Content Requirements Mission profile Work Progress UCAVs and system survey Preliminary Design Comparison of the two final configurations
|
|
- Abigayle Patrick
- 5 years ago
- Views:
Transcription
1
2 Content Requirements Mission profile Work Progress UCAVs and system survey Existing UCAVs Armament Engines EO/IR sensors SAR Satellite comm. Avionics Aerial refueling Yaw Control Conceptual design RCS Definition of two configurations Initial Sizing Definition of required thrust Comparison of configurations with one/two engines Engine selection Weight Breakdown Airfoils Preliminary Design Landing gears Aerial refueling / Fuel lines Performance Layout Comparison of the two final configurations Configuration Selection Summary Second Semester Tasks
3 Requirements: Operation range of 2000 NM with refueling capability Armament carrying capability of 2x500[kg] smart bombs BVR (beyond visual range) Capability Stealth Capability Capability of carrying EO/IR sensors operating in all weather conditions, including night time target acquisition
4 Mission profile 1) Taxi To Runway 2) Warm-up 3) Takeoff 4) Climb to 36,000 ft 5) M=0.8 for 1,000 nm 6) 20 min loiter over target 7) M=0.8 for 500 nm 8) 10 min loiter for aerial refuel 9) Descend to S-L 10) Landing and Taxi. 1,000 nm 20 min 500nm 10 min ,000 ft
5 Mission Range 1500 NM Max Range 1000 NM Mission Radius 750 NM Combat Radius
6 Work Process Flow Chart
7
8 UCAVs Survey X-47 A X-47 B Barracuda Neuron X-45 A X-45 C MQ-9 Weight [Lb] 5,500 7,100 13,000 12,200 10,000 Range [NM] unknown 3,200 unknown ,500 3,200 Ammunition Weight [Lb] 1, unknown 1,500 propulsion Turbo Fan Turbo Fan Turbo Fan Turbo Fan Turbo Fan Turbo Fan Turbo prop Stealth capability full full partial full full full low Status Active Demonstrator Prototype build completed Cancelled in Development Active Demonstrator cancelled operational
9 Armament Survey Main requirements: Minimum size (length and diameter) Maximum glide range High accuracy! " # $%&'" # () "() *+,-. /01 /01 /23 /23' " +, ', ,. 22!! 22!! /053 /053,&) : 9: ;77, <46%&= 052<46%&= ) + + # #
10 Armament Survey +! +() #4:! + +> +!!5+ +5
11 Propulsion Survey Turboprop Heron 2 Pratt & Whitney PT6 Reaper Honeywell TPE
12 X-45A Turbofan Honeywell F124-GA-100 X-47A Pratt & Whitney JT15D-5C X-47B Pratt & Whitney F
13 EO/IR sensors Survey Star SAFIR HD MX-15 True HD Sonoma 474 Toplite Manufacture FLIR WESCAM L-3 RAFAEL Weight(kg) TFU:45 CEU:10.4 Turret:46.72 MCU:9.07 Turret:86.4 Turret:59 Size[mm] 450x x394 Outside dia. 528 Endurance MIL-STD-810 MIL-STD [ c] MIL-STD-810 MIL-STD-461 MIL-STD-810 MIL-STD-461 MIL-STD-810 MIL-STD-461 Stabilization 6 axis LOS stabilization< 5urad 6 axis LOS stabilization< 6urad 5 axis LOS stabilization< 2urad 4axis LOS stabilization< 0.7mrad Resolution Day and night vision IR:1280x720 CCD:1280x720 yes IR:640x512 CCD:470TV lines yes IR:640x512 Not mentioned Not mentioned Not mentioned /A/ Laser Range[km] Not mentioned
14 EO/IR sensors Survey Selected Main requirements: Day & night detection ability Detection range: height: 10.67[km] (36,000 ft) horizontal range:9.75[km] (5.4 NM) Minimum decrease in stealth capability The EO sensor will be custom made to fit our configuration in a way that minimizes RCS increase. We will use the parameters of the selected alternative.
15 SAR Survey model "Honeywell" "EL/M- 2055D" "EL/M- 2055DX" SANDIA- MiniSAR" Range 35 Km 50 Km Frequency [GHz] Power[W] Weight[Kg] Honeywell EL/M-2055D EL/M-2055DX SANDIA-MiniSAR
16 Satellite Communication Survey Model Angle coverage[deg] Frequency [GHz] Gain[dB] Weight[Kg] "Gimbaled" "MIJET" "MIJETLite" "MiniMIJET" (each side)
17 Avionics Selection GPS/INS model: LN-100G. Lightweight, High MTBF, Low power consumption, Military proven hardware. Receiver/Transmitter model: ARC-210. C96; C65691$; Provides services for both the Ku and the C band antennas, Resistant to jamming. Identification Transponder model: APX-. Small ; (limited to line of sight-uhf). B 280x180x x145x x120x210 C-band antenna model: ANT5812SN. Small, Lightweight, Low power consumption. 210x180x45
18 Aerial Refueling Survey Two approaches: 1. Hose & Drogue Does not require an operator for the hose. Simultaneous refuel of several crafts capability. 2. Boom & Receptacle Does not require a drogue which sticks out of the receiving aircraft. Easy to make contact to refuel (boom operator s job). The boom is rigid and less susceptible to wind perturbations. The mass fuel flow is greater.
19 Yaw control Survey Control method Picture Yaw moment created by Pros Cons Forward opening spoilers Upper spoilers with inclination opening forward Very low RCS increment Few information about this control method Crowmixing Two elevons open in opposite directions Light weight High coupling with roll Spoilers Upper and lower spoilers High moment High RCS increment Splitters Control surface splits Low RCS increment Thrust vectoring Change of thrust direction Low dependence of flight speed Complexity High weight
20
21 RCS (Radar Cross Section) The RCS is mostly affected by: Radome Cavities Leading edges Flat sides of fuselage Corner reflection Surface currents that scatter at discontinuity Protruding elements
22 There are several ways to reduce RCS Minimize reflecting directions Use of special weapons bays Upper and curved intake to conceal the engine compressors facing Slanted/without vertical stabilizer Use of Radar Absorbing Materials
23 Definition of two configurations The design will be based on a flying wing configuration. We simultaneously developed two configurations : Zigzag configuration Delta configuration
24 Configuration and Airfoils Flying wing configuration was selected to meet stealth requirements Advantages: High fuel efficiency (high L/D) Light weight (Less materials required ) Low drag Disadvantages: Lateral and longitudinal instabilities Loss of lift due to elevator deflections Difficulty to create pitching moment Therefore special care should be applied for the stability margin Recommended approach: Use of reflex or reverse camber
25 Initial size estimation Assumption of L/D Calculation of fuel fracture required for the mission for given L/D Relation between empty and take-off weight L/DCalculation of from drag polar Based on take-off weight Comparison withother UCAV s Yields take-off weight This is an iterative method which stops with the convergence of take-off weight
26 Initial size estimationfor the two configurations Thrust required: 5700 [Lb]!"#$%$& ' ( )* +#$, -. +#, *+ *, The two configurations have the same take-off weight however the delta carries more fuel. Assuming Thrust/Weight of 0.38 (average of other UCAV s) we will need an engine that gives 5700 [Lb] thrust.
27 Comparison between single and twin engine configuration Comparison parameters single engine configuration Twin engines configuration Engine model P&W pw306a P&W JT15-5D Volume 932[lit] 2x563.5=1127[lit] Weight 1043[lb] 2x627=1254[lb] Thrust 6400[lb] 2x3045=6090[lb] TSFC 0.394[lb/hr/lb] 0.55[lb/hr/lb] Redundancy One engine Two engines Accompanying system weight 330[lb] 430[lb] Inlet Weight 150[lb] 310[lb] Inlet Area 4[ft^2] 4.5[ft^2] Nozzle Weight 21[lb] 30[lb] Nozzle Area 2.7[ft^2] 3[ft^2]
28 Engine Model P&W pw306a Honeywell AS907 CFE B Povazske DV-2A Rolls Royce Adour MK871 Thrust 6400 [lb st] 6500 [lb st] 5725 [lb st] 5693 [lb st] 6030 [lb st] Weight 1043 [lb] 1364 [lb] 1325 [lb] 1389 [lb] 1330 [lb] Length 75.6 [in] 90 [in] 99 [in] 68 [in] 76.7 [in] Fan diameter TSFC [lb/hr/lb] 31.6 [in] 34.2[in] 34.4 [in] 25.4[in] 30.9 [in] 0.42 [lb/hr/lb] [lb/hr/lb] [lb/hr/lb] BPR
29 The selected engine is : P&W pw306a Thrust:6400 [lb st] Weight: 1043 [lb] Fan diameter: 31.6 [in] TSFC min:0.394 [lb/hr/lb] Conclusion: The selected engine has some advantages over the other engines Lightest engine Growth possibility One of the shortest engines Good TSFC
30 Weight Breakdown Component Delta Weight [lb] Wing Fuselage Engine 1043 Air induct Tailpipe 60.2 Nose landing gear Main landing gear Propulsion system Fuel system Hydraulics Electrical system Avionics Flight control ECS + Anti-icing Handling gear 4.8 Total empty weight 8658 Zig-Zag Component Weight [lb] Wing Fuselage Engine 1043 Air induct Tailpipe 60.2 Nose landing gear Main landing gear Propulsion system Fuel system Hydraulics Electrical system Avionics Flight control ECS + Anti-icing Handling gear 4.8 Total empty weight 8973
31 Weight Breakdown 5 5; 8C C. G. 3.3% MAC X N 8.84% MAC C. G. 0 Rear X N 5.54% MAC C. G. 0 Forward Component Weight [lb] Location [ft] Wing Fuselage Engine Air induct Tailpipe Nose landing gear Main landing gear Propulsion system Fuel Aerial refuel Hydraulics Electrical system Avionics Flight control Armament Misc (spread) Weight Reserve Rear C.G Forward C.G
32 Weight Breakdown 5 5;! C C. G. 0.7% MAC X N 4.6% MAC C. G. 0 Rear X N 5.3% MAC C. G. 0 Forward Component Weight [lb] Location [ft] Wing Fuselage Engine Air induct Tailpipe Nose landing gear Main landing gear Propulsion system Fuel Aerial refuel Hydraulics Electrical system Avionics Flight control Armament Misc (spread) Weight Reserve Rear C.G Forward C.G
33 Airfoil Selection MAX. CAMBER 1.75% at 16.3% 2.17% at 19.5% 1.54% at 27.2% MAX. THICKNESS 12.62% at 34.3% 12.86% at 33.4% 12.23% at 36.9% AIRFOIL EPPLER325 EPPLER326 EPPLER360
34 ;4:2 ;4:1 ;426
35
36 Landing gears landing gears arrangement selection: Tricycle a4 M a Load limitations: M f 0.05 B 0.2 B a3 a1 a2 Criterion a1 [deg] a2 [deg] a3 [deg] a4 [deg] Ma/B Mf/B H [ft] Ma [ft] B [ft] Zig-zag Delta
37
38 Aerial Refueling/Fuel Lines Selected system: Boom & Receptacle. The boom is standard and has a diameter of 200 mm which is derived using dimension analysis. The receptacle is of a unique design enabling it to grasp and detach the boom. # Fuel Lines? Fuel systems can be classified in two broad categories: 1. Gravity-Feed Systems. 2. Pressure-Feed Systems.
39 The fuel lines which carry the fuel from the receptacle to the fuel tanks can use the gravity feed approach. The fuel lines that carry fuel from the fuel tanks to the engine, however, have to utilize fuel pumps; (the fuel pumps are integral in the fuel tanks). Top View: D:66! D16! " - " D46 ; Refueling time calculation: For Zig-Zag : t=0.577[min]=35[sec] For Delta: t=0.667[min]=40[sec] Typical fuel pressure in fuel lines: P 20[ Psi]
40 Performance Analysis Takeoff distance: V V V S S TO TR CL 1 R ln W max 2 S TR R R hobsticle S C t V 0 V V TO ST V ST ST K TO 1 R TR C A 0 K T 2 2 gk A C S S S S S L S 2 TO For Delta configuration takeoff distance is 1.15km For Zig-Zag configuration takeoff distance is 1.22km
41 Performance Analysis Landing distance: V V V S app F TD a ST ST ST 2 2 S F R R hobsticle S S FR B V V V t V TD K ln K K V 2 g K T 2 T A TD S S S S S LF L a F FR B A For Delta configuration landing distance is 1.03km For Zig-Zag configuration landing distance is 1.19km
42 Performance Analysis Takeoff rotation: 1 2 WTO M a H VTO S ref X CP X e CG M rear a C L e e 2 S elevons C L 0.9 K e C l cos e e S ref C For Zig-Zag with e 0.1 elevon angle is 13.9 C C For Delta with e 0.13 elevon angle is 5.7 C
43 Performance Analysis Climb Rate: V ver V C W 2W S 3 T climb D0 K V W climb Vclimb W S 2 T climb T V 12CD0K 3 C W W D0 2 S Altitude [ft] Climb Rate [ft/min] Climb Velocity [kts] Mach Number 10, , , Altitude [ft] Climb Rate [ft/min] Climb Velocity [kts] Mach Number 10, , ,
44 Performance Analysis Flight envelopes: Delta Zig-Zag
45 LAYOUT Delta Configuration Development
46 Zig-Zag Zag Configuration Development
47 Delta Configuration
48 Zig-Zag Zag Configuration
49 Delta Animation
50 Zig-Zag Zag Animation
51 Delta interior components? - E7! # F%& ' F %???+ 7! ;G$% #7
52 Zig-Zag Zag interior components? - E7! # F%& ' F %???+ 7! ;G$% #7
53 Delta Section View Animation
54 Zig-Zag Zag Section View Animation
55 Configuration Comparison Category Zig-Zag Delta Weight 14,300 [lb] 14,460 [lb] Fuel weight 3,117 [lb] 3,600 [lb] AR Wing loading 30 [lbf/ft^2] 36 [lbf/ft^2] Engine P&W pw306a P&W pw306a Airfoil Eppler 360 Eppler 360 Flight ceiling 46,000 [ft] 40,000 [ft] Takeoff distance 1.22 [km] 1.15 [km] Takeoff rotation (elevon angle) Landing distance 1.19 [km] 1.03 [km] Aerial refueling time 35 [sec] 40 [sec] Climb rate (36,000 [ft]) 4869 [ft/min] 4606 [ft/min] Longitudinal stability Unstable Stable No. of reflecting surfaces (RCS) 2 3
56 Chosen Configuration
57 Summary Goal achievement: Operation range of 2000 NM with refueling capability Armament carrying capability of at least 2x500[kg] smart bombs BVR (beyond visual range) Capability Stealth Capability Capability of carrying EO/IR sensors operating in all weather conditions, including night time target acquisition
58 Second Semester Tasks Detail design and Analysis of: Wing structure Landing gear Control surfaces Flight control system Evaluation of RCS Wind tunnel test: Design of wind tunnel model Manufacture of wind tunnel model Conducting wind tunnel test
59
CERBERUS UCAV: Unmanned Combat Aerial Vehicle.
CERBERUS UCAV: Unmanned Combat Aerial Vehicle. Team members: Marina Kats, Alex Konevsky, Tomer Buium, Oran Katzuni, Matan Argaman, Jacob Frumkin, Amir Levy. Project supervisor: Mr. Dror Artzi Abstract
More informationAN ADVANCED COUNTER-ROTATING DISK WING AIRCRAFT CONCEPT Program Update. Presented to NIAC By Carl Grant November 9th, 1999
AN ADVANCED COUNTER-ROTATING DISK WING AIRCRAFT CONCEPT Program Update Presented to NIAC By Carl Grant November 9th, 1999 DIVERSITECH, INC. Phone: (513) 772-4447 Fax: (513) 772-4476 email: carl.grant@diversitechinc.com
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 informationAnalysis of JSF Prototypes
Analysis of JSF Prototypes By: Timothy D. Collins Photo from: http://www.popsci.com/scitech/features/xplane/index.html Boeing X-32 on Left, and Lockheed-Martin X-35 on Right. These two aircraft are designed
More informationAE 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 informationThe Airplane That Could!
The Airplane That Could! Critical Design Review December 6 th, 2008 Haoyun Fu Suzanne Lessack Andrew McArthur Nicholas Rooney Jin Yan Yang Yang Agenda Criteria Preliminary Designs Down Selection Features
More informationClassical Aircraft Sizing I
Classical Aircraft Sizing I W. H. Mason from Sandusky, Northrop slide 1 Which is 1 st? You need to have a concept in mind to start The concept will be reflected in the sizing by the choice of a few key
More informationThree major types of airplane designs are 1. Conceptual design 2. Preliminary design 3. Detailed design
1. Introduction 1.1 Overview: Three major types of airplane designs are 1. Conceptual design 2. Preliminary design 3. Detailed design 1. Conceptual design: It depends on what are the major factors for
More informationGACE Flying Club Aircraft Review Test 2018 N5312S & N5928E. Name: GACE #: Score: Checked by: CFI #:
GACE Flying Club Aircraft Review Test 2018 N5312S & N5928E Name: GACE #: Score: Checked by: CFI #: Date: (The majority of these questions are for N5312S. All N5928E questions will be marked 28E) 1. What
More informationPredator B: The Multi-Role UAV
Predator B: The Multi-Role UAV June 2002 Report Documentation Page Form Approved OMB No. 0704-0188 Public reporting burden for the collection of information is estimated to average 1 hour per response,
More informationUninhabited Air Vehicle (UAV) Costing Considerations PSI Team. SCAF Workshop 22 November 2010
Uninhabited Air Vehicle (UAV) Costing Considerations PSI Team SCAF Workshop 22 November 2010 UAV Design Considerations 1. Role 2. Design quality military / commercial? 3. Performance altitude, speed, endurance
More informationJay 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 informationEurofighter. Pilot s Notes CONTENTS. INTRODUCTION... 2 Eurofighter specifications... 2 AIRCRAFT IN THIS SIMULATION... 4 FLIGHT DYNAMICS...
Eurofighter Pilot s Notes CONTENTS INTRODUCTION... 2 Eurofighter specifications... 2 AIRCRAFT IN THIS SIMULATION... 4 FLIGHT DYNAMICS... 12 WEAPONS AND EQUIPMENT... 13 EUROFIGHTER WALK AROUND... 17 COCKPIT
More informationUSAF Strike Fighters. An analysis of range, stamina, turning, and acceleration By Spurts
USAF Strike Fighters An analysis of range, stamina, turning, and acceleration By Spurts The Contenders There are currently slated to be three USAF strike aircraft in the 2020 timeframe F-15E Strike Eagle
More informationAircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, 2012 Chapter 11 Aircraft Weight Distribution Tables
Aircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, 01 Chapter 11 Aircraft Weight Distribution Tables No Component group Elements Weight X cg Y cg Z cg 1 Wing 1.1. Wing main structure 1..
More informationGeneral Dynamics F-16 Fighting Falcon
General Dynamics F-16 Fighting Falcon http://www.globalsecurity.org/military/systems/aircraft/images/f-16c-19990601-f-0073c-007.jpg Adam Entsminger David Gallagher Will Graf AOE 4124 4/21/04 1 Outline
More informationDesign Considerations for Stability: Civil Aircraft
Design Considerations for Stability: Civil Aircraft From the discussion on aircraft behavior in a small disturbance, it is clear that both aircraft geometry and mass distribution are important in the design
More informationAE 452 Aeronautical Engineering Design II Installed Engine Performance. Prof. Dr. Serkan Özgen Dept. Aerospace Engineering March 2016
AE 452 Aeronautical Engineering Design II Installed Engine Performance Prof. Dr. Serkan Özgen Dept. Aerospace Engineering March 2016 Propulsion 2 Propulsion F = ma = m V = ρv o S V V o ; thrust, P t =
More information1.1 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 informationWHEN BORDER SECURITY MATTERS
WHEN BORDER SECURITY MATTERS WHEN BORDER SECURITY MATTERS Archangel performs long-range Intelligence, Surveillance and Reconnaissance (ISR) and standoff precision strike missions while maintaining a Common
More informationNorth American F-86F Sabre USER MANUAL. Virtavia F-86F Sabre DTG Steam Edition Manual Version 1
North American F-86F Sabre USER MANUAL 0 Introduction The F-86 Sabre was a natural replacement for the F-80 Shooting Star. First introduced in 1949 for the United States Air Force, the F-86 featured excellent
More informationCessna Citation Model Stats
Cessna Citation Model Stats Cessna Citation Sovereign - Dimensions Length 63 ft 6 in (19.35 m) Height 20 ft 4 in (6.20 m) Wingspan 72 ft 4 in (22.04 m) Wing Wing Area Wing Sweep Wheelbase Tread 516 sq
More informationDESIGNING AND DEVELOPMENT OF UNMANNED AERIAL VEHICLE
ICAS 2002 CONGRESS DESIGNING AND DEVELOPMENT OF UNMANNED AERIAL VEHICLE MUHAMMAD ASIM Engineering Wing PAF Base Minhas PAKISTAN,43175 a007pk@yahoo.com DR ABID ALI KHAN Aerospace Engg Dept College of Aeronautical
More informationAE 451 Aeronautical Engineering Design I Estimation of Critical Performance Parameters. Prof. Dr. Serkan Özgen Dept. Aerospace Engineering Fall 2015
AE 451 Aeronautical Engineering Design I Estimation of Critical Performance Parameters Prof. Dr. Serkan Özgen Dept. Aerospace Engineering Fall 2015 Airfoil selection The airfoil effects the cruise speed,
More informationAT-10 Electric/HF Hybrid VTOL UAS
AT-10 Electric/HF Hybrid VTOL UAS Acuity Technologies Robert Clark bob@acuitytx.com Summary The AT-10 is a tactical size hybrid propulsion VTOL UAS with a nose camera mount and a large payload bay. Propulsion
More informationSafety & Economics Trade Study
Safety & Economics Trade Study Principal Investigator: Prof. Ken Sivier Graduate Research Assistant: Jennifer Bradley 1 2-1 SMART ICING SYSTEMS Research Organization Core Technologies Aerodynamics and
More informationFull-Scale 1903 Wright Flyer Wind Tunnel Test Results From the NASA Ames Research Center
Full-Scale 1903 Wright Flyer Wind Tunnel Test Results From the NASA Ames Research Center Henry R. Jex, Jex Enterprises, Santa Monica, CA Richard Grimm, Northridge, CA John Latz, Lockheed Martin Skunk Works,
More informationPIAGGIO 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 informationFlugzeugentwurf / Aircraft Design SS Part 35 points, 70 minutes, closed books. Prof. Dr.-Ing. Dieter Scholz, MSME. Date:
DEPARTMENT FAHRZEUGTECHNIK UND FLUGZEUGBAU Flugzeugentwurf / Aircraft Design SS 2015 Duration of examination: 180 minutes Last Name: Matrikelnummer: First Name: Prof. Dr.-Ing. Dieter Scholz, MSME Date:
More informationThe winner team will have the opportunity to perform a wind tunnel test campaign in the transonic/supersonic Wind tunnel at the VKI.
Aircraft Design Competition Request for proposal (RFP) - High speed UAV Objectives: This RFP asks for an original UAV design capable of reaching, in less than 15 minutes, a given target located at 150
More informationDesigning evtol for the Mission NDARC NASA Design and Analysis of Rotorcraft. Wayne Johnson From VTOL to evtol Workshop May 24, 2018
Designing evtol for the Mission NDARC NASA Design and Analysis of Rotorcraft Wayne Johnson From VTOL to evtol Workshop May 24, 2018 1 Conceptual Design of evtol Aircraft Conceptual design Define aircraft
More informationSPECIAL MISSION AIRCRAFT
SPECIAL MISSION AIRCRAFT precision from above FACTS AND SPECIFICATIONS DA42 MPP Guardian - Facts and Specifications Power plant Engine Propeller Fuel grades 2x AUSTRO ENGINE AE300 (168 hp, turbo charged)
More informationneuron 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 informationAircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, 2012 Chapter 3 Aircraft Conceptual Design. Tables
Aircraft Design: A Systems Engineering Approach, M. Sadraey, Wiley, 2012 Chapter 3 Aircraft Conceptual Design Tables No Component Primary function Major areas of influence 1 Fuselage Payload accommodations
More informationSpan m [65.16 ft] Length m [43.89 ft] Height m [12.08 ft]
MPA Multirole Patrol Aircraft Dimensions Span 21.378 m [65.16 ft] Length 14.400 m [43.89 ft] Height 3.964 m [12.08 ft] Weights Max Takeoff (MTOW) Max Landing (MLW) Zero Fuel (ZFW) Mission Payload (mission
More informationFlying Low and Slow. (and the Tools for its Calculation) Dieter Scholz. Hamburg University of Applied Sciences
AIRCRAFT DESIGN AND SYSTEMS GROUP (AERO) (and the Tools for its Calculation) Hamburg University of Applied Sciences 12th European Workshop on Aircraft Design Education (EWADE) 2015 (and the Tools for its
More informationElectric 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 informationAERONAUTICAL ENGINEERING
AERONAUTICAL ENGINEERING SHIBIN MOHAMED Asst. Professor Dept. of Mechanical Engineering Al Ameen Engineering College Al- Ameen Engg. College 1 Aerodynamics-Basics These fundamental basics first must be
More informationMethodology for Distributed Electric Propulsion Aircraft Control Development with Simulation and Flight Demonstration
1 Methodology for Distributed Electric Propulsion Aircraft Control Development with Simulation and Flight Demonstration Presented by: Jeff Freeman Empirical Systems Aerospace, Inc. jeff.freeman@esaero.com,
More informationChapter 8. Example Point Design - Suppression of Enemy Air Defenses
Chapter 8 Example Point Design - Suppression of Enemy Air Defenses In order to quantify the sensitivity of UAVs to potential technological advances and to define promising UAVs as precisely as possible,
More information31 st Annual American Helicopter Society Student Design Competition: Graduate Submission
Rotorcraft Adaptive and Morphing Structures Lab The Emperor UAV: Executive Summary George Jacobellis Alex Angilella Jean-Paul Reddinger Andrew Howard Matthew Misiorowski Michael Pontecorvo Jayanth Krishnamurthi
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 informationPAC 750XL PAC 750XL PAC-750XL
PAC 750XL The PAC 750XL combines a short take off and landing performance with a large load carrying capability. The PAC 750XL is a distinctive type. Its design philosophy is reflected in the aircraft's
More informationAircraft Design Conceptual Design
Université de Liège Département d Aérospatiale et de Mécanique Aircraft Design Conceptual Design Ludovic Noels Computational & Multiscale Mechanics of Materials CM3 http://www.ltas-cm3.ulg.ac.be/ Chemin
More informationDISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.
IMPORTANT NOTICE: A hard copy of this document may not be the document currently in effect. The current version is always the version on the Lockheed Martin network. Bill Gigliotti 25 October 2014 2014
More informationHigh aspect ratio for high endurance. Mechanical simplicity. Low empty weight. STOVL or STOL capability. And for the propulsion system:
Idealized tilt-thrust (U) All of the UAV options that we've been able to analyze suffer from some deficiency. A diesel, fixed-wing UAV could possibly satisfy the range and endurance objectives, but integration
More informationInnovating 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 informationFlugzeugentwurf / Aircraft Design WS 10/ Klausurteil 30 Punkte, 60 Minuten, ohne Unterlagen. Prof. Dr.-Ing. Dieter Scholz, MSME
DEPARTMENT FAHRZEUGTECHNIK UND FLUGZEUGBAU Prof. Dr.-Ing. Dieter Scholz, MSME Flugzeugentwurf / Aircraft Design WS 10/11 Bearbeitungszeit: 180 Minuten Name: Matrikelnummer.: Vorname: Punkte: von 68 Note:
More informationEWADE 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 informationFLYEYE 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 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 informationVisit Beechcraft.com or contact a defense company sales rep:
AT-6 Visit or contact a defense company sales rep: +1.316.676.0800 Images may show optional equipment. 2013 Beechcraft Defense Company LLC. All rights reserved. Beechcraft is a registered trademark of
More informationAIAA UNDERGRADUATE TEAM DESIGN COMPETITION PROPOSAL 2017
TADPOLE AIAA UNDERGRADUATE TEAM DESIGN COMPETITION PROPOSAL 2017 Conceptual Design of TADPOLE Multi-Mission Amphibian MIDDLE EAST TECHNICAL UNIVERSITY 5-10-2017 Team Member AIAA Number Contact Details
More informationAnswer Key. Page 1 of 10
Name: Answer Key Score: [1] When range and economy of operation are the principal goals, the pilot must ensure that the airplane will be operated at the recommended A. equivalent airspeed. B. specific
More informationClean Sky 2. LifeCraft Demonstrationt (IADP RC 2 & ITDs) Consultation meetings Brussels th December 2012 OUTLINE
Clean Sky 2 LifeCraft Demonstrationt (IADP RC 2 & ITDs) Consultation meetings Brussels 10-14 th December 2012 1 1 LifeCraft - The Compound Demo OUTLINE Presentation of the Compound R/C Concept Impact &
More informationF-5E Tiger II USER MANUAL. Virtavia F-5E Tiger II DTG Steam Edition Manual Version 2.0
F-5E Tiger II USER MANUAL 0 Introduction The F-5E Tiger II is an improved version of the original F-5 Freedom Fighter that entered service with the US Military in the early 1960s. It is a lightweight,
More informationProp effects (Why we need right thrust) Torque reaction Spiraling Slipstream Asymmetric Loading of the Propeller (P-Factor) Gyroscopic Precession
Prop effects (Why we need right thrust) Torque reaction Spiraling Slipstream Asymmetric Loading of the Propeller (P-Factor) Gyroscopic Precession Propeller torque effect Influence of engine torque on aircraft
More informationGRC Aircraft Operations Office
GRC Aircraft Operations Office Glenn Research Center Aircraft Operations 1 Mission Provide safety, operational, and engineering oversight to all GRC research experiments involving flight, including non-nasa
More informationThis Flight Planning Guide is published for the purpose of providing specific information for evaluating the performance of the Cessna Corvalis TT.
May 2010 TABLE OF CONTENTS This Flight Planning Guide is published for the purpose of providing specific information for evaluating the performance of the Cessna Corvalis TT. This guide is developed from
More informationEGLIN AERO CLUB C-172 OPEN BOOK EXAMINATION Apr Total usable fuel capacity for the aircraft with long range tanks is:
(The following questions are taken from the C-172N POH) 1. Total usable fuel capacity for the aircraft with long range tanks is: a. 54 gallons b. 50 gallons c. 62 gallons d. 40 gallons 2. Total fuel capacity
More informationUSAF Strike Fighters. An analysis of range, stamina, turning, and acceleration
USAF Strike Fighters An analysis of range, stamina, turning, and acceleration The Contenders There are currently slated to be three USAF strike aircraft in the 2020 timeframe F-15E Strike Eagle One of
More informationFlight Test Evaluation of C-130H Aircraft Performance with NP2000 Propellers
Flight Test Evaluation of C-130H Aircraft Performance with NP2000 Propellers Lance Bays Lockheed Martin - C-130 Flight Sciences Telephone: (770) 494-8341 E-Mail: lance.bays@lmco.com Introduction Flight
More informationPENGUIN 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 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 informationMike Gibbons Paul Summers John Murnane
Outpacing threats in a 2030+ A2/AD environment affordably! RROI 13-01092 - BDS Mike Gibbons Paul Summers John Murnane August 27, 2013 Capability Continuum Evolution of the Super Hornet Mission Systems
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 informationHow the V-22 Osprey Works
How the V-22 Osprey Works It has long been a dream of aircraft designers to create an airplane that not only can fly long ranges at high speeds and carry heavy cargo, but can also take off, hover and land
More informationDassault Falcon 50 Microsoft Flight Simulator 2004
Dassault Falcon 50 Microsoft Flight Simulator 2004 Model and bitmaps Yannick Lavigne Custom gauge programming Fred Banting Flight dynamics Rob Young and Eric Dantes. Foto: Gerry Stegmeier Foto: Dassault
More informationAW139. Search and Rescue SIMPLY NO RIVALS
AW139 Search and Rescue SIMPLY NO RIVALS PERFORMING IN ALL CONDITIONS The AW139 is the market-leading intermediate twin-engine helicopter. Designed specifically to meet the multi-mission demands of a broad
More informationHeavy Lifters Design Team. Virginia Polytechnic Institute and State University Free-Weight Final Report Spring 2007
Heavy Lifters Design Team Virginia Polytechnic Institute and State University Free-Weight Final Report Spring 2007 The Heavy Lifters Leslie Mehl AIAA # 281854 Daniel Opipare AIAA #275371 Dzejna Mujezinovic
More informationAIAA Foundation Undergraduate Team Aircraft Design Competition. RFP: Cruise Missile Carrier
AIAA Foundation Undergraduate Team Aircraft Design Competition RFP: Cruise Missile Carrier 1999/2000 AIAA FOUNDATION Undergraduate Team Aircraft Design Competition I. RULES 1. All groups of three to ten
More informationFokker 50 - Limitations GENERAL LIMITATIONS MASS LIMITATIONS. Page 1. Minimum crew. Maximum number of passenger seats.
GENERAL LIMITATIONS Minimum crew Cockpit: Two pilots Maximum number of passenger seats Sixty-two (62) Maximum operating altitudes Maximum operating pressure altitude: Maximum take-off and landing pressure
More informationBAYLOR UNIVERSITY DEPARTMENT OF ENGINEERING. EGR 4347 Analysis and Design of Propulsion Systems Fall 2002 ASSIGNMENT GUIDELINES
BAYLOR UNIVERSITY DEPARTMENT OF ENGINEERING EGR 4347 Analysis and Design of Propulsion Systems Fall 2002 Design Project I Dr Van Treuren 100 points ASSIGNMENT GUIDELINES For this assignment, you may work
More informationAIRCRAFT DESIGN SUBSONIC JET TRANSPORT
AIRCRAFT DESIGN SUBSONIC JET TRANSPORT Analyzed by: Jin Mok Professor: Dr. R.H. Liebeck Date: June 6, 2014 1 Abstract The purpose of this report is to design the results of a given specification and to
More informationSEASPRITE. SH-2G Super MODERN MARITIME SOLUTION
SEASPRITE SH-2G Super MODERN MARITIME SOLUTION Flexible The Kaman SH-2G Super Seasprite is the ideal multimission maritime helicopter. From anti-submarine warfare, to anti-surface warfare, over-the-horizon
More informationSupervisor: Artzi Dror. Preliminary Design Review
Remote Special Purpose- Eye Supervisor: Artzi Dror Preliminary Design Review This project deals with UAV, that is carried and launched by the existing manned plane. The UAV s purpose is to enlarge the
More informationDavid s Flight Simulator Operations Manual
DPW Solutions David s Flight Simulator Operations Manual Draft 0.2 David Woolterton Update 10/5/2016 Table of Contents Pre-Start Checklist... 2 Startup Checklist... 3 Before Taxi Checklist... 3 Taxi Checklist...
More informationDUCHESS BE-76 AND COMMERCIAL MULTI ADD-ON ORAL REVIEW FOR CHECKRIDE
DUCHESS BE-76 AND COMMERCIAL MULTI ADD-ON ORAL REVIEW FOR CHECKRIDE The Critical Engine The critical engine is the engine whose failure would most adversely affect the airplane s performance or handling
More informationChapter 4 Estimation of wing loading and thrust loading - 10 Lecture 18 Topics
Chapter 4 Estimation of wing loading and thrust loading - 10 Lecture 18 Topics 4.15.3 Characteristics of a typical turboprop engine 4.15.4 Characteristics of a typical turbofan engine 4.15.5 Characteristics
More informationFLASHCARDS AIRCRAFT. Courtesy of the Air Safety Institute, a Division of the AOPA Foundation, and made possible by AOPA Services Corporation.
AIRCRAFT FLASHCARDS Courtesy of the Air Safety Institute, a Division of the AOPA Foundation, and made possible by AOPA Services Corporation. Knowing your aircraft well is essential to safe flying. These
More informationTHE 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 informationPredator ACTD. Presentation To NDIA IOT&E
Predator ACTD Presentation To NDIA IOT&E Tier 2 ACTD Highlights Program run by Joint Program Office (JPO) GOAL: rapid deployment of long endurance medium unmanned ISR platform Performance objectives: Over
More informationReview of. Eurofighter Typhoon. Developed by Just Flight
Review of Eurofighter Typhoon Developed by Just Flight The Eurofighter is a twin engine, single/twin seat, delta wing, multirole fighter built by Eurofighter GmbH since the mid-1990s. It was developed
More informationPreliminary Detailed Design Review
Preliminary Detailed Design Review Project Review Project Status Timekeeping and Setback Management Manufacturing techniques Drawing formats Design Features Phase Objectives Task Assignment Justification
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 informationA-VIATOR (AP68TP 600) Presentation
A-VIATOR (AP68TP 600) Presentation All reasonable care has been taken by VULCANAIR to ensure the accuracy of the information contained in the present document. However, the material presented is provided
More informationEjemplos de aeronaves existentes similares a las propuestas en los RFP 2007
Ejemplos de aeronaves existentes similares a las propuestas en los RFP 2007 UAV Sergio Esteban sesteban@us.es 1 Advanced Technologies and Engineering Co (Pty) Ltd (ATE). Vulture Production: Production
More informationDevelopment 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 informationInnovative Airship Solutions from Guardian Flight Systems
Innovative Airship Solutions from Guardian Flight Systems ITAR Disclaimer: This presentation does not contain Technical Data per 22 CFR 120.10 distribution unrestricted w/o 3282. Presentation Preview About
More informationRepublic 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 informationInternational Journal of Scientific & Engineering Research, Volume 4, Issue 7, July ISSN BY B.MADHAN KUMAR
International Journal of Scientific & Engineering Research, Volume 4, Issue 7, July-2013 485 FLYING HOVER BIKE, A SMALL AERIAL VEHICLE FOR COMMERCIAL OR. SURVEYING PURPOSES BY B.MADHAN KUMAR Department
More informationSR-71 PROPULSION SYSTEM P&W J58 ENGINE (JT11D-20) ONE OF THE BEST JET ENGINES EVER BUILT
SR-71 PROPULSION SYSTEM P&W J58 ENGINE (JT11D-20) PETER LAW ONE OF THE BEST JET ENGINES EVER BUILT Rolls-Royce Milestone Engines Merlin Conway W2B Welland Derwent Trent SR-71 GENERAL CHARACTERISTICS
More informationCONCEPTUAL DESIGN OF UTM 4-SEATER HELICOPTER. Mohd Shariff Ammoo 1 Mohd Idham Mohd Nayan 1 Mohd Nasir Hussain 2
CONCEPTUAL DESIGN OF UTM 4-SEATER HELICOPTER Mohd Shariff Ammoo 1 Mohd Idham Mohd Nayan 1 Mohd Nasir Hussain 2 1 Department of Aeronautics Faculty of Mechanical Engineering Universiti Teknologi Malaysia
More informationEurofighter -Typhoon Entwicklungsprogramm. Peter Huber Chief Engineer Typhoon CASSIDIAN AS
Eurofighter -Typhoon Entwicklungsprogramm Peter Huber Chief Engineer Typhoon CASSIDIAN AS Page 1 1 Content Initial Concept Studies Top-Level Operational Requirements International Cooperation Eurofighter
More informationSuper 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 informationDESIGN OF AN ARMAMENT WING FOR A LIGHT CATEGORY HELICOPTER
International Journal of Engineering Applied Sciences and Technology, 7 Published Online February-March 7 in IJEAST (http://www.ijeast.com) DESIGN OF AN ARMAMENT WING FOR A LIGHT CATEGORY HELICOPTER Miss.
More informationLip wing Lift at zero speed
Lip wing Lift at zero speed Dusan Stan, July 2014 http://hypertriangle.com/lipwing.php dusan.stan@hypertriangle.com HyperTriangle 2014 Lip_wing_Lift_at_zero_speed_R2.doc Page 1 of 7 1. Introduction There
More informationHigh Altitude Long Endurance UAV Configurations:
High Altitude Long Endurance UAV Configurations: Civil UAV APplications & Economic Effectivity of Potential CONfiguration Solutions Giulio ROMEO, Politecnico Di Torino (Turin Polytec. Univ.).), Dept. of
More informationChapter 10 Miscellaneous topics - 2 Lecture 39 Topics
Chapter 10 Miscellaneous topics - 2 Lecture 39 Topics 10.3 Presentation of results 10.3.1 Presentation of results of a student project 10.3.2 A typical brochure 10.3 Presentation of results At the end
More informationFacts, Fun and Fallacies about Fin-less Model Rocket Design
Facts, Fun and Fallacies about Fin-less Model Rocket Design Introduction Fin-less model rocket design has long been a subject of debate among rocketeers wishing to build and fly true scale models of space
More information