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MA-4878 Unmanned Aerial Vehicles Capsule-1

Course Layout

MA4878 Unmanned Aerial Vehicles

Dr. Rajkumar S. Pant Dr. Lou Kok Yong

Visiting Professor Adj. Asst. Prof.

MAE @NTU


COURSE DESCRIPTION

Lectures: 26 hours

Lab/project: 39 hours

Pre-requisites:

MA3701 Aerodynamics

MA3703 Flight Dynamics


ObjectivesThis course aims to provide the students with the knowledge ondesign aspects of Unmanned Aerial Vehicles (UAV) in terms ofconsideration of UAV subsystems, such as Aerodynamics,Payloads, Sensors, Flight control systems, and Propulsion. The

whole UAV system integration issues will also be covered Outcomes1. Understand the components building up to a UAV system

2. Understand functionalities of various UAV subsystems

3. Appreciate UAV design considerations based on missionrequirements

4. Appreciate integration challenges of various UAV subsystems

Course Objectives & Outcomes


Breakdown of Lectures

Dr. Rajkumar Pant

11th Jan to 22nd Feb

TITLE HRS

Introduction 1

Overview of UAV Systems 3

Aerodynamics Considerations 4

Propulsion 2

Performance 3

TOTAL 13

Dr. Lou Kok Yong

7th Mar to 18th Apr

TITLE HRS

Flight Modeling & Simulations 3

Flight Control Systems. 3

Payload and Sensors 3

Other UAV Types 4

TOTAL 13


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Five Capsules

Introduction (1)Definition of UAV Systems. Historical overview. Scope and coverage

Overview of UAV Systems (3)Aerial vehicles. Mission planning. Launch and recovery. Payloads and sensors.Data links. Ground support equipment. Classes of UAV systems.

Aerodynamics Considerations (4)Review of aerodynamics. Aerodynamic considerations for various UAV types.Determination of aerodynamic parameters for analysis

Propulsion (2)

Propulsion Systems for UAV. IC engines. Gas turbines. Other propulsivetechniques: e.g. flapping wings.

Performance (3)Performance measures for various UAV. Flight performance considerations:speed, range, endurance, maneuverability. Launch and recovery performance.Unconventional maneuvers


Evaluation Scheme

Continuous Assessment: 50%

Dr. Rajkumar Pant 25%

o Project based submissions

Dr. Lou Kok Yong 25%

Final Examination: 50%

Closed Book examination

Duration 2 hours


Course and Reference Books

Textbook

P. Fahlstrom, T. Gleason,Introduction to UAV Systems,2nd edition, UAV SystemsInc., Columbia, MD, USA,2005.

References

P. Castillo et al., Modellingand Control of Mini-FlyingMachines, Springer-Verlag,2005.

T. Mueller et al., Introductionto the Design of Fixed-WingMicro Air Vehicles, AIAAEducation Series, 2007.


Course Material on NTU Learn

Most communication by e-mail

Hand Phones to be switched off (not mute)

Or else I get to answer !

Questions and Interruptions Welcome !

Course Policies


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[email protected]

Office : N3.2-02-45

Phone: 67906891

Meetings mostly by prior appointments

Open Door policy for quick doubts

My Contact Details


MY BACKGROUND

Who am I ??


Academic

Three degrees in Aeronautical Engineering

Bachelors

oPunjab Engineering College Chandigarh, India, 1979-83

Masterso Indian Institute of Technology Madras, India, 1984-86

oSponsored by Hindustan Aeronautics Limited

Doctoral

oCollege of Aeronautics, Cranfield University, UK, 1993-97

oCommonwealth Scholarship Commission in UK


Work Experience

Five years industrial experience

Hindustan Aeronautics Limited, Kanpur (1984-88)

oDo-228 and HS-748 structural modifications

Hindustan Aeronautics Limited, Nashik (1988-89)

oMiG 27-M and -21 Aerodynamics & Flight Testing

~25 years teaching & research @ IIT Bombay

Lecturer (1989-90)

Asst. Prof. (1990-01)

Associate Prof. (2001-12)

Prof. (2012 )


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Aircraft I have mainly worked on


Other aircraft I worked on


Aircraft I have flown (in the cockpit !)


UNMANNED AERIAL VEHICLES

My Research Portfolio


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Overview

Technical vetting of Vihang Netra Mk-I

Design of a Snow UAV

Multicriteria Optimization of Snow UAV

Conceptual Design of Vihang Netra Mk-II

Conceptual Design of Hand Launched UAV

Aerodynamic Analysis of Flapping Wing UAV


TECHNICAL VETTING OF DESIGN

VIHANG Netra Mk-1 UAV for SASE


VIHANG NETRA Mk-I

Short Range Unmanned Surveillance System

Key Specifications

Range 30 Km

Endurance 2 hours

Payload 25 Kg

Max Altitude 15000 feet (above MSL)


Vihang Netra-Mk-1


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Trials at Gliding Center, Pune



monstration Flight


Trials at Bhuntar Airfield in Kulu


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MA-4878 Unmanned Aerial Vehicles Capsule-1 MA-4878 Unmanned Aerial Vehicles Capsule-1

Landing at Helipad


VIHANGA NETRA HIGH ALTITUDE TRIALS


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Trials with standing snow


High Altitude Trials at Sissu


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DESIGN OF UAV FOR SASE

Case Study-II


Specified Requirements


Critical Requirements

Take off and Landing within 100m @ 12000ft

Maximum altitude of 18000 ft

Sustaining cross winds of 28 kmph

Wide temperature range of operation i.e.

from -300C to 500C


Tools used

RDS-Professional

Advanced Aircraft

Analysis


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CONFIGURATIONS INVESTIGATED

DRAGONFLY SPARROW SHADOW-600

VULTURE SENTRY BLUE HORIZON


Snow U V


Multicriteria Optimization ofSNOWUAV

Dinesh Kumar

M. Tech. Project: 2009-10

Dineshkumar, M. and Pant, R. S., Conceptual Sizing and Multicriteria

Optimization of UAV for Snow Studies, Journal of Aerospace Sciences and

Technologies, Aeronautical Society of India, August 2013.


Aim and ScopeAim

Conceptual sizing of a UAV

For snow studies in lower Himalayas

To set up a multi-objective optimization problem

Scope

Development of a methodology for UAV sizing

Optimize and compare results from different optimizers

Multi-objective optimization

Identification of conflicting objectives

Obtain Pareto front for the conflicting objectives


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Mission Specification

CLIMB

INITIALALTITUDE=100m

FINALALTITUDE = 3000m

MACHNO.= 0.5

CRUISE

ALTITUDE = 3000m

DISTANCE= 92.6km

MACH NUMBER= 0.6

LOITER

ALTITUDE = 3000m

DURATION= 30min

MACH NUMBER= 0.5

DASH

ALTITUDE = 3000m

DURATION= 5 min

MACH NUMBER= 0.8

MANEUVERALTITUDE = 2000m

NO. OFTURNS= 2

MACH NUMBER= 0.5

CRUISEALTITUDE = 2000m

DISTANCE= 92.6km

MACH NUMBER= 0.6


Assumptions

Baseline Configuration of VN-Mk II

Sharma, S.C., Feasibility Study for the design and Development of an Unmanned Aerial Vehicle

for the Evaluation of Snow Cover, Punjab Engineering College, Chandigarh, 2007


Optimization

READ

POPULATION SIZE = NPNUMBRE OF GENERATION = NGSTRING LENGTH = LSCROSSOVER PROBABILITY=PCMUTATION PROBABILITY = PMINITIAL SEED = IS

INITIALIZE

POPULATION

GEN=1

FITNESS EVALUATION

REPRODUCTION

CROSSOVER

MUTATION

GEN=

NG

STOP

GEN=GEN+1

READ DESIGN VARIABLES

AND CONSTRAINTS

GEOMETRY

MASS

ESTIMATION

PACKAGING

CALCULATION

MISSION

PROFILE

ENGINE

DATA

AERODYNAMICS

PERFORMANCE

CALCULATION

OBJECTIVE FUNCTION

AND PENELTY

ESTIMATION

GENETIC ALGORITHM UAV DESIGN ALGORITHM


Design Variable Lower Limit Upper Limit

1 Aspect Ratio 6 10

2 Wing Span (m) 4 10

3 Wing t/c 10 20

4 Wing Setting Angle (deg) 0 5

5 Flap Area Percent 0.0 0.25

6 Propeller Radius (m) 0.2 0.8

7 Fuel Mass (kg) 1 8

8 Vehicle Length (m) 3 6

9 Design Mass (kg) 70 120

10 Air Brake CD0

0.5 1.98

Inputs

..ContinuedDesign Variables

Three Engine options available

Engine

Power

(kW)

Mass

(kg)

Length

(m)

Width

(m)

Height

(m)

LIMBACH L 275 E 15 7.8 0.4 0.26 0.26

Simonini Flying MINI 2 PLUS 19 18.3 0.25 0.26 0.45

UAV Engines AR 741 28 16 0.4 0.26 0.26


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Computed Constraint Type Reference

1 Mission fuel +reserve = Fuel Mass

2 Total Mass Computed = Total Mass

3 Takeoff Distance < 100 m

4 Landing Distance < 100 m

5 Wing Location + Wing Chord < Fuselage Length

6 Propeller Tip Mach number < 0.8

7 Stall Speed 1.5 < Design Speed

Constraints


Multicriteria Optimization


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Multi-objective Optimization

Identification of Conflicting Objectives


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Pareto Front

6.5

7.0

7.5

8.0

8.5

6.0 6.5 7.0 7.5 8.0 8.5 9.0 9.5

Stall Speed (m/s)

WingSpan(m)

1

23

45

6

7


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1 2 3 4 5 6 7

Aspect Ratio 7.26 6.31 6.0

Wing Span (m) 7.12 7.21 7.26 8.02 8.06 8.35 8.39

Wing t/c 15.48 18.71 20 17.42 17.42

Wing Setting Angle (deg) 0.48 0.0 0.48 0.32 1.13 0.32

Flap Area Fraction 0.25

Propeller Radius (m) 0.32 0.41 0.34

Fuel Mass (kg) 1.56 2.22 2.11 1.89

Vehicle Length (m) 3 5.67 3.29

Design Mass (kg) 70 88.82 95.1

AirBrake CD0 1.49 1.59 1.19 0.89 1.98

Engine L 275E

Objective Functions

Stall Speed (m/s) 7.43 7.01 6.92 6.76 6.55 6.5 6.46

Wing Span (m) 7.12 7.21 7.26 8.02 8.06 8.35 8.39

Design Variables of Pareto Front


501

2

3

45

6

7

0.0

0.2

0.4

0.6

0.8

1.0

Design Variables Pareto Front


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Observations

Multi Objective Optimization

Seven non-dominating objectives obtained

Minimum stall speed 6.46 m/s @ wing span of 8.39 m

Minimum wing span 7.12 m @ stall speed of 7.43 m/s

LIMBACH 275 E powerplant is selected in all the cases

Maximum flap fraction of 0.25 is selected in all the cases


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Summary & Conclusions

Dedicated methodology for conceptual

sizing and optimization for one-class of

UAVs developed

Multi-criteria Optimization Evolutionary optimization Algorithm can find full Pareto front

Seven Pareto designs obtained offers various possibilities in the design


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HAUSS PROJECT

Visiting Faculty @ Dept. of AOE, Virginia Tech, 2010-11


Team Members:

Jason Berti Anish Bhatt

Donald Brooks Michael Hazuda

David Rigotti Sumeet SinghAnthony Swago Andrew WangSupervisor:

Prof. Rajkumar S. Pant


Introducing

The NEW



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Conceptual Design Study of aHand Launched UAV

M. Naveesh ReddyUndergraduate Project

2011-12

Reddy, N., Pant, R., Conceptual Design Study of a Hand Launch UAV,

Paper AIAA-2013-4423, Proceedings of AVIATION 2013, Los Angeles,

USA, 12-14 August 2013MA-4878 Unmanned Aerial Vehicles Capsule-1

Desired Features

Light weight, hand launched and belly landing

Undetectable, low observability

Loiter optimization

Portability

No special piloting skills

Reliable


Specific Requirements

All up Weight 7 kg

Endurance : 3 hours

Loiter speed : 12 m/s - 25 m/s

Range: 30 km


Existing HaL-UAVs

Specifications

UAV

Wing

span

(m)

Length

(m)

Gross

Weight

(kg)

Range

(km)

Endurance

(min)

Velocity

(km/h)

Operational

Altitude

(m)

AeroVironment Pointer 2.74 1.83 4.5 5 60 80

(max)

Upto 300

AGL

AeroVironment Raven 1.4 0.9 1.9 10 6090 32-81 152 AGL

AeroVironment PUMA 2.8 1.4 5.9 15 120 37-83 152 AGL

AeroVironment Dragon Eye 1.1 0.9 2.7 5 45-60 35-65 300 AGL

Skylark 1 LE 2.9 2.2 6.1 15 180 37-74 -273 to 914

from take off

METU Guventurk 2.2 1.35 4.5 10 90 33-85 300 AGL

Bayraktar 1.6 1.2 4 15 60 95 (max) Upto 900

AGL

Desert Hawk 1.37 0.91 4 15 90 30 -80 150 AGL


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Baseline UAV

Skylark 1 LE

Belly landing with inflated

cushion

Composite Structure

STAMP

Stabilized Miniature Payload

Daylight, night, uncooled

thermal and HD


Propulsion System

Battery pack, propeller, motor and speed controller

Type Advantage Disadvantage Voltage Energy Density

(W-hr/kg)

NiCd Cheapest, Fast charging, not very

sensitive to overcharging,

Heavy, memory

problem, low

capacity,

1.2 40-80

NiMH No memory problems, Medium

cost,

Heavy, sensitive to

overcharging

1.2 60-100

LiPo Light weight, Highest capacity

and no memory problems, 3.7

volts/cell

Expensive, needs

special charger, Risk

of explosion

3.7 130 +

Li ion No memory effect, high energy

density

Risk of explosion 3.6 100-160


Airfoil Selection

Fx 63137

S1223MA-4878 Unmanned Aerial Vehicles Capsule-1

Comparison :S1223 v/s FX 63137


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Constraint Analysis

Design Point (Hp/W , W/S) = (0.013 hp/N, 58.32 N/m2)MA-4878 Unmanned Aerial Vehicles Capsule-1

Refined sizing

6


Design Layout


Sensitivity to Weight

5

5.5

6

6.5

7

150 160 170 180 190 200 210GrossWeight(kgs)

Endurance (minutes)

Endurance

5

5.5

6

6.5

7

27 28 29 30 31 32 33

GrossWeight(kgs)

Range (kms)

Range

4

5

6

7

8

16 17 18 19 20GrossWeight(kg)

Velocity (m/s)

Max. Velocity


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Thanks for your attention !

Open for queries

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