Deployment and Drop Test for Inflatable Aeroshell for Atmospheric Entry Capsule with using Large Scientific Balloon

Size: px
Start display at page:

Download "Deployment and Drop Test for Inflatable Aeroshell for Atmospheric Entry Capsule with using Large Scientific Balloon"

Transcription

1 , 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 Nagata, Masashi Koyama (The University of Tokyo) Daisuke Abe, Yusuke Kimura, A. Koichi Hayashi (Aoyama Gakuin University) Hitoshi Makino (Tokai University) Daisuke Akita (Tokyo Institute of Technology)

2 CONTENTS Background Membrane aeroshell for atmospheric-entry capsule (MAAC) Advantage and key technology. Past research Aerodynamics of flexible structure. Investigation of Inflatable structure and material performance. Development schedule. Second balloon experiment (MINI-MAAC) Objectives. Experimental vehicle. Results. Conclusions. Future Plan Atmospheric entry demonstration using sounding rocket.

3 Background HAYABUSA capsule returned to the earth with success. From now on, even more sample return missions and planetary entry missions will be proposed. Withstand Aerodynamic heating We weed innovation of atmospheric-entry system for frequent space transportation between space and planet surface. One of the candidates is flexible aeroshell system Avoid Aerodynamic heating Large and light aeroshell is deployed in the space before reentry Flexible aeroshell can be packed in launching and operating in space. Vehicle re-enters into atmosphere with low aerodynamic heating and make soft landing without a parachute

4 Advantage and key technology <Advantages of flexible aeroshell> Significant reduction of aerodynamic heating during reentry. 1) To understand aerodynamic characteristics in whole range of Mach number 2) To develop a large but low-mass flexible aeroshell utilizing inflatable structure Vehicle with large and light aeroshell can decelerate at high altitude where the atmospheric density is very low. Soft landing without additional parachute system or retro jet. Large and light aeroshell also works to reduce terminal velocity same as conventional parachute before landing. <Key technologies of flexible aeroshell> Flare-type membrane aeroshell supported by inflatable torus. Inflatable torus 3) To develop and evaluate flexible material especially thermal durability Thin membrane Capsule (payload)

5 Past research 1 Aerodynamics is first motivation of this research, because behavior of flexible structure was not understand, especially in supersonic flow. Can the flexible aeroshells be used as decelerator of a high speed vehicle like a reentry system? Various wind tunnel test & Numerical simulation Demonstration <First balloon experiment> Transonic Subsonic 1.5m Supersonic Numerical simulation Successful flight!! Vehicle is quit steady. Mach number in flight test is lower than (Subsonic ~ Transonic)

6 Past research 2 After the first balloon flight test, our group started various researches to apply this system to actual mission. Heater (hot wind) <Thermal durability> Laser Structure strength <Inflatable aeroshell> Demonstration Deployment in vacuum chamber Hypersonic wind tunnel test. Demonstration Second balloon test.

7 Development schedule Inflatable aeroshell Aerodynamics *Wind tunnel test *Numerical simulation <1 st Balloon experiment> Subsonic flight demonstration Thermal durability xx *Aeroshell system trade-off *Try and error using prototype *deployment demonstration *Structural strength test *Full scale model demonstration *Wind tunnel test *Numerical simulation <2 nd Balloon experiment> <3 rd Balloon experiment> *Aerodynamics in Hypersonic flow *Aerodynamics in Low speed flow *Aerodynamic in actual condition *Aerodynamics of full scale model <Hypersonic wind tunnel test> <Sounding rocket experiment> <Re-entry demonstration> *Martial testing *Aerodynamics heating environment *Actual condition demonstration <Mars exploration and /or Transportation system from LEO>

8 2 nd balloon experiment MIMI-MAAC Deployment and Drop Test of Inflatable Aeroshell for Atmospheric-entry Capsule

9 MINI-MAAC (2 nd balloon test) <Objectives> To demonstrate deployment and free flight of flare-type aeroshell supported by inflatable torus which is one of the next generation reentry system. To demonstrate the aeroshell deployment in vacuum condition in the air with remote control. To acquire the knowledge of the structural strength of inflatable torus against aerodynamic force during free flight condition. To obtain the aerodynamic characteristics of low-ballistic-coefficient vehicle in subsonic regime in free flight condition. Launch Free drop All flight data is transmitted to ground station. Deployment and Separation Aeroshell is packed Ascend at ALT=25km Vehicle separation from gondola after aeroshell deployment. We does not request recover of experimental vehicle

10 Experimental flight vehicle Capsule Packed aeroshell Deployed aeroshell 64mm 60deg Center of mass CCD camera with fish-eye lens 200mm 1264mm All of device including sensor, telemetry, transmitter and battery is in capsule. Measurement item: Image of aeroshell, Ambient pressure, Inflatable pressure, Position by GPS, Accelerator, Angle velocity and so on Flare part was made of Nylon cloth. Inflatable torus was made of Nylon cloth coated by Urethane rubber. Total mass : 3.375kg

11 Flight operation This experiment was carried out at TARF in 25 th August, This is first fight with user s payload in TARF which is new balloon base in Japan. Electrical compatibility check Just before launch Mechanical compatibility check User s room Successful launch and ascend.

12 Results of MINI-MAAC We acquired a lot of information and technology for flare-type inflatable aeroshell from MINI-MAAC experiment. The data in free flight condition is acquired just only flight test. For example, Deployment demonstration in vacuum condition. Vehicle trajectory in horizontal direction compared with wind profile. Drag coefficient in low speed regime during free flight. Structural strength of inflatable torus against aerodynamic force. Deformation of flare type aeroshell. Attitude of capsule during flight. In this presentation, three topics of them will be introduced.

13 Deployment demonstration The inflatable aeroshell was deployed by injecting gas at altitude 25km. <Compact and simple gas injection system> Vehicle was separated from gondola after deployment Deployment was completed in 0.3 second after gas injection

14 Drag coefficient Drag coefficient during free flight was estimated from altitude history. <Time history of altitude> <Comparison with simulation> Aeroshell was collapsed in 24 min after separation at altitude 4.0km. This is as planned Drag coefficient of vehicle during flight is estimated as In wind tunnel test, CD is measured as 0.9

15 Structural Strength of inflatable torus The inner pressure in inflatable torus is about 60kPaA. The aeroshell was collapsed during flight due to ambient pressure increase <Time history of inflatable pressure> <Collapse of aeroshell> Captured by onboard CCD camera with fish-eye lens 5.2kPa Aeroshell was collapsed when the differential pressure is 5.2kPa in free flight. The results is discussed for the design of the vehicle, comparing with wind tunnel data.

16 Conclusions of MINI-MAAC Our group carried out Deployment and drop test of inflatable aeroshell using large scientific balloon in series of development of membrane aeroshell for new atmospheric-entry system Our group achieved the following results in this test. 1) Successful deployment of inflatable aeroshell in the high altitude condition with remote control. 2) Aerodynamics data (drag coefficient) of vehicle with inflatable aeroshell in free flight condition. 3) Knowledge about structural strength of flare type membrane aeroshell supported by inflatable torus in free flight condition. These data will be very useful for the vehicle design in next phase of development.

17 Future Plan Next milestone : Re-entry demonstration using sounding rocket. 3. Aeroshell is deployment in zero gravity and vacuum condition 2. Fairing open and vehicle separation after rocket engine stopped 4. Aeroshell shape and vehicle attitude become stable by aerodynamic force. Packed aeroshell 5. At altitude about 55km Maximum dynamic pressure: 0.65kPa Maximum Mach number: 4.45 Maximum heat flux: 20.0kW/m 2 Capsule 1. Aeroshell is packed around the capsule in launching 6. Vehicle splash down with 16.8m/s in 1015 sec after top of trajectory. The vehicle floats on the sea with buoyant force of inflatable torus.

18 For sounding rocket experiment We are designing the experimental vehicle for reentry demonstration now. The aeroshell which have high temperature durability is being developed for reentry demonstration 0.2m This experiment is planned to carried out in m

19 Acknowledgement The balloon experiments in this study were carried out with the collaboration of Research and Operation Office for Scientific Ballooning, ISAS / JAXA. We would like to thank to the staff of Research and Operation Office for Scientific Ballooning and Taiki Aerospace Research Field for the appropriate supports and advices.

Deployment and Flight Test of Inflatable Membrane Aeroshell using Large Scientific Balloon

Deployment 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 information

Reentry Demonstration Plan of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket

Reentry 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 information

Hypersonic 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 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 information

Structural 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 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 information

Hypersonic Wind Tunnel Test of a Flare-type Membrane Aeroshell for Atmospheric Entry Capsules

Hypersonic 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 information

MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT. Nazlıcan KARACA

MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT. Nazlıcan KARACA ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS MULTIDISCIPLINARY ANALYSIS OF AN INFLATABLE AND FLEXIBLE VEHICLE IN SUBORBITAL REENRTY GRADUATION PROJECT Nazlıcan KARACA Department

More information

Venus 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) 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 information

Subsonic Parachutes for Future Mars Missions

Subsonic 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 information

External Aerodynamics: Lift of airship created only by buoyancy which doesn t need lift generating surface like an airfoil or a wing

External 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 information

Coupled Aero-Structural Modelling and Optimisation of Deployable Mars Aero-Decelerators

Coupled 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 information

Case Study: ParaShield

Case 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 information

NASA - USLI Presentation 1/23/2013. University of Minnesota: USLI CDR 1

NASA - 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 information

Jordan 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 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 information

Adrestia. A mission for humanity, designed in Delft. Challenge the future

Adrestia. 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 information

LOW 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 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 information

SpaceLoft XL Sub-Orbital Launch Vehicle

SpaceLoft 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 information

CHANGING ENTRY, DESCENT, AND LANDING PARADIGMS FOR HUMAN MARS LANDER

CHANGING 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 information

Pre-Launch Procedures

Pre-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 information

Long-Range Rovers for Mars Exploration and Sample Return

Long-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 information

SSC Swedish Space Corporation

SSC 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 information

ReachMars 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 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 information

Georgia 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 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 information

Keywords: Supersonic Transport, Sonic Boom, Low Boom Demonstration

Keywords: 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 information

Entry, 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 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 information

IRENE PROGRAM. European Sounding Rocket Experiment on Hypersonic Deployable Re-entry Demonstrator

IRENE 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 information

ENGINE STARTING PERFORMANCE EVALUATION AT STATIC STATE CONDITIONS USING SUPERSONIC AIR INTAKE

ENGINE 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 information

SILENT SUPERSONIC TECHNOLOGY DEMONSTRATION PROGRAM

SILENT 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 information

Rocketry, the student way

Rocketry, 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 information

Supersonic Combustion Experimental Investigation at T2 Hypersonic Shock Tunnel

Supersonic 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 information

IST Sounding Rocket Momo User Guide

IST Sounding Rocket Momo User Guide 2 Table of contents Revision History Note 1.Introduction 1 1.Project Overview 1 2. About the Momo Sounding Rocket 1 3.Launch Facility 2.Mission Planning Guide 2 1. Flight stages 2 2. Visibility from the

More information

Mars Aerocapture/Aerobraking Aeroshell Configurations by Abraham Chavez

Mars 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 information

K. P. J. Reddy Department of Aerospace Engineering Indian Institute of Science Bangalore , India.

K. 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 information

LOW 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 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 information

Challenges of Designing the MarsNEXT Network

Challenges 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 information

Preface. Acknowledgments. List of Tables. Nomenclature: organizations. Nomenclature: acronyms. Nomenclature: main symbols. Nomenclature: Greek symbols

Preface. 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 information

From MARS To MOON. V. Giorgio Director of Italian Programs. Sorrento, October, All rights reserved, 2007, Thales Alenia Space

From 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 information

OMOTENASHI. (Outstanding MOon exploration TEchnologies demonstrated by NAno Semi-Hard Impactor)

OMOTENASHI. (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 information

Observation of Flame Stabilized at a Hydrogen-Turbojet-Engine Injector Installed into a Lab-Scale Combustion Wind Tunnel

Observation 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 information

Aircraft Pollution Monitoring Project

Aircraft 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 information

Development of a Low Cost Suborbital Rocket for Small Satellite Testing and In-Space Experiments

Development of a Low Cost Suborbital Rocket for Small Satellite Testing and In-Space Experiments Development of a Low Cost Suborbital Rocket for Small Satellite Testing and In-Space Experiments Würzburg, 2015-09-15 (extended presentation) Dr.-Ing. Peter H. Weuta Dipl.-Ing. Neil Jaschinski WEPA-Technologies

More information

DemoSat-B User s Guide

DemoSat-B User s Guide January 5, 2013 Authors: Chris Koehler & Shawn Carroll Revisions Revision Description Date Approval DRAFT Initial release 7/31/2009 1 Updated for 2011 2012 program dates, added revision page 9/27/11 LEM

More information

Auburn University. Project Wall-Eagle FRR

Auburn 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 information

Blue Origin Achievements and plans for the future

Blue Origin Achievements and plans for the future Blue Origin Achievements and plans for the future Blue Origin A private aerospace manufacturer and spaceflight services company Founded in 2000 by Amazon.com CEO Jeff Bezos Headquarters in Kent (Seattle),

More information

Design Rules and Issues with Respect to Rocket Based Combined Cycles

Design Rules and Issues with Respect to Rocket Based Combined Cycles Respect to Rocket Based Combined Cycles Tetsuo HIRAIWA hiraiwa.tetsuo@jaxa.jp ABSTRACT JAXA Kakuda space center has been studying rocket based combined cycle engine for the future space transportation

More information

D-SEND#2 - FLIGHT TESTS FOR LOW SONIC BOOM DESIGN TECHNOLOGY

D-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 information

Formation Flying Experiments on the Orion-Emerald Mission. Introduction

Formation Flying Experiments on the Orion-Emerald Mission. Introduction Formation Flying Experiments on the Orion-Emerald Mission Philip Ferguson Jonathan P. How Space Systems Lab Massachusetts Institute of Technology Present updated Orion mission operations Goals & timelines

More information

Development of an Extended Range, Large Caliber, Modular Payload Projectile

Development 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 information

Experimental Testing of a Rotating Detonation Engine Coupled to Nozzles at Conditions Approaching Flight

Experimental Testing of a Rotating Detonation Engine Coupled to Nozzles at Conditions Approaching Flight 25 th ICDERS August 2 7, 205 Leeds, UK Experimental Testing of a Rotating Detonation Engine Coupled to Nozzles at Conditions Approaching Flight Matthew L. Fotia*, Fred Schauer Air Force Research Laboratory

More information

SPARTAN. Date: All rights reserved 2011, Thales Alenia Space. Business Unit Space Infrastructures & Transportation

SPARTAN. Date: All rights reserved 2011, Thales Alenia Space. Business Unit Space Infrastructures & Transportation SPARTAN Date: Business Unit Space Infrastructures & Transportation February the 17 2011 All rights reserved 2011, Thales Alenia Space Project Overview 2 From 3 rd Fp7 Space Call Grant Agreement n. 262837

More information

Auburn University Student Launch. PDR Presentation November 16, 2015

Auburn 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 information

CHAPTER 6 ENVIRONMENTAL CONDITIONS

CHAPTER 6 ENVIRONMENTAL CONDITIONS ENVIRONMENTAL CONDITIONS 6.1 Summary This chapter introduces the natural environment of launch site, thermal environment during SC operation, thermal and mechanical environments (vibration, shock & noise)

More information

BY 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 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 information

Success of the H-IIB Launch Vehicle (Test Flight No. 1)

Success 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 information

DRAG CHARACTERISTICS AND SUITABILITY OF TEE-FOOT LON$ PARACHUSI-ETC (U) NAY 61 c T calzanwo UNCLASSFIED

DRAG 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 information

SMARTSat. Shape Memory Alloy Research Technology Satellite. Allison Barnard Alicia Broederdorf. Texas A&M University Space Engineering Institute

SMARTSat. Shape Memory Alloy Research Technology Satellite. Allison Barnard Alicia Broederdorf. Texas A&M University Space Engineering Institute SMARTSat Shape Memory Alloy Research Technology Satellite Allison Barnard Alicia Broederdorf Texas A&M University Space Engineering Institute Outline Introduction / Mission Objectives Systems Overview

More information

INTERMEDIATE EXPERIMENTAL VEHICLE. JETTISON MECHANISM ENGINEERING AND TEST

INTERMEDIATE EXPERIMENTAL VEHICLE. JETTISON MECHANISM ENGINEERING AND TEST INTERMEDIATE EXPERIMENTAL VEHICLE. JETTISON MECHANISM ENGINEERING AND TEST L. Caldirola (1), B. Schmid (1) (1) RUAG Schweiz AG, RUAG Space, Schaffhauserstrasse 580, 8052 Zürich Email: luca.caldirola@ruag.com

More information

USA FALCON 1. Fax: (310) Telephone: (310) Fax: (310) Telephone: (310) Fax: (310)

USA FALCON 1. Fax: (310) Telephone: (310) Fax: (310) Telephone: (310) Fax: (310) 1. IDENTIFICATION 1.1 Name FALCON 1 1.2 Classification Family : FALCON Series : FALCON 1 Version : FALCON 1 Category : SPACE LAUNCH VEHICLE Class : Small Launch Vehicle (SLV) Type : Expendable Launch Vehicle

More information

Palamede, more than a microsatellite. Workshop on University Micro Satellites in Italy Rome, July 27, 2005

Palamede, more than a microsatellite. Workshop on University Micro Satellites in Italy Rome, July 27, 2005 Palamede, more than a microsatellite The Palamede Team (represented by Franco Bernelli and Roberto Armellin) Workshop on University Micro Satellites in Italy Rome, July 27, 2005 Outline Mission and educational

More information

PROJECT AQUILA 211 ENGINEERING DRIVE AUBURN, AL POST LAUNCH ASSESSMENT REVIEW

PROJECT AQUILA 211 ENGINEERING DRIVE AUBURN, AL POST LAUNCH ASSESSMENT REVIEW PROJECT AQUILA 211 ENGINEERING DRIVE AUBURN, AL 36849 POST LAUNCH ASSESSMENT REVIEW APRIL 29, 2016 Motor Specifications The team originally planned to use an Aerotech L-1520T motor and attempted four full

More information

FLIGHT TEST RESULTS AT TRANSONIC REGION ON SUPERSONIC EXPERIMENTAL AIRPLANE (NEXST-1)

FLIGHT 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

SABRE FOR HYPERSONIC & SPACE ACCESS PLATFORMS

SABRE FOR HYPERSONIC & SPACE ACCESS PLATFORMS SABRE FOR HYPERSONIC & SPACE ACCESS PLATFORMS Mark Thomas Chief Executive Officer 12 th Appleton Space Conference RAL Space, 1 st December 2016 1 Reaction Engines Limited REL s primary focus is developing

More information

H-IIA Launch Vehicle Upgrade Development

H-IIA Launch Vehicle Upgrade Development 26 H-IIA Launch Vehicle Upgrade Development - Upper Stage Enhancement to Extend the Lifetime of Satellites - MAYUKI NIITSU *1 MASAAKI YASUI *2 KOJI SHIMURA *3 JUN YABANA *4 YOSHICHIKA TANABE *5 KEITARO

More information

OPTIMAL MISSION ANALYSIS ACCOUNTING FOR ENGINE AGING AND EMISSIONS

OPTIMAL 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 information

1 Evaluation of Power Control System for Micro and Nano Satellites by Hardware-in-the-Loop Simulator

1 Evaluation of Power Control System for Micro and Nano Satellites by Hardware-in-the-Loop Simulator 1 Evaluation of Power Control System for Micro and Nano Satellites by Hardware-in-the-Loop Simulator Yuji Sakamoto, Toshinori Kuwahara, et al. Tohoku University, Japan 16 AUG 2012 Small Satellite Conference

More information

CRITICAL DESIGN REVIEW. University of South Florida Society of Aeronautics and Rocketry

CRITICAL DESIGN REVIEW. University of South Florida Society of Aeronautics and Rocketry CRITICAL DESIGN REVIEW University of South Florida Society of Aeronautics and Rocketry 2017-2018 AGENDA 1. Launch Vehicle 2. Recovery 3. Testing 4. Subscale Vehicle 5. Payload 6. Educational Outreach 7.

More information

Overview. Mission Overview Payload and Subsystems Rocket and Subsystems Management

Overview. 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 information

Annual Report Summary Green Regional Aircraft (GRA) The Green Regional Aircraft ITD

Annual Report Summary Green Regional Aircraft (GRA) The Green Regional Aircraft ITD Annual Report 2011 - Summary Green Regional Aircraft (GRA) The Green Regional Aircraft ITD Green Regional Aircraft ITD is organised so as to: 1. develop the most promising mainstream technologies regarding

More information

GIT LIT NASA STUDENT LAUNCH PRELIMINARY DESIGN REVIEW NOVEMBER 13TH, 2017

GIT 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 information

A PARAMETRIC STUDY OF THE DEPLOYABLE WING AIRPLANE FOR MARS EXPLORATION

A PARAMETRIC STUDY OF THE DEPLOYABLE WING AIRPLANE FOR MARS EXPLORATION A PARAMETRIC STUDY OF THE DEPLOYABLE WING AIRPLANE FOR MARS EXPLORATION Koji Fujita* * Department of Aerospace Engineering, Tohoku University, Sendai, Japan 6-6-, Aramaki-Aza-Aoba, Aoba-ku, Sendai, Miyagi

More information

Part II. HISTORICAL AND ENGINEERING ANALYSIS OF AIRSHIP PLAN-AND- DESIGN AND SERVICE DECISIONS

Part II. HISTORICAL AND ENGINEERING ANALYSIS OF AIRSHIP PLAN-AND- DESIGN AND SERVICE DECISIONS CONTENTS MONOGRAPHER S FOREWORD DEFENITIONS, SYMBOLS, ABBREVIATIONS, AND INDICES Part I. LAWS AND RULES OF AEROSTATIC FLIGHT PRINCIPLE Chapter 1. AIRCRAFT FLIGHT PRINCIPLE 1.1 Flight Principle Classification

More information

Martin J. L. Turner. Expedition Mars. Published in association with. Chichester, UK

Martin J. L. Turner. Expedition Mars. Published in association with. Chichester, UK Martin J. L. Turner Expedition Mars Springer Published in association with Praxis Publishing Chichester, UK Contents Preface Acknowledgements List of illustrations, colour plates and tables xi xv xvii

More information

Development of Low-thrust Thruster with World's Highest Performance Contributing to Life Extension of Artificial Satellites

Development of Low-thrust Thruster with World's Highest Performance Contributing to Life Extension of Artificial Satellites Development of Low-thrust Thruster with World's Highest Performance Contributing to Life Extension of Artificial Satellites 40 NOBUHIKO TANAKA *1 DAIJIRO SHIRAIWA *1 TAKAO KANEKO *2 KATSUMI FURUKAWA *3

More information

MINI-REIS A FAMILY OF MULTIFUNCTIONAL UNMANNED LIGHT JET AIRCRAFTS

MINI-REIS A FAMILY OF MULTIFUNCTIONAL UNMANNED LIGHT JET AIRCRAFTS National Aerospace University Kharkiv Aviation Institute KhAI Public Joint Stock Company "Kyiv Radio Plant" Inter-Industry Scientific & Research Institute of the Problems of Aircraft Flight Mode Physical

More information

Nacelle Chine Installation Based on Wind-Tunnel Test Using Efficient Global Optimization

Nacelle 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 information

FEDERAL SPACE AGENCY OF RUSSIAN FEDERATION LAVOCHKIN ASSOCIATION PROGRAM OF THE MOON EXPLORATION BY AUTOMATIC SPACE COMPLEXES

FEDERAL SPACE AGENCY OF RUSSIAN FEDERATION LAVOCHKIN ASSOCIATION PROGRAM OF THE MOON EXPLORATION BY AUTOMATIC SPACE COMPLEXES FEDERAL SPACE AGENCY OF RUSSIAN FEDERATION LAVOCHKIN ASSOCIATION PROGRAM OF THE MOON EXPLORATION BY AUTOMATIC SPACE COMPLEXES 2007 CONCEPT 1. The program foresees development of automatic space complexes

More information

Cable-Controlled Aeroshell Deceleration System

Cable-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 information

MASCOT Asteroid Lander with innovative Mobility Mechanism

MASCOT Asteroid Lander with innovative Mobility Mechanism www.dlr.de Slide 1 MASCOT Asteroid Lander with innovative Mobility Mechanism Dr. Josef Reill German Aerospace Center - DLR Institute of Robotics and Mechatronics Team-Members: Josef Reill Hans-Jürgen Sedlmayr

More information

Design Rules and Issues with Respect to Rocket Based Combined Cycles

Design Rules and Issues with Respect to Rocket Based Combined Cycles Respect to Rocket Based Combined Cycles Tetsuo HIRAIWA hiraiwa.tetsuo@jaxa.jp ABSTRACT JAXA Kakuda space center has been studying rocket based combined cycle engine for the future space transportation

More information

Y. 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 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 information

Development of Internationally Competitive Solid Rocket Booster for H3 Launch Vehicle

Development 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 information

Wind Tunnel Measurement Of Aerodynamic Characteristics Of A Generic Eurocopter Helicopter

Wind 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 information

An 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. 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 information

Study of Flexible Wheels for Lunar Exploration Rovers: Running Performance of Flexible Wheels with Various Amount of Deflection

Study of Flexible Wheels for Lunar Exploration Rovers: Running Performance of Flexible Wheels with Various Amount of Deflection Journal of Asian Electric Vehicles, Volume 7, Number 2, December 2009 Study of Flexible Wheels for Lunar Exploration Rovers: Running Performance of Flexible Wheels with Various Amount of Deflection Koiro

More information

Welcome to Aerospace Engineering

Welcome to Aerospace Engineering Welcome to Aerospace Engineering DESIGN-CENTERED INTRODUCTION TO AEROSPACE ENGINEERING Notes 5 Topics 1. Course Organization 2. Today's Dreams in Various Speed Ranges 3. Designing a Flight Vehicle: Route

More information

Super Squadron technical paper for. International Aerial Robotics Competition Team Reconnaissance. C. Aasish (M.

Super Squadron technical paper for. International Aerial Robotics Competition Team Reconnaissance. C. Aasish (M. Super Squadron technical paper for International Aerial Robotics Competition 2017 Team Reconnaissance C. Aasish (M.Tech Avionics) S. Jayadeep (B.Tech Avionics) N. Gowri (B.Tech Aerospace) ABSTRACT The

More information

NEXT Exploration Science and Technology Mission. Relevance for Lunar Exploration

NEXT Exploration Science and Technology Mission. Relevance for Lunar Exploration NEXT Exploration Science and Technology Mission Relevance for Lunar Exploration Alain Pradier & the NEXT mission team ILEWG Meeting, 23 rd September 2007, Sorrento AURORA PROGRAMME Ministerial Council

More information

17/11/2016. 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 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 information

THE SIMULATION OF ONE SIDE OF TETRAHEDRON AIRBAGS IMPACT ATTENUATION SYSTEM

THE 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 information

Architecture Options for Propellant Resupply of Lunar Exploration Elements

Architecture Options for Propellant Resupply of Lunar Exploration Elements Architecture Options for Propellant Resupply of Lunar Exploration Elements James J. Young *, Robert W. Thompson *, and Alan W. Wilhite Space Systems Design Lab School of Aerospace Engineering Georgia Institute

More information

Cable Dragging Horizontal Takeoff Spacecraft Air Launch System

Cable 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 information

Multifunction Rocket System Development based on Advanced Hybrid Propulsion

Multifunction 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 information

Turbo-Rocket. A brand new class of hybrid rocket. Rene Nardi and Eduardo Mautone

Turbo-Rocket. A brand new class of hybrid rocket. Rene Nardi and Eduardo Mautone Turbo-Rocket R A brand new class of hybrid rocket Rene Nardi and Eduardo Mautone 53 rd AIAA/SAE/ASEE Joint Propulsion Conference July 10 12, 2017 - Atlanta, Georgia Rumo ao Espaço R - UFC Team 2 Background

More information

MARS-OZ: A Design for a Simulated Mars Base in the Arkaroola Region

MARS-OZ: A Design for a Simulated Mars Base in the Arkaroola Region MARS-OZ: A Design for a Simulated Mars Base in the Arkaroola Region David Willson (david.willson@au.tenovagroup.com) and Jonathan D. A. Clarke (jon.clarke@bigpond.com), Mars Society Australia The centrepiece

More information

Powertrain and Chassis Hardware-in-the- Loop (HIL) Simulation of Ford s Autonomous Vehicle Platform

Powertrain and Chassis Hardware-in-the- Loop (HIL) Simulation of Ford s Autonomous Vehicle Platform Powertrain and Chassis Hardware-in-the- Loop (HIL) Simulation of Ford s Autonomous Vehicle Platform Adit Joshi Research Engineer Automated Driving HIL Simulation Ford Motor Company 1 OUTLINE Autonomous

More information

On the feasibility of a fast track return to Mars

On 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 information

Abstract #1756. English. French. Author(s) and Co Author(s) ispace & Team Hakuto s 2017 Lunar Mission

Abstract #1756. English. French. Author(s) and Co Author(s) ispace & Team Hakuto s 2017 Lunar Mission 4/25/2017 CIM TPMS Abstract #1756 English ispace & Team Hakuto s 2017 Lunar Mission This presentation will introduce ispace, a lunar exploration company headquartered in Tokyo, Japan, and Team Hakuto,

More information

Mathematical Model of Electric Vehicle Power Consumption for Traveling and Air-Conditioning

Mathematical Model of Electric Vehicle Power Consumption for Traveling and Air-Conditioning Journal of Energy and Power Engineering 9 (215) 269-275 doi: 1.17265/1934-8975/215.3.6 D DAVID PUBLISHING Mathematical Model of Electric Vehicle Power Consumption for Traveling and Air-Conditioning Seishiro

More information

CONTENTS Duct Jet Propulsion / Rocket Propulsion / Applications of Rocket Propulsion / 15 References / 25

CONTENTS 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 information

Suitability of reusability for a Lunar re-supply system

Suitability of reusability for a Lunar re-supply system www.dlr.de Chart 1 Suitability of reusability for a Lunar re-supply system Etienne Dumont Space Launcher Systems Analysis (SART) Institut of Space Systems, Bremen, Germany Etienne.dumont@dlr.de IAC 2016

More information

Modeling, Structural & CFD Analysis and Optimization of UAV

Modeling, 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 information