Design and construction a flying wing unmanned aerial vehicles

Size: px
Start display at page:

Download "Design and construction a flying wing unmanned aerial vehicles"

Transcription

1 Design and construction a flying wing unmanned aerial vehicles Vasile Prisacariu 1, Mircea Boscoianu 2 SUMMARY: Unmanned aerial vehicles (UAV) are starting to represent a larger importance in the aerospace sphere due to the fact that it can execute a wide range of missions. The ampleness of its development in the last years is due to its possibility to be also used in civil applications. The development of optic-electronics, nanotechnology and the use of smart materials make UAV projects innovative. In this paper we propose to approach a systematic scheme of a UAV concept with a presentation in steps of how we can realize a UAV type flying wing. Keywords: UAV, first person visual (FPV), flying wing Chapter 1 Introduction Unmanned aerial vehicles (UAV) are starting to represent a greater importance in the aerospace sphere. The development of optic-electronics, nanotechnology and the use of smart materials make UAV projects innovative. In the last years they have tried building smaller aerial vehicles dedicated for special missions. The flight widgets must transport sensors which will transmit information from interest zone (video, acoustic, chemical and biological); these widgets are called micro aerial vehicles. They became topicality due to the progress in miniaturization and use of unconventional materials. Aerial vectors must be capable to have sensors that transmit information from interest zones (video, acoustic, chemical and biological). Figure 1 Onboard sensor (video, acoustic, chemical and biological). The succession rate of mission depends on a series of factor like: meteorological conditions and operation restrictions; the performance of the sensors; the training level of the operators; the equipment level; the interoperability level with the other structures involved in the mission. 1 Vasile Prisacariu, Ph.D. student, Transilvania University, Colina Universităţii 1, Braşov, Romania, aerosavelli73@yahoo.com 2 Mircea Boşcoianu, Prof. Ph.D. Faculty of Aeronautical Management, Henri Coandă Air Force Academy Mihai Viteazu 160 Braşov, Romania, boscoianu.mircea@yahoo.com 1

2 In other words the succession rate of the mission is directly influenced by the aerial vector capabilities, the most important being: the vectors reliability, the correlation speeds with the stages of the mission, minimal print (radar, acoustic, and thermo). The main types of aerial vectors type flying wing are represented in table 1. Table 1. The aerial vectors type flying wing Micro UAS Mini UAS Close Range Black Wodow, USA Orbiter, USA Maxi 10, Franţa Short range Medium range Low altitude, long endurance Exodrone, USA Snowgoose, Canada Eaglescan, USA Lethal UAS Unmanned combat aircraft Cutlass, USA-Israel Corax, UK Chapter 2 The design and manufacturing a UAV type flying wing Design management The realization of an unmanned aerial vector must take in consideration a series of limits and requests for the aerial machines: geometry, aerodynamics, propulsion, technology and exploitation. These determine the characteristics and performance of the aerial product. 2

3 Fig.2 Design diagram The characteristics and performance of the aerial vector (geometry, aerodynamics, machines and propulsion) are defined after a series of laboratory tests (aerodynamic tunnels) in real situations (flight attempts). The proposition of a constructive solution The technical solution proposed by a flying wing (figure 3) can be found as a class of mini UAV, with a total weight of 1.6kg. The proposed concept has the purpose of fulfilling data acquiring missions (image and weather) out of the visual range of the unmanned aerial system operator. Fig. 3 The flying wing The proposed constructive configuration is flying wing (tailless) tricycle landing gear, the vector being equipped with the following systems: propulsion system (electric motor), flight control system, electric system, data acquiring system and flight parameters (video, FPV sensors-height, speed, altitude, GPS), terrestrial equipment (visual data, maintenance and transport) Platform structure (airframe) Wing. The wing type is mono-strut (hard aluminum) composed of expanded polystyrene with extreme ribs from plywood (figure 3). It is composed of 2 semi-plans that are mounted on the central fuselage with a dihedral angel of 0. The main characteristics are pointed out in table 2. The aerodynamic profile picked by HS 522, for a easier manufacturing of the wing. The profile (figure 4) has the features as in table 3 and the polar as in figure 6 and 7, calculated using Profili software v

4 Table 2.Wing characteristics Span (m) 2 Aspect ratio 6.96 Root chord (m) 0,4 Wight (g) 1800 Surface (m 2 ) 0,575 Wing load (kg/m 2 ) 1,730 Fig. 5 HS 522 airfoil Fig. 6 cl-alfa, cd-alfa Fig. 7 Cl/cd-alfa, cm-alfa Tabelul 3. HS 522 aifoil data The aero mechanic analysis of the flying wing is performed with the help of the XFLR5 v.6.06 software. According to figure 8 the wing develops portance marks, resistance for going forward and induced resistance using the VLM method (vortex lattice method), at 15 m/s and o incidence angel of 10 degrees. 4

5 Fig 8 Amprenta portanţei şi rezistenţei la înaintare 2.2. Board systems The propulsion systems are composed of a brushless electric motor equipped with a electronic regulator of 40A which can train a 12x6 bipal propeller (figure 9a). The flight control system is composed of: radio-control system necessary for flying the aerial vector at distance and composed of transmitter, receiver, four servo-mechanisms and a auto stabilization method on 3 axis (figure 9b). Data acquisition system (sensors) is composed of digital videocamera, temperature recorder/ ambient moisture. The electricity is assured by a LiPo 4000 ma accumulator with reduced weight. a b c Fig. 9 Onboard equipment (a. electric propulsion, b. radio control system, c battery ) 3. Performances and features Mass features and performances resulted from the banc tests and flight attempts are detailed according to table 4 and 5. The results are obtained following the compromise between the aerodynamic concept and the utility of the aerial vector. Table 4 Mass repartition Airframe weight (empty) Engine weight Equipments Total weight 1 kg 0,3 kg 0,5 kg 1,8 kg Table 5 Performances and features of the aerial vector Span Minimum /Maximum speed 2000 mm 42 / 90 km/h 5

6 Maximum ceiling Range Autonomy 2500 m 5 km 20 min Conclusions The vector in his current state is easy to be piloted and does not have extreme problems with the exploitation. The auto stabile behavior of the aerial vector was obtained due to the auto stabilization method used. The performance of the aerial systems can affect directly the quality of the mission with major influences regarding the acquisition capacity, dissemination and decision regarding data from interest zones. The global performances of an aerial vehicle directly depend on the boarded aerodynamic concept, board equipment, the exploitation method used by the human user which is on the ground and last but not least the weather conditions. Acknowledgment The authors wish to thank the Transilvania University of Braşov and "Henri Coandă" Air Force Academy of Braşov for supporting the research necessary for writing this article. References 1 UAS Yearbook, Unmanned aircraft systems The Global Perspective 2011/2012, Blyenburg & Co, june 2011, Paris, ISSN , p 216, URL:< [cit ] 2 URL:< ] 3 URL:< [cit ] 4 Guidelines for XFLR5 v6.03, 2011, 71p., URL:< [cit ] 5 URL:< [cit ] 6 SANDRU, V., RADULESCU,, M., CIUFUDEAN, C., BOSCOIANU, E.C. Critical aspects regarding the integration of a low cost up-grade architecture in hightechnology assets for defense, in Advances in Applied Mathematics, Montreux, Dec GUNDLACH J., Designing unmanned aircraft systems, Virginia, USA, AIAA series, 2012, 805 p. 6

ASPECTS REGARDING THE ELECTRIC PROPULSION OF THE UAV MULTICOPTER

ASPECTS REGARDING THE ELECTRIC PROPULSION OF THE UAV MULTICOPTER Review of the Air Force Academy No.3 (35)/2017 ASPECTS REGARDING THE ELECTRIC PROPULSION OF THE UAV MULTICOPTER Vasile PRISACARIU *, Bogdan HERCIU *, Andrei LUCHIAN ** * Henri Coandă Air Force Academy

More information

CFD ANALYSIS FOR UAV OF FLYING WING

CFD ANALYSIS FOR UAV OF FLYING WING SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE-AFASES 2016 CFD ANALYSIS FOR UAV OF FLYING WING Dumitru PEPELEA, Marius Gabriel COJOCARU, Adrian TOADER, Mihai Leonida NICULESCU National Aerospace Research,

More information

Jay Gundlach AIAA EDUCATION SERIES. Manassas, Virginia. Joseph A. Schetz, Editor-in-Chief. Blacksburg, Virginia. Aurora Flight Sciences

Jay Gundlach AIAA EDUCATION SERIES. Manassas, Virginia. Joseph A. Schetz, Editor-in-Chief. Blacksburg, Virginia. Aurora Flight Sciences Jay Gundlach Aurora Flight Sciences Manassas, Virginia AIAA EDUCATION SERIES Joseph A. Schetz, Editor-in-Chief Virginia Polytechnic Institute and State University Blacksburg, Virginia Published by the

More information

DSSI UAV. Unmanned Aerial Vehicle. Research & Development Project

DSSI UAV. Unmanned Aerial Vehicle. Research & Development Project UAV Unmanned Aerial Vehicle HISTORY AND SKILLS of Small UAV with electrically powered propeller Description of the solution: Airframe,electronics, 2 battery sets 1 spare Airframe, battery charger Transport

More information

Electric VTOL Aircraft

Electric VTOL Aircraft Electric VTOL Aircraft Subscale Prototyping Overview Francesco Giannini fgiannini@aurora.aero 1 08 June 8 th, 2017 Contents Intro to Aurora Motivation & approach for the full-scale vehicle Technical challenges

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

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

UNCLASSIFIED FY 2017 OCO. FY 2017 Base

UNCLASSIFIED FY 2017 OCO. FY 2017 Base Exhibit R-2, RDT&E Budget Item Justification: PB 2017 Air Force Date: February 2016 3600: Research, Development, Test & Evaluation, Air Force / BA 2: Applied Research COST ($ in Millions) Prior Years FY

More information

1.1 REMOTELY PILOTED AIRCRAFTS

1.1 REMOTELY PILOTED AIRCRAFTS CHAPTER 1 1.1 REMOTELY PILOTED AIRCRAFTS Remotely Piloted aircrafts or RC Aircrafts are small model radiocontrolled airplanes that fly using electric motor, gas powered IC engines or small model jet engines.

More information

Development of a Variable Stability, Modular UAV Airframe for Local Research Purposes

Development of a Variable Stability, Modular UAV Airframe for Local Research Purposes Development of a Variable Stability, Modular UAV Airframe for Local Research Purposes John Monk Principal Engineer CSIR, South Africa 28 October 2008 Outline A Brief History of UAV Developments at the

More information

Preliminary Design of a LSA Aircraft Using Wind Tunnel Tests

Preliminary Design of a LSA Aircraft Using Wind Tunnel Tests Preliminary Design of a LSA Aircraft Using Wind Tunnel Tests Norbert ANGI*,1, Angel HUMINIC 1 *Corresponding author 1 Aerodynamics Laboratory, Transilvania University of Brasov, 29 Bulevardul Eroilor,

More 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

DEVELOPMENT OF A MORPHING FLYING PLATFORM FOR ADAPTIVE CONTROL SYSTEM STUDY

DEVELOPMENT OF A MORPHING FLYING PLATFORM FOR ADAPTIVE CONTROL SYSTEM STUDY 27 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES DEVELOPMENT OF A MORPHING FLYING PLATFORM FOR ADAPTIVE CONTROL SYSTEM STUDY Taufiq Mulyanto, M. Luthfi I. Nurhakim, Rianto A. Sasongko Faculty

More information

DESIGN AND DEVELOPMENT OF A MICRO AIR VEHICLE (µav) CONCEPT: PROJECT BIDULE

DESIGN AND DEVELOPMENT OF A MICRO AIR VEHICLE (µav) CONCEPT: PROJECT BIDULE DESIGN AND DEVELOPMENT OF A MICRO AIR VEHIE (µav) CONCEPT: PROJECT BIDULE Mr T. Spoerry, Dr K.C. Wong School of Aerospace, Mechanical and Mechatronic Engineering University of Sydney NSW 6 Abstract This

More information

In 2003, A-Level Aerosystems (ZALA AERO) was founded by current company President Alexander Zakharov, since then he has led

In 2003, A-Level Aerosystems (ZALA AERO) was founded by current company President Alexander Zakharov, since then he has led A-Level Aerosystems In 2003, A-Level Aerosystems (ZALA AERO) was founded by current company President Alexander Zakharov, since then he has led the company to be a leader in the micro UAV market in Russian

More information

Unmanned Air Vehicles (UAVs): Classification, Legislation and Future applications Presenter: Dr-Ing Dimitrios E. Mazarakos

Unmanned Air Vehicles (UAVs): Classification, Legislation and Future applications Presenter: Dr-Ing Dimitrios E. Mazarakos Unmanned Air Vehicles (UAVs): Classification, Legislation and Future applications Presenter: Dr-Ing Dimitrios E. Mazarakos The presenter Dr-Ing Dimitrios E. Mazarakos Dipl. in Mechanical Engineering and

More information

DRONE & UAV.

DRONE & UAV. www.erapkorea.co.kr DRONE & UAV Extended flight time Proven to be reliable, safe and easy to use Various fields of operation Completely autonomous, and manually controlled ERAP DRONE & UAV WHY ERAP s MAPPING

More information

SURVEYOR-H. Technical Data. Max speed 120 km/h. Engine power 7.2 hp. Powerplant Modified Zenoah G29E. Fuel tank volume 3.6 l

SURVEYOR-H. Technical Data. Max speed 120 km/h. Engine power 7.2 hp. Powerplant Modified Zenoah G29E. Fuel tank volume 3.6 l rev. 28.10.14 * features & specifications are subject to change without notice. Technical Data Max speed 120 km/h Engine power 7.2 hp Powerplant Modified Zenoah G29E Fuel tank volume 3.6 l Payload with

More information

CONCEPTUAL DESIGN OF ECOLOGICAL AIRCRAFT FOR COMMUTER AIR TRANSPORTATION

CONCEPTUAL DESIGN OF ECOLOGICAL AIRCRAFT FOR COMMUTER AIR TRANSPORTATION 26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES CONCEPTUAL DESIGN OF ECOLOGICAL AIRCRAFT FOR COMMUTER AIR TRANSPORTATION Yasuhiro TANI, Tomoe YAYAMA, Jun-Ichiro HASHIMOTO and Shigeru ASO Department

More information

FABRICATION OF CONVENTIONAL CYLINDRICAL SHAPED & AEROFOIL SHAPED FUSELAGE UAV MODELS AND INVESTIGATION OF AERODY-

FABRICATION OF CONVENTIONAL CYLINDRICAL SHAPED & AEROFOIL SHAPED FUSELAGE UAV MODELS AND INVESTIGATION OF AERODY- ISSN 232-9135 28 International Journal of Advance Research, IJOAR.org Volume 1, Issue 3, March 213, Online: ISSN 232-9135 FABRICATION OF CONVENTIONAL CYLINDRICAL SHAPED & AEROFOIL SHAPED FUSELAGE UAV MODELS

More information

INSTYTUT TECHNICZNY WOJSK LOTNICZYCH Air Force Institute of Technology

INSTYTUT TECHNICZNY WOJSK LOTNICZYCH Air Force Institute of Technology 1953-2014 INSTYTUT TECHNICZNY WOJSK LOTNICZYCH Air Force Institute of Technology 01 Aircraft Engines Division Airworthiness Division IT Logistics Support Systems Division Aeroplanes & Helicopters Division

More information

VAST AUAV (Variable AirSpeed Telescoping Additive Unmanned Air Vehicle)

VAST AUAV (Variable AirSpeed Telescoping Additive Unmanned Air Vehicle) VAST AUAV (Variable AirSpeed Telescoping Additive Unmanned Air Vehicle) Michael Stern & Eli Cohen MIT Lincoln Laboratory RAPID 2013 June 11 th, 2013 This work is sponsored by the Air Force under Air Force

More information

Electric Penguin s philosophy:

Electric Penguin s philosophy: UNMANNED PLATFORMS AND SUBSYSTEMS Datasheet v 1.1 Penguin BE Electric Unmanned Platform Up to 110 minutes of endurance 2 with 2.8 kg payload 23 liters of payload volume Quick replaceable battery cartridge

More information

How To Build An Unmanned Aerial Vehicle/Aircraft System (Drone) [Name of the Writer] [Name of the Institution]

How To Build An Unmanned Aerial Vehicle/Aircraft System (Drone) [Name of the Writer] [Name of the Institution] 1! How To Build An Unmanned Aerial Vehicle/Aircraft System (Drone) [Name of the Writer] [Name of the Institution] !2 How To Build An Unmanned Aerial Vehicle/Aircraft System (Drone) Introduction Terminology

More information

Powertrain Design for Hand- Launchable Long Endurance Unmanned Aerial Vehicles

Powertrain Design for Hand- Launchable Long Endurance Unmanned Aerial Vehicles Powertrain Design for Hand- Launchable Long Endurance Unmanned Aerial Vehicles Stuart Boland Derek Keen 1 Justin Nelson Brian Taylor Nick Wagner Dr. Thomas Bradley 47 th AIAA/ASME/SAE/ASEE JPC Outline

More information

MAV and UAV Research at Rochester Institute of Technology. Rochester Institute of Technology

MAV and UAV Research at Rochester Institute of Technology. Rochester Institute of Technology MAV and UAV Research at Andrew Streett 5 th year BS/MS Student 2005-2006 MAV Team Lead Jason Grow BS/MS Graduate of RIT 2003-2004 MAV Team Lead Boeing Phantom Works, HB 714-372-9026 jason.a.grow@boeing.com

More information

A brief History of Unmanned Aircraft

A brief History of Unmanned Aircraft A brief History of Unmanned Aircraft Technological Background Dr. Bérénice Mettler University of Minnesota Jan. 22-24, 2012 (v. 1/15/13) Dr. Bérénice Mettler (University of Minnesota) A brief History of

More information

AE 451 Aeronautical Engineering Design Final Examination. Instructor: Prof. Dr. Serkan ÖZGEN Date:

AE 451 Aeronautical Engineering Design Final Examination. Instructor: Prof. Dr. Serkan ÖZGEN Date: Instructor: Prof. Dr. Serkan ÖZGEN Date: 11.01.2012 1. a) (8 pts) In what aspects an instantaneous turn performance is different from sustained turn? b) (8 pts) A low wing loading will always increase

More information

Analysts/Fund Managers Visit 19 April Autonomous Systems and Future Capability Mark Kane

Analysts/Fund Managers Visit 19 April Autonomous Systems and Future Capability Mark Kane Analysts/Fund Managers Visit 19 April 2007 Autonomous Systems and Future Capability Mark Kane The Rationale for UAVs The Rationale for UAVs UAVs generally seen to carry out the dull, dirty, and dangerous

More information

EWADE th European Workshop on Aircraft Design Education - Naples 2011

EWADE th European Workshop on Aircraft Design Education - Naples 2011 EWADE 2011 10th European Workshop on Aircraft Design Education - Naples 2011 Regional turboprop conversion for purposes supposing auxiliary engine installation. Technical and economical analysis Prof.

More information

Solar Glider. ENG460 Engineering Thesis Final Report. Ben Marshall,

Solar Glider. ENG460 Engineering Thesis Final Report. Ben Marshall, Solar Glider ENG460 Engineering Thesis Final Report Ben Marshall, 30769634 2012 A report submitted to the School of Engineering and Energy, Murdoch University in partial fulfilment of the requirements

More information

A STUDY OF STRUCTURE WEIGHT ESTIMATING FOR HIGH ALTITUDE LONG ENDURENCE (HALE) UNMANNED AERIAL VEHICLE (UAV)

A STUDY OF STRUCTURE WEIGHT ESTIMATING FOR HIGH ALTITUDE LONG ENDURENCE (HALE) UNMANNED AERIAL VEHICLE (UAV) 5 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES A STUDY OF STRUCTURE WEIGHT ESTIMATING FOR HIGH ALTITUDE LONG ENDURENCE (HALE UNMANNED AERIAL VEHICLE (UAV Zhang Yi, Wang Heping School of Aeronautics,

More information

Small UAV A French MoD perspective and planning

Small 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 information

ANALYSIS OF THE LIGHT OFF-ROAD VEHICLE ENDOWMENT POSSIBILITIES IN ORDER TO USE IT FOR AIR FORCE MISSIONS

ANALYSIS OF THE LIGHT OFF-ROAD VEHICLE ENDOWMENT POSSIBILITIES IN ORDER TO USE IT FOR AIR FORCE MISSIONS HENRI COANDA AIR FORCE ACADEMY ROMANIA INTERNATIONAL CONFERENCE of SCIENTIFIC PAPER AFASES 2015 Brasov, 28-30 May 2015 GENERAL M.R. STEFANIK ARMED FORCES ACADEMY SLOVAK REPUBLIC ANALYSIS OF THE LIGHT OFF-ROAD

More information

Evaluation of Novel Wing Design for UAV

Evaluation of Novel Wing Design for UAV Evaluation of Novel Wing Design for UAV P. K. Bahumanyam 1 1 University of Alabama in Huntsville, Huntsville, AL, USA *Corresponding author: pkb0003@uah.edu Abstract: Viable design alternative for the

More information

Propeller Blade Bearings for Aircraft Open Rotor Engine

Propeller Blade Bearings for Aircraft Open Rotor Engine NTN TECHNICAL REVIEW No.84(2016) [ New Product ] Guillaume LEFORT* The Propeller Blade Bearings for Open Rotor Engine SAGE2 were developed by NTN-SNR in the frame of the Clean Sky aerospace programme.

More information

PENGUIN C UAS OPERATIONS & MAINTENANCE TRAINING 20 HOURS FLIGHT ENDURANCE 100KM RANGE ITAR - FREE CREW OF TWO

PENGUIN C UAS OPERATIONS & MAINTENANCE TRAINING 20 HOURS FLIGHT ENDURANCE 100KM RANGE ITAR - FREE CREW OF TWO PENGUIN C UAS LONG ENDURANCE UNMANNED AERIAL SYSTEM 20 HOURS FLIGHT ENDURANCE OPERATIONS & MAINTENANCE TRAINING 100KM RANGE ITAR - FREE CREW OF TWO U AV FAC T O RY LT D., E U R O P E U AV FAC T O RY U

More information

THE KARANTANIA UNMANNED AERIAL SYSTEM

THE KARANTANIA UNMANNED AERIAL SYSTEM THE KARANTANIA UNMANNED AERIAL SYSTEM ABSTRACT Tomaž Meze, Bogo Štempihar, Mihael Grom MIBO MODLI d.o.o. Čevica 6, SI 1370 Logatec, Slovenia tomi.meze@siol.net, info@mibojets.com Tone Magister University

More information

A SOLAR POWERED UAV. 1 Introduction. 2 Requirements specification

A SOLAR POWERED UAV. 1 Introduction. 2 Requirements specification A SOLAR POWERED UAV Students: R. al Amrani, R.T.J.P.A. Cloosen, R.A.J.M. van den Eijnde, D. Jong, A.W.S. Kaas, B.T.A. Klaver, M. Klein Heerenbrink, L. van Midden, P.P. Vet, C.J. Voesenek Project tutor:

More information

The (in)compatibility of flying outdoors and indoors with the same MAV

The (in)compatibility of flying outdoors and indoors with the same MAV The (in)compatibility of flying outdoors and indoors with the same MAV Rick Ruijsink Contents Introduction Ruijsink Dynamic Engineering Operational criteria for outdoor flight Operational criteria for

More information

PENGUIN B UAV PLATFORM

PENGUIN B UAV PLATFORM UNMANNED PLATFORMS AND SUBSYSTEMS Datasheet v.0 PENGUIN B UAV PLATFORM Penguin B platform ready for payload and autopilot integration 0+ hour endurance Fuel injected engine option Up to 10 kg payload capacity

More information

The Institution of Engineering and Technology Seminar on. Micro UAVs. Dr Tom Richardson University of Bristol. 20 th February 2007

The Institution of Engineering and Technology Seminar on. Micro UAVs. Dr Tom Richardson University of Bristol. 20 th February 2007 The Institution of Engineering and Technology Seminar on Micro UAVs Dr Tom Richardson University of Bristol 20 th February 2007 Contact Information Address: Email: Dr Tom Richardson Department of Aerospace

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

JSBSim Library for Flight Dynamics Modelling of a mini-uav

JSBSim Library for Flight Dynamics Modelling of a mini-uav JSBSim Library for Flight Dynamics Modelling of a mini-uav Tomáš Vogeltanz and Roman Jašek Tomas Bata University in Zlín, Faculty of Applied Informatics Department of Informatics and Artificial Intelligence

More information

UNCLASSIFIED R-1 ITEM NOMENCLATURE. FY 2014 FY 2014 OCO ## Total FY 2015 FY 2016 FY 2017 FY 2018

UNCLASSIFIED R-1 ITEM NOMENCLATURE. FY 2014 FY 2014 OCO ## Total FY 2015 FY 2016 FY 2017 FY 2018 COST ($ in Millions) Years FY 2012 FY 2013 # ## FY 2015 FY 2016 FY 2017 FY 2018 To Program Element 335.638 51.642 9.122 3.326-3.326 1.396 0.930 0.279 0.284 0.000 402.617 675143: Predator 335.638 51.642

More information

THE FALCON REDUNDANCY HIGH WIND TOLERANCE BEST USED FOR SURVEILLANCE & SECURITY DELIVERY & TRANSPORT

THE FALCON REDUNDANCY HIGH WIND TOLERANCE BEST USED FOR SURVEILLANCE & SECURITY DELIVERY & TRANSPORT THE FALCON REDUNDANCY HIGH WIND TOLERANCE The Falcon's new air frame and motor configuration is the new best in its class of light payloads with flight times of up to 50 minutes. This makes the Falcon

More information

THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAV ZULKIFLI BIN YUSOF UNIVERSITI MALAYSIA PAHANG

THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAV ZULKIFLI BIN YUSOF UNIVERSITI MALAYSIA PAHANG THE ANALYSIS OF WING PERFORMANCE FOR RECONNAISSANCE UAV ZULKIFLI BIN YUSOF UNIVERSITI MALAYSIA PAHANG The Analysis of Wing Performance for Reconnaissance UAV ZULKIFLI BIN YUSOF Report submitted in partial

More information

Investigative Technologies and Techniques

Investigative Technologies and Techniques Investigative Technologies and Techniques Using Drones In Accident Investigation (Aerial Photography) Drone used in accident investigation Technical specifications and performance Flat 8 motor configuration

More information

Experimental Investigations of Biplane Bimotor Fixed-Wing Micro Air Vehicles

Experimental Investigations of Biplane Bimotor Fixed-Wing Micro Air Vehicles Experimental Investigations of Biplane Bimotor Fixed-Wing Micro Air Vehicles C. Thipyopas *, B. Bataillé and J.-M. Moschetta LAP SUPAERO, Toulouse, France, 31055 The low speed biplane MAV concept has been

More information

Aerodynamic Characteristic Analysis of UAV (Unmanned Aerial Vehicle) By Using CFD

Aerodynamic Characteristic Analysis of UAV (Unmanned Aerial Vehicle) By Using CFD Aerodynamic Characteristic Analysis of UAV (Unmanned Aerial Vehicle) By Using CFD Naresh S 1, Dr.V. Ravi 2 1 PG student, 2 Professor, Department of Mechanical engineering, BITM, Ballari, Karnataka, India

More information

Innovating the future of disaster relief

Innovating the future of disaster relief Innovating the future of disaster relief American Helicopter Society International 33rd Annual Student Design Competition Graduate Student Team Submission VEHICLE OVERVIEW FOUR VIEW DRAWING INTERNAL COMPONENTS

More information

Development of a Subscale Flight Testing Platform for a Generic Future Fighter

Development of a Subscale Flight Testing Platform for a Generic Future Fighter Development of a Subscale Flight Testing Platform for a Generic Future Fighter Christopher Jouannet Linköping University - Sweden Subscale Demonstrators at Linköping University RAVEN Rafale Flight Test

More information

CONCEPTUAL DESIGN OF FLYING VEHICLE

CONCEPTUAL DESIGN OF FLYING VEHICLE International Journal of Mechanical Engineering and Technology (IJMET) Volume 8, Issue 6, June 2017, pp. 471 479, Article ID: IJMET_08_06_049 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=8&itype=6

More information

neuron An efficient European cooperation scheme

neuron An efficient European cooperation scheme DIRECTION GÉNÉRALE INTERNATIONALE January, 2012 neuron An efficient European cooperation scheme I - INTRODUCTION 2 II - AIM OF THE neuron PROGRAMME 3 III - PROGRAMME ORGANISATION 4 IV - AN EFFICIENT EUROPEAN

More information

MA THOR SolarLight UAS

MA THOR SolarLight UAS Marques Aviation Ltd Advanced-technology Hybrid Propulsion Air Platform Advanced-technology innovative air platform project that supersedes the capabilities of the majority of MALE UAVs. Hybrid solar-electric-hydrogen

More information

SENSITIVITY ANALYSIS OF DESIGN PARAMETERS OF A SMALL SOLAR-POWERED ELECTRIC UNMANNED AERIAL VEHICLE

SENSITIVITY ANALYSIS OF DESIGN PARAMETERS OF A SMALL SOLAR-POWERED ELECTRIC UNMANNED AERIAL VEHICLE Journal of Engineering Science and Technology Vol. 13, No. 12 (2018) 3922-3931 School of Engineering, Taylor s University SENSITIVITY ANALYSIS OF DESIGN PARAMETERS OF A SMALL SOLAR-POWERED ELECTRIC UNMANNED

More information

31 st National Conference on FMFP, December 16-18, 2004, Jadavpur University, Kolkata

31 st National Conference on FMFP, December 16-18, 2004, Jadavpur University, Kolkata 31 st National Conference on FMFP, December 16-18, 24, Jadavpur University, Kolkata Experimental Characterization of Propulsion System for Mini Aerial Vehicle Kailash Kotwani *, S.K. Sane, Hemendra Arya,

More information

PIAGGIO AERO P.1HH HammerHead UAS

PIAGGIO AERO P.1HH HammerHead UAS Medium Altitude Long Endurance ISR Unmanned Aerial System Dimensions Span 15.600 m [51.18 ft] Length 14.408 m [47.27 ft] Height 3.980 m [13.05 ft] Areas Wing 18.00 m2 [193.75 ft2] Horizontal Tail 3.834

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

Overview of BAE Systems Regional Aircraft

Overview of BAE Systems Regional Aircraft Overview of BAE Systems Regional Aircraft Dr Mike West Chief Technologist Introduction to BAE Systems Regional Aircraft Eurofighter /Typhoon Joint Strike Fighter Nimrod MRA4 Surface Ships Customer Solutions

More information

Republic of Korea Airworthiness Certification of Unmanned Aerial System

Republic of Korea Airworthiness Certification of Unmanned Aerial System Republic of Korea Airworthiness Certification of Unmanned Aerial System Name : Maj. Na, Kyeong-min(ROK), Hwang, Ki-Lyong(KAL) E-mail : kminn@korea.kr, klhwang@koreanair.com Contents PART I Introduction

More information

Multirotor UAV propeller development using Mecaflux Heliciel

Multirotor UAV propeller development using Mecaflux Heliciel Multirotor UAV propeller development using Mecaflux Heliciel Sale rates of multirotor unmanned aerial vehicles, for both private and commercial uses, are growing very rapidly these days. Even though there

More information

THE INVESTIGATION OF CYCLOGYRO DESIGN AND THE PERFORMANCE

THE INVESTIGATION OF CYCLOGYRO DESIGN AND THE PERFORMANCE 25 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES THE INVESTIGATION OF CYCLOGYRO DESIGN AND THE PERFORMANCE Hu Yu, Lim Kah Bin, Tay Wee Beng Department of Mechanical Engineering, National University

More information

Design of HOMA Micro Air Vehicle at IUT

Design of HOMA Micro Air Vehicle at IUT Design of HOMA Micro Air Vehicle at IUT Hesam Salehipour *, Nasim Amiri Mechanical Engineering Students, Isfahan, IRAN and Mahmud Ashrafizaadeh Assistant Professor, Department of Mechanical Engineering,

More information

Design and Analysis of UCAV Wing with a by Varying the Cant Angle

Design and Analysis of UCAV Wing with a by Varying the Cant Angle Design and Analysis of UCAV Wing with a without Winglet by Varying the Cant Angle Rajesh A Assistant Professor, Department of Mechanical Engineering, New Horizon College of Engineering, Bangalore-560103,

More information

Future Vision in Composites & Manufacturing and their Challenges. Lars Sjostrom Director Future Business Saab Aeronautics

Future Vision in Composites & Manufacturing and their Challenges. Lars Sjostrom Director Future Business Saab Aeronautics Future Vision in Composites & Manufacturing and their Challenges Lars Sjostrom Director Future Business Saab Aeronautics November 2014 Agenda Introduction, Composites & Manufacturing Trends general aeronautics,

More information

ELECTRICAL SYSTEMS AIAA TEAM 1 VT AIAA TEAM 1 1

ELECTRICAL SYSTEMS AIAA TEAM 1 VT AIAA TEAM 1 1 ELECTRICAL SYSTEMS AIAA TEAM 1 VT AIAA TEAM 1 1 Electrical Systems in Aircraft Avionics Hydraulics Environmentalcontrol Lighting Subsystems VT AIAA TEAM 1 2 Electrical System Composition Batteries Alternators/Generators

More information

'Prototype' Commission Regulation on Unmanned Aircraft Operations. FAI proposal for model flying activities

'Prototype' Commission Regulation on Unmanned Aircraft Operations. FAI proposal for model flying activities Lausanne, 17 January 2017 'Prototype' Commission Regulation on Unmanned Aircraft Operations FAI proposal for model flying activities Annexes: 1- Article 15 - Provisions for model aircraft operations 2-

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

FLYEYE Unmanned Aerial System

FLYEYE Unmanned Aerial System FLYEYE Unmanned Aerial System FLYEYE Unmanned Aerial System About Flytronic FLYTRONIC is a dynamic modern engineering company focussed on developing Unmanned Aerial Systems to provide observation and reconnaissance

More information

Flight Research using Radio-controlled Small Airplanes

Flight Research using Radio-controlled Small Airplanes Flight Research using Radio-controlled Small Airplanes S P Govinda Raju S P Govinda Raju is a Professor at the Aerospace Engineering Department, Indian Institute of Science, Bangalore. His interests are

More information

DEVELOPMENT OF A DRIVING CYCLE FOR BRASOV CITY

DEVELOPMENT OF A DRIVING CYCLE FOR BRASOV CITY DEVELOPMENT OF A DRIVING CYCLE FOR BRASOV CITY COVACIU Dinu *, PREDA Ion *, FLOREA Daniela *, CÂMPIAN Vasile * * Transilvania University of Brasov Romania Abstract: A driving cycle is a standardised driving

More information

RDT&E BUDGET ITEM JUSTIFICATION SHEET (R-2 Exhibit) February 2003

RDT&E BUDGET ITEM JUSTIFICATION SHEET (R-2 Exhibit) February 2003 COST ($ in Thousands) Actual FY 2005 FY 2006 FY 2007 FY 2008 FY 2009 Cost to Total Cost 2671 F-16 Squadrons 107,035 81,639 87,478 99,867 111,954 120,079 111,450 113,519 Continuing TBD Quantity of RDT&E

More information

Dragon Eye. Jessica Walker Rich Stark Brian Squires. AOE 4124 Configuration Aerodynamics

Dragon Eye. Jessica Walker Rich Stark Brian Squires. AOE 4124 Configuration Aerodynamics Dragon Eye Jessica Walker Rich Stark Brian Squires Outline Purpose/Mission Air Vehicle Configuration Airfoil Data Planform Data Aerodynamic Characteristics Assessment Purpose / Mission: Real-Time Imagery

More information

THE SAGRES PROJECT - A NEW VERY LIGHT AEROPLANE. Department of Aerospace Sciences Universidade da Beira Interior Covilhã, Portugal

THE SAGRES PROJECT - A NEW VERY LIGHT AEROPLANE. Department of Aerospace Sciences Universidade da Beira Interior Covilhã, Portugal THE SAGRES PROJECT - A NEW VERY LIGHT AEROPLANE Ivan A. Camelier * & Pedro V. Gamboa Department of Aerospace Sciences Universidade da Beira Interior Covilhã, Portugal Abstract This project aims at designing

More information

Aeronautical Systems Center

Aeronautical Systems Center Aeronautical Systems Center Global Hawk Program Overview Michael Johnston 303 AESG/LG DSN: 787-4047 Comm: 937-255-4047 michael.johnston@wpafb.af.mil RQ-4A Global Hawk System Global Hawk: High-altitude,

More information

PROPOSED DESIGN OF SELF PROPELLED AERIAL VEHICLE

PROPOSED DESIGN OF SELF PROPELLED AERIAL VEHICLE PROPOSED DESIGN OF SELF PROPELLED AERIAL VEHICLE Asst.Prof. B.J.Saradava 1, Vishvesh J Upadhyay 2, Raj Dadhania 3, Mayur Gosai 4 1 Mechanical Engg. Department, Atmiya Institute of Technology and Science,

More information

SAE Aero Design. Apr 29, 2016

SAE Aero Design. Apr 29, 2016 SAE Aero Design Ali Alqalaf, Jasem Alshammari, Dong Yang Cao, Darren Frankenberger, Steven Goettl, and John Santoro Department of Mechanical Engineering Apr 29, 2016 Overview Introduction Need Statement

More information

Adapting to Limitations of a Wind Tunnel Test Facility in the Aerodynamic Testing of a new UAV

Adapting to Limitations of a Wind Tunnel Test Facility in the Aerodynamic Testing of a new UAV Adapting to Limitations of a Wind Tunnel Test Facility in the Aerodynamic Testing of a new UAV Dr K.C. Wong, Mr H.J.H. Peters 1, Mr P. Catarzi 2 School of Aerospace, Mechanical and Mechatronic Engineering

More information

SAE Aero Design. Operations Manual. Ali Alqalaf, Jasem Alshammari, Dong Yang Cao, Darren Frankenberger, Steven Goettl, and John Santoro.

SAE Aero Design. Operations Manual. Ali Alqalaf, Jasem Alshammari, Dong Yang Cao, Darren Frankenberger, Steven Goettl, and John Santoro. SAE Aero Design Operations Manual Ali Alqalaf, Jasem Alshammari, Dong Yang Cao, Darren Frankenberger, Steven Goettl, and John Santoro Team 16 Submitted towards partial fulfillment of the requirements for

More information

Primary control surface design for BWB aircraft

Primary 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 information

DESIGN AND PERFORMANCE TEST OF A TWIN- FUSELAGE CONFIGURATION SOLAR-POWERED UAV

DESIGN AND PERFORMANCE TEST OF A TWIN- FUSELAGE CONFIGURATION SOLAR-POWERED UAV DESIGN AND PERFORMANCE TEST OF A TWIN- FUSELAGE CONFIGURATION SOLAR-POWERED UAV Xian-Zhong GAO*, Zhong-Xi HOU*, Zheng GUO* Xiao-Qian CHEN* *College of Aerospace Science and Engineering, National University

More information

Keywords: UAS, SIL, Modular UAS

Keywords: UAS, SIL, Modular UAS 27 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES THE DEVELOPMENT OF AN UNMANNED AIRCRAFT SYSTEMS INTEGRATION LABORATORY AND MODULAR RESEARCH UAV J S Monk Council for Scientific and Industrial

More information

Design and Development of the UTSA Unmanned Aerial System ACE 1

Design and Development of the UTSA Unmanned Aerial System ACE 1 Design and Development of the UTSA Unmanned Aerial System ACE 1 For use in the 2010 AUVSI Student UAS Competition Ilhan Yilmaz Department of Mechanical Engineering (Team Lead) Christopher Weldon Department

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

Design of 'Iris', a Small Autonomous Surveillance UAV

Design of 'Iris', a Small Autonomous Surveillance UAV Utah State University DigitalCommons@USU Mechanical and Aerospace Engineering Faculty Publications Mechanical and Aerospace Engineering 1-9-2006 Design of 'Iris', a Small Autonomous Surveillance UAV Jennifer

More information

UAV KF-1 helicopter. CopterCam UAV KF-1 helicopter specification

UAV KF-1 helicopter. CopterCam UAV KF-1 helicopter specification UAV KF-1 helicopter The provided helicopter is a self-stabilizing unmanned mini-helicopter that can be used as an aerial platform for several applications, such as aerial filming, photography, surveillance,

More information

OPTIMAL GAP DISTANCE BETWEEN ROTORS OF MINI QUADROTOR HELICOPTER

OPTIMAL GAP DISTANCE BETWEEN ROTORS OF MINI QUADROTOR HELICOPTER 8th International DAAAM Baltic Conference INDUSTRIAL ENGINEERING 19-21 April 2012, Tallinn, Estonia OPTIMAL GAP DISTANCE BETWEEN ROTORS OF MINI QUADROTOR HELICOPTER Aleksandrov, D.; Penkov, I. Abstract:

More information

Evaluation of the Applicability of the Vortex Lattice Method to the Analysis of Human Powered Aircraft

Evaluation of the Applicability of the Vortex Lattice Method to the Analysis of Human Powered Aircraft McNair Scholars Research Journal Volume Article Evaluation of the Applicability of the Vortex Lattice Method to the Analysis of Human Powered Aircraft Armando R. Collazo Garcia III Embry-Riddle Aeronautical

More information

How to build a RC Coanda Effect Saucer

How to build a RC Coanda Effect Saucer How to build a RC Coanda Effect Saucer By Jean-Louis Naudin 1) Required electronic material for the RC version 2) Construction material - a 3 mm thick styrofoam sheet XPS (Depron, Gediplac, Ectrupor),

More information

Presentation. 16 September Piaggio Aerospace: Fuel Cells in Unmanned Aerial Vehicle Research Perspectives

Presentation. 16 September Piaggio Aerospace: Fuel Cells in Unmanned Aerial Vehicle Research Perspectives Presentation 16 September 2015 Piaggio Aerospace: Fuel Cells in Unmanned Aerial Vehicle Research Perspectives Historical background Aircraft manufacturing is started Company merges with Pegna- Bonmartini

More information

Prototyping Collision Avoidance for suas

Prototyping Collision Avoidance for suas Prototyping Collision Avoidance for Michael P. Owen 5 December 2017 Sponsor: Neal Suchy, FAA AJM-233 DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. Trends in Unmanned

More information

Integrated Airborne Surveillance Systems. November 2014

Integrated Airborne Surveillance Systems. November 2014 Integrated Airborne Surveillance Systems November 2014 Integrated Airborne Surveillance Systems ATOS Mission System for Manned Platforms Unmanned Aerial Systems (UAS) 2 ATOS Mission System ATOS (Airborne

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

Flight Stability and Control of Tailless Lambda Unmanned Aircraft

Flight Stability and Control of Tailless Lambda Unmanned Aircraft IJUSEng 2013, Vol. 1, No. S2, 1-4 http://dx.doi.org/10.14323/ijuseng.2013.5 Editor s Technical Note Flight Stability and Control of Tailless Lambda Unmanned Aircraft Pascual Marqués Unmanned Vehicle University,

More information

Lockheed Martin. Team IDK Seung Soo Lee Ray Hernandez Chunyu PengHarshal Agarkar

Lockheed Martin. Team IDK Seung Soo Lee Ray Hernandez Chunyu PengHarshal Agarkar Lockheed Martin Team IDK Seung Soo Lee Ray Hernandez Chunyu PengHarshal Agarkar Abstract Lockheed Martin has developed several different kinds of unmanned aerial vehicles that undergo harsh forces when

More information

Approche novatrice pour la conception et l exploitation d avions écologiques, sous incertitudes.

Approche 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 information

Autonomous Unmanned Aerial Systems 1. ABSTRACT

Autonomous Unmanned Aerial Systems 1. ABSTRACT 1. ABSTRACT Zeppelin FC 26, a team formed in 2014, has undergone exponential growth. We have delved into diverse and challenging endeavors, ranging from systems integration to design and development of

More information

Helicopter Experience, Date: August 1-6 Location: Central Connecticut State University

Helicopter Experience, Date: August 1-6 Location: Central Connecticut State University Helicopter Experience, 2010 Date: August 1-6 Location: Central Connecticut State University 1 Out Line Schedule Selection Process What students will receive 2 com For All Details 3 Sunday, August 1, 2010,

More information

On-Demand Mobility Electric Propulsion Roadmap

On-Demand Mobility Electric Propulsion Roadmap On-Demand Mobility Electric Propulsion Roadmap Mark Moore, ODM Senior Advisor NASA Langley Research Center EAA AirVenture, Oshkosh July 22, 2015 NASA Distributed Electric Propulsion Research Rapid, early

More information