCH TECHNOLOGY CFD ANALYSIS OF GAS COOLER FOR ASSORTED DESIGN PARAMETERS B Nageswara Rao * & K Vijaya Kumar Reddy * Head of Mechanical Department,
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 informationAIRCRAFT WING DESIGN BY USING THE FINITE ELEMENT METHOD AND THE ANALYTICAL TECHNIQUES GRADUATION PROJECT. Emre ÜNLÜ. Aeronautical Engineering
ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS AIRCRAFT WING DESIGN BY USING THE FINITE ELEMENT METHOD AND THE ANALYTICAL TECHNIQUES GRADUATION PROJECT Emre ÜNLÜ Aeronautical Engineering
More informationName: Space Exploration PBL
Name: Space Exploration PBL Students describe the history and future of space exploration, including the types of equipment and transportation needed for space travel. Students design a lunar buggy and
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 informationCFD Investigation of Influence of Tube Bundle Cross-Section over Pressure Drop and Heat Transfer Rate
CFD Investigation of Influence of Tube Bundle Cross-Section over Pressure Drop and Heat Transfer Rate Sandeep M, U Sathishkumar Abstract In this paper, a study of different cross section bundle arrangements
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 informationDesign, Fabrication & Simulation of a Semi-Rigid Helicopter Swashplate Control Mechanisms
International Journal of Engineering Science Invention (IJESI) ISSN (Online): 2319 6734, ISSN (Print): 2319 6726 Volume 7 Issue 12 Ver I Dec 2018 PP 16-21 Design, Fabrication & Simulation of a Semi-Rigid
More informationSubsonic Parachutes for Future Mars Missions
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 Mars Parachutes
More informationUse of Flow Network Modeling for the Design of an Intricate Cooling Manifold
Use of Flow Network Modeling for the Design of an Intricate Cooling Manifold Neeta Verma Teradyne, Inc. 880 Fox Lane San Jose, CA 94086 neeta.verma@teradyne.com ABSTRACT The automatic test equipment designed
More informationRDT&E BUDGET ITEM JUSTIFICATION SHEET (R-2 Exhibit) June 2001
PE NUMBER: 0603302F PE TITLE: Space and Missile Rocket Propulsion BUDGET ACTIVITY RDT&E BUDGET ITEM JUSTIFICATION SHEET (R-2 Exhibit) June 2001 PE NUMBER AND TITLE 03 - Advanced Technology Development
More informationEuropean Workshop on Aircraft Design Education 2002
From Specification & Design Layout to Control Law Development for Unmanned Aerial Vehicles Lessons Learned from Past Experience Zdobyslaw Goraj WUT, Poland Philip Ransom, Paul Wagstaff Kingston University,
More informationTHE EFFECT OF VORTEX TRAP ON HELICOPTER BLADE LIFT
THE EFFECT OF VORTEX TRAP ON HELICOPTER BLADE LIFT MOHD FAUZI BIN YAAKUB A thesis submitted in fulfilment of the requirements for the award of the Degree of Master of Mechanical Engineering Faculty of
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 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 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 informationThe Effects of Damage and Uncertainty on the Aeroelastic / Aeroservoelastic Behavior and Safety of Composite Aircraft. JAMS Meeting, May
The Effects of Damage and Uncertainty on the Aeroelastic / Aeroservoelastic Behavior and Safety of Composite Aircraft JAMS Meeting, May 2010 1 JAMS Meeting, May 2010 2 Contributors Department of Aeronautics
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 informationAerospace Propulsion Systems
Brochure More information from http://www.researchandmarkets.com/reports/1288672/ Aerospace Propulsion Systems Description: Aerospace Propulsion Systems is a unique book focusing on each type of propulsion
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 informationDIRECT TORQUE CONTROL OF A THREE PHASE INDUCTION MOTOR USING HYBRID CONTROLLER. RAJESHWARI JADI (Reg.No: M070105EE)
DIRECT TORQUE CONTROL OF A THREE PHASE INDUCTION MOTOR USING HYBRID CONTROLLER A THESIS Submitted by RAJESHWARI JADI (Reg.No: M070105EE) In partial fulfillment for the award of the Degree of MASTER OF
More informationCurb Weights of HD Vehicles a study about possibilities to increase payload and reduce fuel consumption
a study about possibilities to increase payload and reduce fuel consumption Markku Ikonen, (M. Sc.) Senior Lecturer Engineering student Kalle Viljanen Engineering student Arvet Palkov Turku University
More informationInternational Journal of Engineering Research and General Science Volume 5, Issue 3, May-June, 2017 ISSN
HEAT TRANSFER AND FLUID FLOW ANALYSIS OF CIRCULAR RECEIVER TUBE OF SOLAR COLLECTOR Swati Patel 1, M.A.Kadam 2 1 P.G. Student, Department of Mechanical Engineering, Bharati Vidyapeeth Deemed University,
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 information2012/2013 AIAA Foundation Graduate Team Aircraft Design Competition
2012/2013 AIAA Foundation Graduate Team Aircraft Design Competition High Altitude Long Endurance (HALE)Unmanned Aerial System (UAS) for Missile Defense with Directed Energy (DE) Laser Weapon I. Rules-General
More informationIRENE PROGRAM. European Sounding Rocket Experiment on Hypersonic Deployable Re-entry Demonstrator
IRENE PROGRAM European Sounding Rocket Experiment on Hypersonic Deployable Re-entry Demonstrator R. Savino, R. Aurigemma, Dr. Pasquale Dell Aversana, L. Gramiccia, F. Punzo, J. Longo, L. Scolamiero, L.
More informationOpportunities For Innovative Collaboration. Propulsion Directorate Propulsion & Power for the 21st Century Warfighter
Opportunities For Innovative Collaboration Propulsion Directorate Propulsion & Power for the 21st Century Warfighter Propulsion Directorate Our Mission Create and transition advanced air breathing and
More informationEXPERIMENTAL INVESTIGATIONS OF DOUBLE PIPE HEAT EXCHANGER WITH TRIANGULAR BAFFLES
International Research Journal of Engineering and Technology (IRJET) e-issn: 2395-56 Volume: 3 Issue: 8 Aug-216 www.irjet.net p-issn: 2395-72 EXPERIMENTAL INVESTIGATIONS OF DOUBLE PIPE HEAT EXCHANGER WITH
More informationParticle size and distribution of oil mist from cooking equipments in electrical commercial kitchens
Indoor Air 8, 7- August 8, Copenhagen, Denmark - Paper ID: 4 Particle size and distribution of oil mist from cooking equipments in electrical commercial kitchens Ryohei oshida, asushi Kondo, Hajime oshino,,
More informationINVESTIGATION OF HEAT TRANSFER CHARACTERISTICS OF CIRCULAR AND DIAMOND PILLARED VANE DISC BRAKE ROTOR USING CFD
SDRP JOURNAL OF NANOTECHNOLOGY & MATERIAL SCIENCE. INVESTIGATION OF HEAT TRANSFER CHARACTERISTICS OF CIRCULAR AND DIAMOND PILLARED VANE DISC BRAKE ROTOR USING CFD Research AUTHOR: A.RAJESH JUNE 2017 1
More informationTurbostroje 2015 Návrh spojení vysokotlaké a nízkotlaké turbíny. Turbomachinery 2015, Design of HP and LP turbine connection
Turbostroje 2015 Turbostroje 2015 Návrh spojení vysokotlaké a nízkotlaké turbíny Turbomachinery 2015, Design of HP and LP turbine connection J. Hrabovský 1, J. Klíma 2, V. Prokop 3, M. Komárek 4 Abstract:
More informationTHERMAL PROTECTION SYSTEM SENSORS
WHITE PAPER TO THE NRC DECADAL SURVEY MARS SUBPANEL AND OUTER PLANETS SUB-PANEL THERMAL PROTECTION SYSTEM SENSORS BY Edward R. Martinez, Ames Research Center, Mountain View, CA Edward.R.Martinez@NASA.gov
More informationFinite Element Analysis on Thermal Effect of the Vehicle Engine
Proceedings of MUCEET2009 Malaysian Technical Universities Conference on Engineering and Technology June 20~22, 2009, MS Garden, Kuantan, Pahang, Malaysia Finite Element Analysis on Thermal Effect of the
More informationNational Aeronautics and Space Administration. Inflatable Reentry Vehicles and Instrumentation Needs
National Aeronautics and Space Administration Inflatable Reentry Vehicles and Instrumentation Needs Robert Dillman, NASA Langley Research Center December 15, 2015 Background: Why Inflatables? Payload mass
More informationInvestigation of converging slot-hole geometry for film cooling of gas turbine blades
Project Report 2010 MVK160 Heat and Mass Transport May 12, 2010, Lund, Sweden Investigation of converging slot-hole geometry for film cooling of gas turbine blades Tobias Pihlstrand Dept. of Energy Sciences,
More informationNacelle Chine Installation Based on Wind-Tunnel Test Using Efficient Global Optimization
Trans. Japan Soc. Aero. Space Sci. Vol. 51, No. 173, pp. 146 150, 2008 Nacelle Chine Installation Based on Wind-Tunnel Test Using Efficient Global Optimization By Masahiro KANAZAKI, 1Þ Yuzuru YOKOKAWA,
More informationModeling and Control for Turboelectric Aircraft
Modeling and Control for Turboelectric Aircraft Aidan Dowdle adowdle@mit.edu NASA GRC AS&ASTAR Fellow 11/1/17 This material is based upon work supported by the National Aeronautics and Space Administration
More informationSuborbital Flight Opportunities for Cubesat-Class Experiments Aboard NLV Test Flights
Suborbital Flight Opportunities for Cubesat-Class Experiments Aboard NLV Test Flights Christopher Bostwick John Garvey Garvey Spacecraft 9th ANNUAL CUBESAT DEVELOPERS WORKSHOP April 18-20, 2012 Cal Poly
More informationEngine Encapsulation for Increased Fuel Efficiency of Road Vehicles
Engine Encapsulation for Increased Fuel Efficiency of Road Vehicles A project within the program: Energy and Environment Start: July 2013 End: June 2017 Blago Minovski Department of Mechanics and Maritime
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 informationAdrestia. A mission for humanity, designed in Delft. Challenge the future
Adrestia A mission for humanity, designed in Delft 1 Adrestia Vision Statement: To inspire humanity by taking the next step towards setting a footprint on Mars Mission Statement Our goal is to design an
More informationEffects of Dilution Flow Balance and Double-wall Liner on NOx Emission in Aircraft Gas Turbine Engine Combustors
Effects of Dilution Flow Balance and Double-wall Liner on NOx Emission in Aircraft Gas Turbine Engine Combustors 9 HIDEKI MORIAI *1 Environmental regulations on aircraft, including NOx emissions, have
More informationSuccess of the H-IIB Launch Vehicle (Test Flight No. 1)
53 Success of the H-IIB Launch Vehicle (Test Flight No. 1) TAKASHI MAEMURA *1 KOKI NIMURA *2 TOMOHIKO GOTO *3 ATSUTOSHI TAMURA *4 TOMIHISA NAKAMURA *5 MAKOTO ARITA *6 The H-IIB launch vehicle carrying
More informationDevelopment of Internationally Competitive Solid Rocket Booster for H3 Launch Vehicle
Development of Internationally Competitive Solid Rocket Booster for H3 Launch Vehicle YANAGISAWA Masahiro : Space Launch Vehicle Project Office, Rocket Systems Department, IHI AEROSPACE Co., Ltd. KISHI
More informationInternational Journal of Scientific & Engineering Research, Volume 6, Issue 10, October ISSN
International Journal of Scientific & Engineering Research, Volume 6, Issue 0, October-205 97 The Effect of Pitch and Fins on Enhancement of Heat Transfer in Double Pipe Helical Heat Exchanger 2 Abdulhassan
More informationAircraft Gas Turbine Engine Technology Treager
We have made it easy for you to find a PDF Ebooks without any digging. And by having access to our ebooks online or by storing it on your computer, you have convenient answers with aircraft gas turbine
More informationFACT SHEET SPACE SHUTTLE EXTERNAL TANK. Space Shuttle External Tank
Lockheed Martin Space Systems Company Michoud Operations P.O. Box 29304 New Orleans, LA 70189 Telephone 504-257-3311 l FACT SHEET SPACE SHUTTLE EXTERNAL TANK Program: Customer: Contract: Company Role:
More informationSystem Analysis of the Diesel Parallel Hybrid Vehicle Powertrain
System Analysis of the Diesel Parallel Hybrid Vehicle Powertrain Kitae Yeom and Choongsik Bae Korea Advanced Institute of Science and Technology ABSTRACT The automotive industries are recently developing
More informationCONTENTS Duct Jet Propulsion / Rocket Propulsion / Applications of Rocket Propulsion / 15 References / 25
CONTENTS PREFACE xi 1 Classification 1.1. Duct Jet Propulsion / 2 1.2. Rocket Propulsion / 4 1.3. Applications of Rocket Propulsion / 15 References / 25 2 Definitions and Fundamentals 2.1. Definition /
More informationINTERCOOLER FOR EXTREMELY LOW TEMPERATURES OF CHARGING
Journal of KONES Powertrain and Transport, Vol. 7, No. 4 200 INTERCOOLER FOR EXTREMELY LOW TEMPERATURES OF CHARGING Emil Toporcer, Peter Tunik University of Žilina, Faculty of Mechanical Engineering Department
More informationA BRIEF DISCUSSION ABOUT REENTRY VEHICLES
Volume 02 - Issue 02 February 2017 PP. 50-63 A BRIEF DISCUSSION ABOUT REENTRY VEHICLES AMRITA MALLICK, BURHANUDDIN KAPADIA, AMAN ARNOLD PINTO Department of Aeronautical Engineering MVJ College of Engineering
More informationTeam Introduction Competition Background Current Situation Project Goals Stakeholders Use Scenario Customer Needs Engineering Requirements
Team Introduction Competition Background Current Situation Project Goals Stakeholders Use Scenario Customer Needs Engineering Requirements Constraints Project Plan Risk Analysis Questions Christopher Jones
More informationRotary Wing Decelerators for Miniature Atmospheric Entry Probes
20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar 4-7 May 2009, Seattle, Washington AIAA 2009-2996 Rotary Wing Decelerators for Miniature Atmospheric Entry Probes First Austin
More informationHeat transfer enhancement of a single row of tube
Heat transfer enhancement of a single row of tube Takayuki Tsutsui 1,* 1 Department of Mechanical Engineering, The National Defense Academy, 1-10-20 Hashirimizu, Yokosuka, Kanagawa 238-8686 Japan Abstract.
More informationDESIGN OF A MODULAR STEERING SYSTEM TEST BENCH FOR DURABILITY, PERFORMANCE AND CHARACTERIZATION TESTS
DESIGN OF A MODULAR STEERING SYSTEM TEST BENCH FOR DURABILITY, PERFORMANCE AND CHARACTERIZATION TESTS Elif KILINÇ, Dr. Orhan ATABAY, Şeref Server ERSOLMAZ, Hatice ERDOĞAN, Automotive Technologies Research
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 informationLiquid Fuel Rocket Engine Capstone
Portland State Unversity Liquid Fuel Rocket Engine Capstone Progress Report - Winter 2016 Cam Yun, John Tucker, Kristin Travis, Tamara Dib, Taylor Rice & Bianca Viggiano Industry Advisor Erin Schmidt Sponsoring
More information2019 SpaceX Hyperloop Pod Competition
2019 SpaceX Hyperloop Pod Competition Rules and Requirements August 23, 2018 CONTENTS 1 Introduction... 2 2 General Information... 3 3 Schedule... 4 4 Intent to Compete... 4 5 Preliminary Design Briefing...
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 informationAerodynamic Design of the Reichstag
Aerodynamic Design of the Reichstag Klaus Peter Neitzke Formerly TU Dresden, now AIRBUS - Wind Tunnel Department The work was performed from 1995 to 1999 at the TU Dresden 18th Liepmann-Ludwieg-Seminar
More informationEnhance the Performance of Heat Exchanger with Twisted Tape Insert: A Review
Enhance the Performance of Heat Exchanger with Twisted Tape Insert: A Review M.J.Patel 1, K.S.Parmar 2, Umang R. Soni 3 1,2. M.E. Student, department of mechanical engineering, SPIT,Basna, Gujarat, India,
More informationFINITE ELEMENT METHOD IN CAR COMPATIBILITY PHENOMENA
Journal of KONES Powertrain and Transport, Vol. 18, No. 4 2011 FINITE ELEMENT METHOD IN CAR COMPATIBILITY PHENOMENA Marcin Lisiecki Technical University of Warsaw Faculty of Power and Aeronautical Engineering
More informationTuition fees. Taught courses Important notes about fees
Tuition s Taught courses 2017-2018 Important notes about s The s outlined within this document apply to all students whose initial date of registration falls on or between 1 August 2017 and 31 July 2018.
More informationIndustrial Use of EsDs ETP4HPC Workshop 22 June 2017 Frankfurt DLR CFD Solver TAU & Flucs for external Aerodynamic
Industrial Use of EsDs ETP4HPC Workshop 22 June 2017 Frankfurt DLR CFD Solver TAU & Flucs for external Aerodynamic Thomas Gerhold Institute of Aerodynamics and Flow Technology German Aerospace Center (DLR)
More informationThe Effects of Damage and Uncertainty on the Aeroelastic / Aeroservoelastic Behavior and Safety of Composite Aircraft
The Effects of Damage and Uncertainty on the Aeroelastic / Aeroservoelastic Behavior and Safety of Composite Aircraft Presented by Professor Eli Livne Department of Aeronautics and Astronautics University
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 informationMultifunction Rocket System Development based on Advanced Hybrid Propulsion
SpaceOps Conferences 16-20 May 2016, Daejeon, Korea SpaceOps 2016 Conference 10.2514/6.2016-2586 Multifunction Rocket System Development based on Advanced Hybrid Propulsion Yen-Sen Chen, Robert Cheng,
More informationDevelopment of Main Propulsion System for Reusable Sounding Rocket: Design Considerations and Technology Demonstration
Trans. JSASS Aerospace Tech. Japan Vol. 12, No. ists29, pp. Tm_1-Tm_6, 2014 Topics Development of Main Propulsion System for Reusable Sounding Rocket: Design Considerations and Technology Demonstration
More informationCable-Controlled Aeroshell Deceleration System
Cable-Controlled Aeroshell Deceleration System University of Illinois at Urbana-Champaign Department of Aerospace Engineering 104 S. Wright Street Urbana, Illinois 61801 Team Members: Sashank Gummella,
More informationDesign, Construction and Testing of a Desktop Supersonic Wind Tunnel
Design, Construction and Testing of a Desktop Supersonic Wind Tunnel Vi H. Rapp, Jennifer Jacobsen, Mark Lawson, Andrew Parker, Kuan Chen * Department of Mechanical Engineering University of Utah Salt
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 informationSimulation Studies on the Effect of Porous Twisted Plate Inserts on the Performance of Fire Tube Steam Packaged Boiler
Simulation Studies on the Effect of Porous Twisted Plate Inserts on the Performance of Fire Tube Steam Packaged Boiler S. Hassan *,a, M. K. Roslim b and R. M. Zain c Mechanical Engineering Department,
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 informationDynamic Modelling of Hybrid System for Efficient Power Transfer under Different Condition
RESEARCH ARTICLE OPEN ACCESS Dynamic Modelling of Hybrid System for Efficient Power Transfer under Different Condition Kiran Kumar Nagda, Prof. R. R. Joshi (Electrical Engineering department, Collage of
More informationEvaluation of the Effect of Tank Temperature on Transport of RAT (Atmospheric Distillation Residue) for the Potiguar Refinery Clara Camarão (RPCC)
Evaluation of the Effect of Tank Temperature on Transport of RAT (Atmospheric Distillation Residue) for the Potiguar Refinery Clara Camarão (RPCC) Gildson Bastos Félix Chemtech Rodrigo Peralta Muniz Moreira
More informationDEVELOPMENT OF COMPRESSED AIR POWERED ENGINE SYSTEM BASED ON SUBARU EA71 MODEL CHEN RUI
DEVELOPMENT OF COMPRESSED AIR POWERED ENGINE SYSTEM BASED ON SUBARU EA71 MODEL CHEN RUI A project report submitted in partial fulfillment of the requirements for the award of the degree of Bachelor of
More informationDevelopment of Japan s Next Flagship Launch Vehicle
20 Development of Japan s Next Flagship Launch Vehicle - To compete and survive in the global commercial market - ATSUTOSHI TAMURA *1 MAYUKI NIITSU *2 TAKANOBU KAMIYA *3 AKIHIRO SATO *4 KIMITO YOSHIKAWA
More informationSMALLSAT PROPULSION. Pete Smith, Roland McLellan Marotta UK Ltd, Cheltenham, and Dave Gibbon SSTL, Guildford, UK.
SMALLSAT PROPULSION Pete Smith, Roland McLellan Marotta UK Ltd, Cheltenham, and Dave Gibbon SSTL, Guildford, UK. ABSTRACT This paper presents an overview of the components, systems and technologies used
More informationABSTRACT I. INTRODUCTION III. GEOMETRIC MODELING II. LITERATURE REVIW
2017 IJSRSET Volume 3 Issue 5 Print ISSN: 2395-1990 Online ISSN : 2394-4099 Themed Section: Engineering and Technology Performance Analysis of Helical Coil Heat Exchanger Using Numerical Technique Abhishek
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 informationSUMMARY: On July 8, 2016, the Department of Commerce (the Department) published its
DEPARTMENT OF COMMERCE International Trade Administration A-570-016 This document is scheduled to be published in the Federal Register on 08/22/2016 and available online at http://federalregister.gov/a/2016-20023,
More informationROCKET - ASSISTED AMMUNITION TECHNOLOGIES for 120 mm MORTARS
ROCKET - ASSISTED AMMUNITION TECHNOLOGIES for 120 mm MORTARS MUNITIONS TECHNOLOGY SYMPOSIUM In Pleasanton on April 11-12, 2000 THOMSON-CSF DAIMLERCHRYSLER AEROSPACE 50 % 50 % TDA 100 % FZ Other subsidiaries
More informationModelling Combustion in DI-SI using the G-equation Method and Detailed Chemistry: Emissions and knock. M.Zellat, D.Abouri, Y.Liang, C.
Modelling Combustion in DI-SI using the G-equation Method and Detailed Chemistry: Emissions and knock Realize innovation. M.Zellat, D.Abouri, Y.Liang, C.Kralj Main topics of the presentation 1. Context
More information