Venus Entry Options Venus Upper Atmosphere Investigations Science and Technical Interchange Meeting (STIM)
|
|
- Brent Scott
- 6 years ago
- Views:
Transcription
1 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 Venkatapathy 1
2 Characteristics of the Entry Problem Entry velocity Driven by interplanetary trajectory Entry angle Must be high enough to avoid skip-out Affects latitude that can be reached Ballistic coefficient Design choice, constrained by packaging Heating rate Constrains material selection Heat load Drives thermal protection thickness Deceleration Drives payload structural requirements ADEPT/NASA Distribution Only 2
3 TPS Mass Scales with Heat Load From Laub and Venkatapathy September 14, 2012 ADEPT/NASA Distribution Only 3
4 Entry Environments for Previous Missions b = 600 Venera 4, 5, 6 Venera/Vega P-V Large Probe September 14, 2012 ADEPT/NASA Distribution Only 4
5 Entry Performance Entry Vehicle Class Ballistic Coefficient Entry Angle Peak deceleration (g s) Peak heat flux (kw/cm2) Total heat load (kj/cm2) Venera >23 Vega Pioneer Large TPS mass fraction (%) ADEPT ~12 (estimated) All cases assume V=11.2 km/s Cases are representative, not matching actual mission conditions September 14, 2012 ADEPT/NASA Distribution Only 5
6 Altitude (km) Venus Entry: Time to Mach ADEPT Pioneer Large Vega Venera Time (s) ADEPT/NASA Distribution Only 6
7 Adaptive Deployable Entry and Placement Technology ADEPT-VITaL Key Facts Launch Vehicle Atlas V 551 Launch Date 29 May 2023 Entry Date 29 September 2024 Entry Flight Path Angle -8.25º Atlas V 551 Launch ADEPT remains stowed during Interplanetary cruise; Deployment at Venus Entry Velocity 10.8 km/s Entry Azimuth Angle 171.0º Peak G-load (nominal) Peak G-load (3s) 30 G 46 G Ballistic Entry (unguided) 6-m Diameter 70º Cone Subsonic parachute for ADEPT separation and VITaL Lander release Landing in Alpha region Alpha Landing Ellipse Estimated 600 km x 600 km 3s landing location uncertainty ellipse based on 2000 case POSTII Monte Carlo with uncertainties in: Entry Position, Entry FPA, Entry Velocity, Drag Coefficient, Density, Wind May 15, 2012 ADEPT/CA250/NASA Distribution Only 7
8 Altitude (km) Any benefit from lifting entry? L/D=0.2 L/D=0 Targeting accuracy Cross range Time Ballistic Coefficient Entry Angle Peak deceleration (g s) Peak heat flux (kw/cm2) Total heat load (kj/cm2) ADEPT Ballistic ADEPT L/D= September 14, 2012 ADEPT/NASA Distribution Only 8
9 Deployment Environment: Venus and Mars UAV design experience from Mars may be relevant for Venus September 14, 2012 ADEPT/NASA Distribution Only 9
10 Summary Vega provides existence proof for entry capability for balloons Requires Carbon Phenolic or equivalent More mass efficient solutions are available Pioneer Venus has similar altitude for M=1 More mass efficient, higher peak deceleration ADEPT decelerates higher, with much lower peak deceleration Opportunity for unfolding UAVs Technology development is in progress Lifting entry adds complexity without obvious benefit September 14, 2012 ADEPT/NASA Distribution Only 10
11 BACKUP September 14, 2012 ADEPT/NASA Distribution Only 11
12 Engineering Challenges for High-Speed Atmospheric Entry Venus Example For rigid aeroshell Size constrained by launch shroud Entry mass constrained by launch vehicle throw capability Ballistic coefficient ~ 250 kg/m 2 Need material that can sustain 2000 W/cm2 Only Carbon Phenolic is available 9/14/
13 Engineering Challenges for High-Speed Atmospheric Entry Venus Example For rigid aeroshell Size constrained by launch shroud Entry mass constrained by launch vehicle throw capability Ballistic coefficient ~ 250 kg/m 2 For a given material, operating near its heating rate capability reduces heat load, which reduces TPS mass 9/14/
14 Engineering Challenges for High-Speed Atmospheric Entry Venus Example For rigid aeroshell Size constrained by launch shroud Entry mass constrained by launch vehicle throw capability Ballistic coefficient ~ 250 kg/m 2 Select entry angle with favorable balance of heat rate and heat load Accept high deceleration (250 g) Certify for this load environment 9/14/
15 Opportunity for High-Speed Atmospheric Entry Venus Example Operate at a lower ballistic coefficient Develop a lower-density material that can sustain 2000 W/cm2 9/14/
16 Opportunity for High-Speed Atmospheric Entry Venus Example Assume ballistic coefficient can be lowered 10 x A material that can sustain 200 W/cm2 is now feasible Peak deceleration reduced by an order of magnitude 9/14/
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 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 informationDeployment 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 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 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 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 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 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 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 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 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 informationDESIGN OF AN ENTRY SYSTEM FOR CARGO DELIVERY TO MARS
DESIGN OF AN ENTRY SYSTEM FOR CARGO DELIVERY TO MARS Robert Thompson, Larry Cliatt, Chris Gruber, Bradley Steinfeldt (1) Tommy Sebastian, Jamie Wilson (2) (1) Georgia Institute of Technology, 270 Ferst
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 informationTurbo-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 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 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 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 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 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 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 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 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 informationMartin 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 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 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 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 informationVehicle Reusability. e concept e promise e price When does it make sense? MARYLAND U N I V E R S I T Y O F. Vehicle Reusability
e concept e promise e price When does it make sense? 2010 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu 1 Sir Arthur C. Clarke: We re moving from the beer can philosophy of space travel
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 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 informationA 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 informationSystems Analysis Branch, NASA Ames Research Center, Moffett Field, CA Neerim Corporation, 2551 Casey Ave. Ste. B, Mountain View, CA 94086
PERFORMANCE CHARACTERIZATION, SENSITIVITY AND COMPARISON OF A DUAL LAYER THERMAL PROTECTION SYSTEM Cole D. Kazemba (1), Mary Kathleen McGuire (2), Austin Howard (3), Ian G. Clark (4), Robert D. Braun (5)
More informationENERGIA 1. IDENTIFICATION. 1.1 Name. 1.2 Classification Family : K Series : K-1/SL-17 Version : 4 strap-ons
1. IDENTIFICATION 1.1 Name 1.2 Classification Family : K Series : K-1/SL-17 Version : 4 strap-ons Category : SPACE LAUNCH VEHICLE Class : Heavy Lift Vehicles (HLV) Type : Expendable Launch Vehicle (ELV)
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 informationTravel: Detailed Flight Plan
DarkSide Logistics Lunar Spaceport Initiative Travel: Detailed Flight Plan The payload will be launched from Cape Canaveral Air Force Station Launch Complex 46 at 15:59:35 ET on January 25, 2010, using
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 informationApproche novatrice pour la conception et l exploitation d avions écologiques, sous incertitudes.
Sylvain Prigent Approche novatrice pour la conception et l exploitation d avions écologiques, sous incertitudes. Challenges Air traffic will double in the next 20 years! *Revenue passenger kilometers (number
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 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 informationAirships: A New Horizon for Science April 30 May 3, Worldwide Aeros Corp. Montebello, California. Presented by:
Airships: A New Horizon for Science April 30 May 3, 2013 Worldwide Aeros Corp. Montebello, California Presented by: Mr. Fred Edworthy V.P. Business Development www.aeroscraft.com 1 25 YEARS INNOVATION,
More informationMars 2018 Mission Status and Sample Acquisition Issues
Mars 2018 Mission Status and Sample Acquisition Issues Presentation to the Planetary Protection Subcommittee Charles Whetsel Manager, Advanced Studies and Program Architecture Office Christopher G. Salvo
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 informationRocket Design. Tripoli Minnesota Gary Stroick. February 2010
Rocket Design Tripoli Minnesota Gary Stroick February 2010 Purpose Focus is on designing aerodynamically stable rockets not drag optimization nor construction techniques! Copyright 2010 by Gary Stroick
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 informationNEXT 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 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 informationINTERMEDIATE 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 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 informationPresentation Outline. # Title # Title
CDR Presentation 1 Presentation Outline # Title # Title 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 Team Introduction Vehicle Overview Vehicle Dimensions Upper Body Section Payload
More informationSolar Based Propulsion System UAV Conceptual Design ( * )
Solar Based Propulsion System UAV Conceptual Design ( * ) Avi Ayele*, Ohad Gur, and Aviv Rosen* *Technion Israel Institute of Technology IAI Israel Aerospace Industries (*) Ayele A., Gur O., Rosen A.,
More informationAF Hypersonic Vision
AF Hypersonic Vision Airbreathing hypersonic platform technologies to produce revolutionary warfighting capabilities Goal: S&T efforts to develop and mature robust, comprehensive technology options for:
More informationArchitecture 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 informationHeavy Payload Tethered Hexaroters for Agricultural Applications: Power Supply Design
Heavy Payload Tethered Hexaroters for Agricultural Applications: Power Supply Design Wasantha 1, Guangwei Wang 2 and Shiqin Wang 3* 1,2,3 Center for Agricultural Resources Research, Institute of Genetics
More informationFEDERAL 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 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 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 informationCRITICAL 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 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 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 informationAppenidix E: Freewing MAE UAV analysis
Appenidix E: Freewing MAE UAV analysis The vehicle summary is presented in the form of plots and descriptive text. Two alternative mission altitudes were analyzed and both meet the desired mission duration.
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 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 informationElectric Flight Potential and Limitations
Electric Flight Potential and Limitations Energy Efficient Aircraft Configurations, Technologies and Concepts of Operation, Sao José dos Campos, 19 21 November 2013 Dr. Martin Hepperle DLR Institute of
More informationAres V: Supporting Space Exploration from LEO to Beyond
Ares V: Supporting Space Exploration from LEO to Beyond American Astronautical Society Wernher von Braun Memorial Symposium October 21, 2008 Phil Sumrall Advanced Planning Manager Ares Projects Office
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 informationPhoenix Lander Implications on in situ resource utilization for robotic exploration of Mars
Phoenix Landing Site May 2008 Phoenix Lander Implications on in situ resource utilization for robotic exploration of Mars LEAG-ICEUM-SRR (2008) Cape Canaveral, FL Robert L. Ash October 29, 2008 Aerospace
More informationSMILE - Small Innovative Launcher for Europe
SMILE - Small Innovative Launcher for Europe Bertil Oving, Netherlands Aerospace Centre (NLR) ESA Microlauncher Workshop, 09.05.2017, 1 Demand source: SpaceWorks Enterprises Inc (SEI) ESA Microlauncher
More informationMartian In Situ Investigations
Mars MetNet Mission and Payload Precursors Martian In Situ Investigations Saariselkä, 30.3.2017 EuroPlanet Workshop Dr. Ari-Matti Harri Finnish Meteorological Institute Finnish Meteorological Institute,
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 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 informationSuitability 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 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 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 informationCHAPTER 3 DESIGN OF THE LIMITED ANGLE BRUSHLESS TORQUE MOTOR
33 CHAPTER 3 DESIGN OF THE LIMITED ANGLE BRUSHLESS TORQUE MOTOR 3.1 INTRODUCTION This chapter presents the design of frameless Limited Angle Brushless Torque motor. The armature is wound with toroidal
More informationMARS-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 informationDevelopment of balloon-borne CO 2 sonde and test flight observations
Development of balloon-borne CO 2 sonde and test flight observations 1 Y. Matsumi, M. Ouchi, T. Nakayama Solar Terrestrial Environment Laboratory, Nagoya University, Japan K. Shimizu, K. Shibata Meisei
More informationCanisterized Satellite Dispenser (CSD) As A Standard For Integrating and Dispensing Hosted Payloads on Large Spacecraft and Launch Vehicles
Canisterized Satellite Dispenser (CSD) As A Standard For Integrating and Dispensing Hosted Payloads on Large Spacecraft and Launch Vehicles Ryan Hevner, Ryan Williams and (Presented by) Walter Holemans
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 informationChapter 4 Lecture 16. Engine characteristics 4. Topics. Chapter IV
Chapter 4 Lecture 16 Engine characteristics 4 Topics 4.3.3 Characteristics of a typical turboprop engine 4.3.4 Characteristics of a typical turbofan engine 4.3.5 Characteristics of a typical turbojet engines
More informationSmall UAV A French MoD perspective and planning
Small UAV A French MoD perspective and planning French ISTAR segmentation portable transportable infrastructure System volume Tactical Small UAV Contact Combat Helicopters (MTI) Fighter Aircrafts Land
More informationWelcome 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 informationLUNAR INDUSTRIAL RESEARCH BASE. Yuzhnoye SDO proprietary
LUNAR INDUSTRIAL RESEARCH BASE DESCRIPTION Lunar Industrial Research Base is one of global, expensive, scientific and labor intensive projects which is to be implemented by the humanity to meet the needs
More informationMASCOT 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 informationASABOOSTER CD005 Conceptual Design Study for an Asaspace Launch Capability Version 0.04
ASABOOSTER CD005 Conceptual Design Study for an Asaspace Launch Capability Version 0.04 by Ed LeBouthillier 1 of 26 Forward In a previous conceptual design study, Asabooster CD004, I examined a vertical
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 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 informationblended wing body aircraft for the
Feasibility study of a nuclear powered blended wing body aircraft for the Cruiser/Feeder eede concept cept G. La Rocca - TU Delft 11 th European Workshop on M. Li - TU Delft Aircraft Design Education Linköping,
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 informationView Numbers and Units
To demonstrate the usefulness of the Working Model 2-D program, sample problem 16.1was used to determine the forces and accelerations of rigid bodies in plane motion. In this problem a cargo van with a
More informationMULTIDISCIPLINARY 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 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 information7. PRELIMINARY DESIGN OF A SINGLE AISLE MEDIUM RANGE AIRCRAFT
7. PRELIMINARY DESIGN OF A SINGLE AISLE MEDIUM RANGE AIRCRAFT Students: R.M. Bosma, T. Desmet, I.D. Dountchev, S. Halim, M. Janssen, A.G. Nammensma, M.F.A.L.M. Rommens, P.J.W. Saat, G. van der Wolf Project
More informationIronless Core DC Motors for Aerospace
Ironless Core DC Motors for Aerospace Market segments covered by AS/EN9100 Support equipment Space shuttle & re entry vehicles Aviation Commercial passenger aircraft Light aircraft Cabin equipment Science
More informationHovercraft
1 Hovercraft 2017-2018 Names: Score: / 44 Show all equations and work. Point values are shown in parentheses at the end of the question. Assume g=9.8 m/s/s for all calculations. Include units in your answer.
More informationHPR Staging & Air Starting By Gary Stroick
Complex Rocket Design Considerations HPR Staging & Air Starting By Gary Stroick 1. Tripoli Safety Code 2. Technical Considerations 3. Clusters/Air Starts 4. Staging 5. Summary 2 1. Complex High Power Rocket.
More informationShu Ting Goh, Research Fellow, ECE, NUS S. A. (Reza) Zekavat, Professor, ECE, MTU (Visiting Prof. WPI)
Shu Ting Goh, Research Fellow, ECE, NUS S. A. (Reza) Zekavat, Professor, ECE, MTU (Visiting Prof. WPI) 1 2 } Aviation challenges: Lower CO2 emissions Lower engine noise } Two solutions: 1. More electric
More informationPropulsion Controls and Diagnostics Research at NASA GRC Status Report
Propulsion Controls and Diagnostics Research at NASA GRC Status Report Dr. Sanjay Garg Branch Chief Ph: (216) 433-2685 FAX: (216) 433-8990 email: sanjay.garg@nasa.gov http://www.lerc.nasa.gov/www/cdtb
More informationThe Sonic Cruiser A Concept Analysis
International Symposium "Aviation Technologies of the XXI Century: New Aircraft Concepts and Flight Simulation", 7-8 May 2002 Aviation Salon ILA-2002, Berlin The Sonic Cruiser A Concept Analysis Dr. Martin
More information