“Polymer Composites for Societal Applications” on mechanics... · Symmetric & Balanced Composite laminates Quasi-isotropic Laminate using Uni-directional ... Constant speed propeller

Dr. G N DayanandaChief Scientist & Head

Centre for Societal Missions & Special TechnologiesChairman, Societal Cluster

CSIR-National Aerospace Laboratories, Bengaluru-560017

“Polymer Composites for SocietalApplications”

School on Mechanics of Reinforced Polymer CompositesKnowledge Incubation for TEQIP, IIT-K, Jan. 22-25, 2017

Outline

• Societal Missions @ NAL

• HANSA

• Renewables - focus on wind

• Radomes

• Autoclaves

• Micro Air Vehicles

Contents are the Property of National Aerospace Laboratories, Bangalore

HANSASARAS

C-NM5LCA Tejas

Participation of CSIR-NAL inAircraft Programmes NALCSIR


CSIR NAL’s Aircrafts

Slybird

Hansa CNM – 5

Black KiteLCAContents are the Property of National Aerospace Laboratories, Bangalore

Societal Missions @ NAL


Centre for Societal Missions & SpecialTechnologies – Primarily Composites Research

Airborne Radomes Wind Turbine Ground Based Radomes

Autoclaves UAVs / MAVsImpregnation Machine


0°

90°

+45°

-45°

+45°

-45°

90°

0°

±45°

0°/90°

±45°

0°/90°

0°/90°

±45°

±45°

0°/90°

Symmetric & Balanced Composite laminates

Quasi-isotropic Laminateusing Uni-directionalLaminae

Quasi-isotropic Laminate usingBi-directional woven Laminae


Continuous Fibre Reinforced laminated Composites


Sandwich Composite Constructions

Foam Core Sandwich Honeycomb Core Sandwich

Face Sheet / Skin

CoreAdhesive Bond


Short Fibre

Discontinuous Reinforcements in Composites

Particulate


Hansa-3 Aircraft Program


Materials :• Epoxy Resin Systems• PVC Foam Cores• Glass Fabrics• Carbon Tapes

Processes :• RT Vacuum Bag Moulding• Carbon Tape Impregnation• Post Curing• Thermoforming• Adhesive Bonding

Material Characterisation :• Mechanical• Thermal• Hygrothermal• Design Data Generation

• NDT• Static Testing• Analysis• Flight Testing

QUALIFICATION/ CERTIFICATION

(JAR-VLA , AUW < 750Kgs.)

All Composite Aircraft - HANSA


LCRA (Feb. ‘87) HANSA-2 (Nov. ‘93)

HANSA-3 Proto-I (Nov. ‘96) HANSA-3 Proto-II (May ‘98)

LCRA to HANSA-3


First effort was to “WET” hands in building and flying aircraft LCRA built from plans and raw materials procured from USA First flight : February 1987 First hand experience with foam – fiber glass construction Flown for 259 hours Flying as UAV at ADE

Light Canard Research Aircraft (LCRA)


Set up Flight Experiments Division 11 June, 1988 to manage HANSA project Participation of many scientific divisions of NAL First flight of HANSA-2 : 23 November, 1993 LCRA technology was adopted Re-engined with a higher power engine - HANSA-2RE AUW was 868 kg 116 hours of flying Improvements required in fuselage shape & performance – HANSA - 3

Hansa-2


First flight of HANSA-3 prototype-1 : 25 November, 1996 Improved fuselage shape Airframe with sandwich construction technology Continental Engine with 125 HP AUW was 800 kg Improvement required in weight reduction - HANSA – 3 PT-2

Hansa-3 PT-1


First flight of HANSA-3 prototype-2 : May, 1998AUW achieved 750 kgRotax Engine with 100 HPAircraft was certified by DGCA on 1st Feb’2000Certified under JAR-VLA via FAR23 CategoryDay / Night VFR operations

Hansa-3 PT-2


Fibre glass composite structureRotax 914 F3 turbo-charged engine

100 BHP continuous115 BHP max.

Constant speed propeller

Certified under JAR-VLA forday / night VFR operationsLightning protected

PerformanceStall speed with flaps : 48 KIASMax. cruise speed : 115 KTASMax R/C : 650 ft / min.Endurance : 4 hTake-off distance : 450 mLanding distance : 600 m

Specifications of Hansa-3


Side by side seating, neat cockpit,very good visibility

Conventional instruments &modern Nav-Com units

Dual flight controls with excellentcontrol harmony

Turbo-charged engine withconstant speed propeller

COCKPIT

Rotax 914 F3 engine

Features of Hansa-3


Extensively tested and documented (for its class)

Fuselage test rig

Engine mount test rig

Wing test rig

Features of Hansa-3 Continued..


Innovative vacuum bag moldingtechnique process for fabricationof airframe

Maintenance and repair of glassfiber composite structure

Design of composite aircraftstructures & integration of smallaircraft

Lightning protection scheme

Structural testing of components

Type certification for civil use

Technologies Developed


Hansa-3 Fabrication in a Nut ShellNALCSIR


Renewables - focus on wind


Present

Antarctica Past

Recent Past

300 kWWTS

500 kWWTS

Kethanur,TNKethanur

Kanyakumari, TN

WindResource

Assessment

A Legacy in Renewable Energy

Kethanur, TN


The Trade Winds:

Steady northeast/southwest

winds between equator and

horse latitudes.

EQUATOR

30°N

60°N

30°S

60°S

Some weather(wind) characteristics of atmosphere

Wind Patterns differfrom one continentto the other.

Vast differences :American/European toIndian sub-continent.

WITHOUTCORIOLIS EFFECT

WITHCORIOLIS EFFECT

Easterlies

Westerlies

NortheastTrades

SoutheastTrades

Doldrums

Westerlies

Easterlies


Major Surface weather characteristicsP Cell

F Cell

H Cell

L L L L L

H H H H

H H H H

H

H

EquatorITC

Trade Winds

Subtropical HighPressure Belt

Prevailing WesterliesPolar Front

Polar Westerlies


Small Wind Solar Hybrids at

Center for Societal Missions & SpecialTechnologies- CSMST

National Aerospace Lab, Bengaluru

Wind-Solar Hybrid (WiSH) System PT1

Targeted for low wind regimes in tropics

28

NALCSIR


29

NALCSIR

Wind-Solar Hybrid (WiSH) System PT2


Composites

RenewableEnergy

Controls

Aerodynamics

Indigenous Wind Turbine Rotor


500 kW2

3

1

421 VC

PD

overallP

50 kW

5 kW

Roto

r Dia

met

er, m

NAL’s Small Wind turbine Rotor Systems

NAL’s Effort

0.5 kW

North America& Europe

Design Wind Speed ~ 2 X Annual Average Wind Speeds(Source : Large Wind Turbines, Eric Hau)

10000

1000

100

10

1

0.1 0 2 4 6 8 10 12 14 16Design Wind Speed, m/s


Fundamental Equation of Wind PowerWind Power depends on air:• Volume• Velocity• Density

Kinetic Energy definition:• KE = ½ * m * v2

Power is KE per unit time:• P = ½ * m. * v2

Mass flow rate• dm/dt = A * v

• Power ~ cube of velocity• Power ~ air density• Power ~ rotor swept area A = r2

• P = ½ * A * v3

m = dm/dt mass flux

V

A


Design Methodology for NALWIN

Aerodynamic analysisby GH-Bladed

Wind TurbineConfiguration, Airfoil

selection, AerodynamicDesign for operating

conditions

Load Matchingusing different

methods

TowTesting

FieldTesting

Systemperformance

studies

Fabrication and off-line structural testing

Quantification ofMass & stiffness

properties of blades

Structuralanalysis using

NASTRAN for thestress & stiffness

based design

Aeroelastic analysisusing GH – Bladed

NALWIN


Aerodynamic Design & Analysis

Twist Distribution

Analysis by GH-Bladed CAD Model of the blade

Chord Distribution

Twist

Chor

d

Radius RadiusContents are the Property of National Aerospace Laboratories, Bangalore

Structural Design and Analysis

CFRP Structural Design and Analysis of the blade using Hypermesh –NASTRAN

Moulds

FE Model

Blade c/s and composite layupscheme

Blade Fabrication Scheme

Stress Distribution


Composite Blade ManufacturingTechnology

Tooling Development• NC machined Master

• Carbon composite (CFRP) Blade fabrication• Novel light weight coreless carbon composite blade

•Room temp. vacuum bag moulding process• Weight of the blade ~950 gms

• Split composite mould


Static Deflection Testing of Blade& Dynamic Balancing of Rotor

Dynamic Balancing of RotorStatic Deflection Testing of BladeContents are the Property of National Aerospace Laboratories, Bangalore

Tow Testing at HAL Airport, Bengaluru

Simulate

Wind speeds

up to 20 m/s


Tow-Testing of Wind Turbine


Unique features of NALWIN

Indigenously developed rotor blade system

Furling for overspeed protection.

Eco-friendlier composite CFRP rotor blade system

Suitable for Indian low wind speed regimes.


Development of 1 kW Wind SolarHybrid (WiSH) system


System Configuration

InverterBatteriesDump Load

AC Load

Solarcharge

controller

WindTurbine

controller

NALWIN Solar PVPanels

CSIR-NAL

CSIR


WiSH System Specification

Type : Horizontal AxisNo. of blades : 3 Nos. / 4 Nos.Blade material : CFRPRated Power : ~ 1000W @ 12 m/sOperating wind speed : 3 – 18 m/sRotor diameter : 2.05 mDirectional control : Tail vaneOverspeed protection : Furling & Dump loadGenerator : Multi-pole Permanent

MagnetDrive train : Direct driveTower : Guyed tilt down typeTower height : > 20m (site specific)

Integrated with 500 W Solar PV Panels


As a Roof Top Application

Wind Turbine

Solar PV Panel


Field trials of Wind Solar Hybrid systems atRenewable Energy Park , NAL

Wind Turbine

Solar Panel

Wind Turbine

Solar Panel

Smart Structures BuildingCSIR-NAL

Field trials at NAL Campus, Kodihalli,Bengaluru


Press Release on WiSH System

The New Indian Express,May 16, 2014

The Hindu, May 24, 2014

46

NALCSIR


NAL-Win @Jyoti Nivas CollegeKoramangala Bengaluru

Wind Turbine :- 900 WDate of Installation :- 26-05-2016


NAL-Win @ Vivekananda Institute of TechnologyKumbalagudu- Bengaluru

Wind Turbine :- 900 WSolar :- 500 WDate of Installation :- 17-09-2016


Networking with Private Players

AerodynamicDesign

MechanicalDesign

CompositeProcess Electrical &

Electronics

Battery(COTS)

Wind Turbine Rotor

Charge Controllercum Inverter

Outdoor Kiosk

Solar PV Panels

JMJ SwitchGears

ARES

49

NAL


Summary Solar/Wind energy programs should not be pursued

in isolation or indiscriminately.

A holistic approach to energy needs taking intoaccount all available regional resources is the need ofthe hour.

Integration of renewable energy to grid is a challengeand must be properly addressed.

Storage of energy is an area that needs to bedeveloped.

Promoting indigenous technology and associatedeco-system is the key to growth.


Renewable Energy Initiative for EducationalInstitutions

A 1 kW class NALWIN wind turbine system is installed at Jyothi NivasCollege, Kormangala, Bengaluru. Another 1 kW class WiSH system is installed at Vivekanada Institute ofTechnology, Bengaluru. 4 Nos. of WiSH system are under installation at CSIR-IMMT,Bhubaneswar under the CSIR 800 Banner Program.

NALWIN Wind Turbine atJyothi Nivas College

NALCSIRWiSH System at

VKIT


South West Monsoon Winds


Largest IndigenousWind Turbine

300 kW Wind Turbine(2004)

100 W Savonius WindTurbine, Antarctica (2000)Water Pumper

WP – 2 WindTurbine (1959 – 64)

Sail Wind Mill(1975)

300 W 3- bladedaero-generator (1993)

2 kW 3- bladedSAMIRA Wind

turbine (1987-89)

A legacy ofexperience inR&D of WindTurbines since

1959

500 kW WindTurbine (2008)

History of NAL’s wind turbine activity


55

Wind ResourceAssessment

500 kWWTS

600 +400 WWindSolar

HybridSystem

Wind Turbine Development

300 kWWTS

Wind Solar HybridSystem

CSIR-NAL's mission – To translate aerospacetechnologies for societal applications


Portable wind batterycharger-Sankalp – remote field

Antarctica- 36 W. 56

CSIR-NAL’s Wind Energy Activities at Antarctica

• Exploitation of wind energy• Power supply to the communication

repeater station & for remote fieldexperiments

NAL’s Savonious Wind battery charger atVittaiah peak, Maitri, Antarctica – 75 W


Radomes


Airborne Radomes

Jaguar Nose Radomes (11 Nos.) for HAL/Indian Air Force (IAF)

Material system: E-glass BD fabric & elevated temp. epoxy matrix

Manufacturing Technology: Contoured fabric preforms & closedmould

pressure assisted Resin InjectionTechnology

(RTM)

Current Status: Transfer of Technology (ToT) to HAL completed formanufacture of 60-70 Nos. of radomes

JAGUAR Nose RadomeNALCSIR


Material : Composite(E-GlassFabric & HighTemp. EpoxyResin)

Shape : StreamlinedType : MonolithicLength : 965.50 mmBase dia.(OD): 522.61 mmWeight : 13.5 kgs.

Jaguar Radome SpecificationsNALCSIR


Conical Preforms for Air-Borne Radomes(Contour varying in 3-Dimensions)

Fighter AircraftJacquard wovenconical seamless

preform(Varying contourfrom base to tip)


Static Load Test Vibration Test

Lightning Test

Testing of Jaguar Radome

EM Test

NALCSIR


Material system: E-glass BD fabric & RT epoxy matrixManufacturing Technology: Honeycomb core sandwichconstruction with RT vacuum bag moulding technologyWeight : 3.5 Kgs.End use: CSIR-NAL’s SARAS prototype

Nose Radome for CSIR-NAL built 14 seater civilian aircraft

SARAS Nose RadomeNALCSIR


• Composite components made from prepregs and Autoclave moulding• Over 30% composite in Air Frame• Use of UD carbon Prepregs

Reinforcements in SARAS AircraftNALCSIR


Total Direction Finder Radome for TU-142M Aircraft

Total Direction Finder Radome - TU142Aircraft

Material system: Quartz BD fabric & high temp. epoxy matrixManufacturing Technology: Contoured fabric preforms and closedmould pressure assisted resin injection technology (RTM)Weight : 95 gms.Supplied : 16 nos.End use: DRDO/ IAF

NALCSIR


Ground based RadomesPrinciple of construction is based on Platonic Solids

TruncatedIcosahedron

Dodecahedron

Soccer Ball

DWR

X-Band

(GoldbergPolyhedron)

12 Pentagons+ 20 Hexagons

12 Pentagons

NALCSIREuler char. formula for Polyhedra = V(60) - E (90) + F(32) = 2

Euler char. formula for Polyhedra = V(20) - E (30) + F(12) = 2


Trial Assembly At BEL,Bangalore

66 Panels, 3700 fasteners

NALCSIR


Mark-I (146 panels)

Material system: E-glass BD fabric and RT cured epoxy matrix

Manufacturing Technology: PU Foam core sandwich construction with RTVBM

End use: Indian Meteorological Department (IMD) /ISRO

Current Status: ToT to BEL completed for manufacture of 30 Nos. of radomes

Installed at Bhuj, Gujarat

Mark-II (66 panels)NALCSIR

13 m Dia DWR Mark-II Radome

Installed at Satish Dhawan SpaceCentre, SHAR – ISRO, Sriharikota


Mark-I (146 panels)


Manufacturing Technology: PU Foam core sandwich construction with RTVBM

End use: Indian Meteorological Department (IMD) /ISRO

Current Status: ToT to BEL completed for manufacture of 30 Nos. of radomes

Installed at Bhuj, Gujarat

Mark-II (66 panels)NALCSIR

13 m Dia DWR Mark-II Radome

Installed at Satish Dhawan SpaceCentre, SHAR – ISRO, Sriharikota


1. BEL, Bangalore 2. Bhuj, Gujarat 3. Cherrapunji, Meghalaya, NE

4. SHAR, Sriharikota 5. Odisha 6. Port Blair

6

13 m Dia DWR Mark-II RadomeNALCSIR

SPECIFICATIONS

1. Dia. : ~13 m

2. Surface Area : 514 m2

3. Operating frequency : 2.7 - 2.9 GHz

4. Design wind speed :250 – 300 kmph5. Construction : Sandwich Composite

Panel1

5

Installed

2

To be Installed

4

6


13m Doppler Weather Radome TOTto BEL, Navi Mumbai

• Hands on training to BEL team onprocessing of composite panels atNAL

.• Shipped all tooling, moulds, fixtures.

• Assisted in setting up facility &initial trial runs.

Inauguration of the facilityon 1st Nov. 2013

CherrapunjiNALCSIR



Fabrication Methodology: PU Foam core sandwich construction with RTVacuum bag moulding technology

Total Number of Panels: 11 nos.

Installation location: NARL, Tirupati.

4.2 m dia X-Band RadomeNALCSIR


Customised Narrow width fabric in Radome panels

4.2 m Diameter X- Band Radome

Housings for WeatherRadars

Radome Panel

NALCSIR


Autoclaves


Cooking anAircraft Airframe? NALCSIR


CSIR-NAL embarked on the development of autoclaves(when they were in the embargo list) in the earlyeighties to meet the requirements of indigenization ofmilitary and civil aircraft programs.

• First indigenous autoclave commissioned in 1986

• First state of the art computer controlled indigenousautoclave commissioned in 1994

• Largest aerospace autoclave in the countrycommissioned in 2009

Aerospace Autoclave Dev. Initiation at NALNALCSIR


CSIR-NAL embarked on the development of autoclaves(when they were in the embargo list) in the earlyeighties to meet the requirements of indigenization ofmilitary and civil aircraft programs.

• First indigenous autoclave commissioned in 1986

• First state of the art computer controlled indigenousautoclave commissioned in 1994

• Largest aerospace autoclave in the countrycommissioned in 2009

Aerospace Autoclave Dev. Initiation at NALNALCSIR


• High-performance, advanced prepreg polymericcomposite aircraft structural components

• Large and complex shapes that meet thestringent weight and quality requirements

• Obtaining high degree of reliability and consistencyin composite products

Investments in autoclaves are considered to bestrategically important in the aerospace industry

Autoclave Processing/ Manufacture for:

The challenge is to develop robust, ruggedindigenous autoclave technologies (that can safelyand reliably process prepreg based expensivepolymeric composites) with wide vendor base andsuit Indian conditions.

NALCSIR


Autoclave Design - Drivers

• High reliability

• Space Optimization

• Fail-Safe operation

• Safety of Charge & Personnel

• Power failure management

• Modularity

• Upgradability

• Ease of Maintenance

NALCSIR


Range of Autoclave Process Parametersat CSIR - NAL

Sl.No.

Parameter Range Can Cater to

1. Temperature 25 - 350°CPrimary load structuresof military and civilaircraft, Hightemperature enginerelated components,Satellite structures,Leading edges of spaceshuttles,rockets etc.,

2. Pressure 1 - 15 bar

3. Length 1- 9 m

4. Diameter 0.6 - 4.5 m

5. Volume 0.2 - 140 m3

On an average over 200 cures/year performed at NAL

NALCSIR


Typical Autoclave cure cycleNALCSIR


82

a = MOULD b = RELEASE AGENT APPLIED TO MOULDc = LAY UP d = BLEEDER e = BREATHERf = POROUS RELEASE FILM g = PRESSURE PADh = BAG

Typical Autoclave Molding BaggingScheme NALCSIR


Industrial Grade, High Temperature and HighPressure Indigenous Autoclaves

Mark IMark II

Mark IV

Mark III Mark 0

NALCSIR


N2 Gen.plant

Eco-system development- Autoclaves

PressurisedBlower motor,Asian – B’lore

ReservoirsPioneer,Meerut

CoolingPaharpur

Vacuum- Indfos

Indcon andVayutech, Delhi

Autoclave shell, H.E.- UCE,Mumbai

Heaters- Escorts,Faridabad

Control valves – L&TChennai

Electrical Control & Inst. SystemDATASOL, Bangalore

NALCSIR


85

Three tier layout ofSubsystems NALCSIR


Innovative Features

HeaterDistribution

•Fool Proof door safety device•Quick Lock Rotating Door•Optimized Door Handling Scheme•Variable Area Heat Exchanger•Evolved Forced Circulation System•Pressurized Blower Motor•Auto, Semi-Auto & Manual mode• Accurate temp. cont. ± 1°C• Temp. uniformity ± 2°C• Open Control Architecture• Fail Safe & Fault Tolerant

Fool proof door locksafety device

Four bar steering mech.-Optimized Door Movement

Variable AreaHeat Exchangerat rear end

NALCSIR


Using Visual studio that supports high levelprogramming such as OPC (Object linking and enablingfor Process Control), MODBUS driver, multi threading,socket programming & low level programminginstructions. Interface with number of process instruments (7nos)

through ‘virtual com’ ports in the computer Main and Hot standby computer architecture PLC software to cater for a novel Heater Power Steering

Logic, pressure sensitive variable speed blower, safetyrequirements, sequential and automatic starting andshutdown control, interlocks etc

In-house Software for Autoclave Cure ControlNALCSIR


6Orders completed5 Orders under execution

Enquiries from Strategic sectorEnquiries from Societal sector

MIT

VSSC

HAL,ADE,ISAC

ASL

DMRL

IITK

DMSRDEMKU

Godrej

OF

Autoclave OrdersExecuted, ongoing

&Bids submitted

IITKharagpur.

6 orders won againstInternational

Bidding

Revenue generatedby PPP

about 31 croresof rupees

RPP

IIT B

IIT Guwahati


3D- Model of Lab scaleAutoclave

3D- Model of Lab scaleAutoclave

900mm dia& 1000mmworking length, 210DegC,7 Barg


Lab Scale Autoclave for IIT Kanpur

Successfully commissioned and handed overon 25.03.14

NALCSIR


Lab scale autoclave for MIT, Manipal, Mangalore

Successfully commissioned andhanded over on 26.08.14

NALCSIR


Longest Autoclave – 3D Model4m dia., 15m length, 10 bar

Mandrel -15 Tons

Crab

Unique Mandrel rotating mechanism

Trolley

NALCSIR


Autoclave Shell Fabrication in progressat UCE, Mumbai

4m Dia x15 m LengthLongest Autoclave in Indian Aerospace Sector

NALCSIR


Longest Autoclave designed and Developed byNAL

• Optimised flange design using FEA•Unique Mandrel rotating mechanism,•Hydrotest @ 20 barg with strain monitoring


Upgradation of Vertical Autoclave forVSSC, Comp. Mfr. Divn., Vattiyoorkavu

Top half of autoclave shell

CONTROLPANEL

Supply and warrantycompleted on 27.04.2014

Specifications:Working Dia. : 4mWorking Height :1.5mMax. Pressure : 7 bargMax. Temp : 200º C

NALCSIR


Autoclave User’s Meet, 3rd Sept. 2013NALCSIR


Press Coverage: On Lab scale autoclaveVijay Karnataka

NALCSIR


NAL’s Microwave Hybridized Autoclave

• Working Dimensions:Ø0.8m X 1.5m lengthTemp: 425 Deg CPres : 15 Barg

• Autoclave shell designedwith multiple Microwaveports and rotating platform.

• Fabrication is in progress.

Study of EM field & temperaturedistribution for Autoclave

ambients.

Microwave ports

Rotating platform

Significant EnergySavings Likely

NALCSIR


Desk top Autoclave forcomposites processing

• Compact, affordableautoclave for

educational& Research Institutions

• Fits in a space of 1.5cubic metre

• Working temperature :200 Deg C

• Working pressure : 7barg

• Works on single phase ,32 A power source


Micro Air Vehicles


Lightweight MAV Airframes; How ‘light’ can itbe?

MaterialDensity(kg/m3) Weight

(grams)

Air 1.2 10Solimide® 6.3 46Rohacell® 32 245PU foam 42 322

Skin StiffenerConst. - 1600

Approx. VolumeOf 1.6 m wing spanSlybird : 0.00768m3

Building an MAVusing only airmolecules !!!

Air Molecules


Micro Air Vehicles @ NAL

Sl.No. MAV Wing span

class (mm)Weight(gms.)

AirframeWeight

Endurance(min.)

A. Microbeacon 150 120 15 15B. Black Kite 300 292 50 35C. Pushpak 450 730 280 45D. Suchan 1600 3600 1800 55-75

A B C D

1600

mm

From the NAL MAV Stables


Structural Concepts for Airframes…Contd

Black Kite Pushpak

Suchan


Suchan 1.6 m MAV

Wing span : 1.6mLength : 1.3mWeight : 3.6 kgs (str. wt: 1.8 kgs.)Endurance : 45-60 minutes

NALCSIR


Features Modular construction Light weight Materials design

Crashworthy features Snapping longerons in

fuselage By design

Mounting for electronicsCOTS items

Stiff CFRP Wing-Fuselage Interface

Fuselage Trolley

‘Suchan’ 1.6 m MAVNALCSIR


Modular wing of MAV-Exploded view

CSIR-NALCSIR

• Completed more than 100 landingsContents are the Property of National Aerospace Laboratories, Bangalore

MAV - Pushpak

Wing span : 450 mmLength : 550 mmWeight : 730gms. (str. wt: 300 gms.)Endurance : 40 min

NALCSIR


MAV - Micro Beacon

Wing span : 150 mmLength : 160 mmWeight : 145 gms (str. wt: 25 gms.)Endurance : ~30 min

NALCSIR


Before droop After droop

Lateraldroop line

Inclineddroop lineLE droop (morphing) of black kite MAV

Morphing 300mm Black Kite MAVNALCSIR


110

Acknowledgements

1. Sri J J Jadhav, Director, CSIR – NAL

2. Director General, CSIR

3. Team CSMST @ CSIR – NAL

4. Team C-CADD

5. Team ACD

6. Dr. U N Sinha.

7. Flosolver Team, NAL

Thank You

Documents

“Polymer Composites for Societal Applications” on mechanics... · Symmetric & Balanced Composite laminates Quasi-isotropic Laminate using Uni-directional ... Constant speed propeller