Uas-15008-a-slides for PDR

MACH.E.T.E.PRELIMINARY DESIGN REVIEW (PDR)ANTONIO ARGUEDASMATÍAS GODOYPAULA SÁNCHEZMIKEL ZUBIETA

UNMANNED AERIAL SYSTEMS MASTER 2015 – GROUP 4

UNMANNED AERIAL SYSTEMS MASTER 2015 – GROUP 4 PRELIMINARY DESIGN REVIEW - PDR PAGE 2

GENERALITIES

01.- UAS AIM & USES

UNMANNED AERIAL SYSTEM AIM

• The aim of this system is to provide the armed forces with a tool that provides laser designation capability for precision strikes, decreasing the trooper efforts and the risk of loss to which they are exposed –specifically during the extraction from hot areas - and which is overall more cost efficient than other related systems.

• As of today, there is no mini UAV in operation capable of fulfilling such missions and above criteria simultaneously.

• This project was born from a real need and a high demand.

UNMANNED AERIAL SYSTEM ALTERNATIVE USES

• This aircraft could be alternatively used as an observation system for objectives and risk areas, allowing the troops to anticipate any issues that might arise.


02.- SIMILAR AIRCRAFTS

SIMILAR AIRCRAFTS [*]


A/C W (kg) T (Kg) S (m2) b (m) L (m) C ROOT (m) A λ

FOTO #1 3860,00 861,47 80,68 21,30 4,60 2,00 5,62 0,80

FOTO #2 4,20 1,47 1,37 2,12 0,82 0,46 3,28 0,40

FOTO #3 202,00 39,32 2,81 3,76 1,88 1,02 5,03 0,58

FOTO #4 1,9 1,90 0,3 1,4 0,9 0,21 6,53 0,48

[*] For further information see document: UAS-CDR-AX-15002-A – Similar Aircrafts.xlsx

03.- AIR VEHICLE OVERVIEW

DESCRIPTIONFlying wing concept, straight tapered midsection wing

WEIGHTS & DIMENSIONSWing Span: 2,07m

Length: 0,788

Chord root: 0,56m

SWET : 2 m2

Weight: 3,3kg

A: 4,4

λ: 0,6

PERFORMANCESRange: 30 Km

Endurance: 35min

VMAX : 80 km/h

Ceiling: 2000 m MSL

Thrust: 2,68 kg

SUMMARYShape: Darkstar

Dimensions: X8

Performances: Raven

Mission: Aquila…with an electric motor!


04.- GROUND SEGMENT

DESCRIPTIONThe Ground Control Station is a portable simplified system based on a laptop computer with specific communication devices and a small LCD screen to receive the video feedback. Also, an RC controller is provided for manual operation.

PERFORMANCESData Link Range: 5 Km

Video Link Range: 5 Km

Endurance: Up to 6h

Total Weight: 5 Kg

Power source: Batteries

Control modes: Automatic and manual

Controllers: Computer and RC controller


05.- MISSION

MISSION DESCRIPTION [*]

1.- Operator on an outpost or base is scrambled to designate a target. 2.- Target is introduced and confirmed by operator, who assembles system and launches MACHETE air vehicle. 3.- Launched from safe area. Target located maximum 5 km away from operator. 4.- One single target is designated. 5.- After the strike, MACHETE returns lands close to operator.


[*] For further information see document: UAS-CDR-AX-15003-A – Mission.xlsx

07.- REQUIREMENTS & MoC

OPERATIONAL REQUIREMENTS [*]

MISSION REQUIREMENTS [*]


[*] For further information see document: UAS-CDR-AX-15001-A – Requirements, Risks & Opportunities.xlsx

08.- RISKS & OPPORTUNITIES

RISKS [*]

OPPORTUNITIES [*]


[*] For further information see document: UAS-CDR-AX-15001-A – Requirements, Risks & Opportunities.xlsx


A/C & GROUND SEGMENT EQUIPMENT

09.- A/C SYSTEMS

AIRCRAFT CONTROL & PROPULSION SUBSYSTEM [*]

• This aircraft is driven by a single electric brushless motor in a pusher configuration. The speed of this motor is assigned by the autopilot system and controlled by the ESC (Electronic Speed Controller).• The control surfaces are elevons controlled by one high-speed servo actuator each.• All systems are electric and powered by two 6000 mAh LiPo batteries.


[*] For further information see document: UAS-CDR-AX-15004-A – Equipments Selection.xlsx

Scorpion SII-3020890 kV

MOTORAeroStar Advance

65 AMultiple V output

ESC AUTOPILOT

Pixhawk5 V

500 mA

BATTERIES (2x)

Turnigy nano-tech6000 mAh3S, 11.1 V

LEFT ELEVON SERVO

BMS-631MGMetal Gear

5.0 kg

RIGHT ELEVON SERVO

BMS-631MGMetal Gear

5.0 kg

Power line

Data line

09.- A/C SYSTEMS

MISSION EQUIPMENT SUBSYSTEM [*]

• Composed by two smaller subsystems: The Laser Designator and the Video Transmitter.• The first consisting on a gimbal stabilized laser designator, driven by a relay and controlled by the autopilot.• The last one is an independent subsystem formed by a video transmitter module and a camera.



UBEC

Kingduino5V

RELAY

GIMBAL

BATTERIES (2x)

LASERDESIGNATOR

AUTOPILOT

650nm(red laser)

200-250mW5V

TurnigyInput: 6v-12.6vOutput: 5v/8A

Pixhawk5V

500 mA

FatShark PilotHD720p, 30 FPS5V, 250 mA

CAMERA

VIDEO TX

Power line

Data line

Tarot T-2D7.4V ~ 14.8V

200mA-500mA

Turnigy nano-tech6000 mAh3S, 11.1 V

SkyZone5.8 GHz, 200 mW7~15 V / 150 mA

10.- GROUND SEGMENT

GROUND SEGMENT SUBSYSTEM [*]

• Portable Ground Control System composed of a laptop computer, and a USB telemetry module to maintain constant communication with the aircraft at all times.• A receiver module will capture video images in real time, which will be displayed on an LCD monitor during the mission.• An RC controller will allow the operator to maneuver in manual mode if necessary.



Mac, Linuxor Windows

LAPTOPCOMPUTER

TELEMETRYMODULE

7 inchesColor display

Battery powered

LCD SCREEN

Rx module5.8 GHz 200 mW

RCA interface

RC CONTROLLER

9 channels2.4 GHz

Tx/Rx moduleUSB interface

433 MHz

VIDEO RECEIVER

11.- EQUIPMENT LIST

COMPLETE EQUIPMENT LIST [*]



P/N QTY SEGMENT DESCRIPTION WEIGHT (gr)

PRICE (€) ALTERNATIVE PENALTY

AP-1 1 Air 3DR Pixhawk 38 179,00 -BATT-1 2 Air Turnigy Nano-tech 6000 mAh 481 43,23 Multistar High Cap. 4S 16000mAh Use only 1 batteryENC-1 1 Air PPM Encoder 2 22,30 -ESC-1 1 Air Aerostar Advance 65A ESC 68 35,14 Turnigy Trust 70A NoneGMB-1 1 Air Tarot T-2D V2 220 87,25 Smart3 3-Axis Higher priceGPS-1 1 Air uBlox LEA-6 17 72,00 - LSR-1 1 Air Laser Generator Diode 200-250mW 650nm 80 10,41 -MTR-1 1 Air Scorpion SII-3020-890KV Brushless Outrunner 166 97,89 Tr 42-50a Lower RPMPTT-1 1 Air Px AirSpeed 4 50,00 -PRP-1 2 Air Carbon Fibre 13x6.5 Folding Prop Blades 20 11,67 - PRP-2 1 Air Alloy Folding Prop Spinner with 3.17/4mm/5mm Adapter 10 7,36 -RDO-1 1 Ground Turnigy 9x (modo 2) 350 53,39 - RDO-2 1 Air RC receiver 18 - -ALT-1 1 Air MB1240 XL- MaxSonar EZ4 Ultrasonic Range Finder 45 34,95 - RLY-1 1 Air 5v Relay module 50 4,63 -SRV-1 2 Air BMS-631MG Super Fast Servo 46 15,09 Hitec HS-485 deluxe NoneTLM-1 1 Air 3DR 433Mhz modulo aire 50 33,99 -BEC-1 1 Air TURNIGY 8-15A UBEC 34 13,71 - VID-1 1 Air FatShark PilotHD 720p 30fps HD FPV Camera 33 29,17 Sony Super HAD CCD NoneVID-2 1 Air SkyZone 5.8Ghz 200mw FPV System (Tx) 25 48,94 TS832 (5.8 GHz 600mW) Higher priceVID-3 1 Ground SkyZone 5.8Ghz 200mw FPV System (Rx) 200 - DIY FPV Goggle Set with Monitor Higher priceVID-4 1 Ground FPV 7inch TFT-LCD Monitor 200 41,68 DIY FPV Goggle Set with Monitor Higher price

TOTAL --- --- --- 2157 891,8 --- ---

12.- GENERAL ARRANGEMENT



INBD PROFILE [*]

Components are positioned in such way to maintain the aircraft CG and also be accessible to operators.

GROUND SEGMENT SUBSYSTEM [*]

Monitor 5W, Transmitter with low battery warning and a time range larger than the plane itself.

13.- SYSTEMS DIMENSIONING



PROPULSION & CONTROL SUBSYSTEM [*]

.

MISSION SUBSYSTEM [*]

Laser Designator: 0,73 kgRattler Diode-pumped laser designator:


POINT PERFORMANCES

STALL [*]

• During the Stall the wing can not make enough lift to keep the aircraft in level flight• It is the most critical performance of the aircraft It will drive the wing surface sizing for the biggest value of needed CL

Hypothesis:Horizontal flightρ (1100m) = 1.05kg/m3

CLmax = 1,4 (Unknown airfoil)

Inputs:Vstall = 27km/h

c = 0,4

14.- PERFORMANCES


[*] For further information see document: UAS-CDR-AX-15005-A – Conceptual Design.xlsx

W/S= 35,4 N/m2

CRUISE [*]

The Cruise is an symmetric horizontal rectilinear flight:

Hypothesis:Minimal Drag: CD=CD|CL=0 =CDo

Maximal Efficiency: CDo=CDi

Swet/Sref=2,5 (flying wing)

T/W= 0,83

Parabolic Polar:CD = 0,013+0,064CL

2

Inputs:Vcruise = 70km/h

c = 0,4mA = 4,4

14.- PERFORMANCES



W/S= 87,9 N/m2

CLIMB & DESCENT [*]

During the Climb and Descent the flight is symmetric and rectilinear:

Hypothesis:Minimal Vclimb must be > 1,1Vstall

T/W= 0,83

Load factor:n = cosß = 0,87

Inputs:Vclimb |min = 29,7km/h

Vdescent = 70km/h

ß= 30°

14.- PERFORMANCES



W/S|climb=243,5 N/m2

W/S|descent =2796,6 N/m2

14.- PERFORMANCES



MAINTANED TURN [*]

The mission requires a loiter maneuver in order to satisfy the target designation.A minimal angle of balance is needed to keep the laser’s FOV.

Hypothesis:T/W= 0,83

Load factor:n = 1/cosɸ = 1,15

Inputs:Vloiter = 11,1m/s

R= 450 mɸ= 10°

W/S= 627,5 N/m2

14.- PERFORMANCES



PERFORMANCES SUMMARY [*]

The critical performance will be the stall. In cruise and stall performances, the velocity has been the design parameter.For climb and descent, a slight angle has been chosen to keep a safe distance from the enemy.

In the maintained turn, the cone of vision must be high to satisfy the requirement of the appointment.

PERFORMANCE V (m/s) W/S (Kg/m2) T/W CLIMB ANGLE (°) TURN ANGLE (°)

STALL 7,5 35,4 0,83 --- ---

CRUISE 19,4 87,9 0,83 --- ---

CLIMB 8,3 243,5 0,83 30 ---

DESCENT 13,9 2796,6 0,83 30 ---

MAINT. TURN 11,1 627,5 0,83 --- 10

DATA FOR PRELIMINARY DESIGN [*]

W (kg) W/S T/W S (m2) b (m) Cr (m) Ct (m) ʎ A Ʌ (°)

3,3 35,4 0,83 0,91 2 0,57 0,34 0,6 4,4 5

UNMANNED AERIAL SYSTEMS MASTER 2015 – GROUP X PRELIMINARY DESIGN REVIEW - PDR PAGE 23

PRELIMINARY DESIGN

ENGINE & PROPELLER SELECTION [*]

15.- ENGINE & PROPELLER



ENGINE PRELIMINARY SIZING [*]

Give it all !!: Top speed 110 kph + powerful climbing thrust!!

16.- WING



TRAPEZOIDAL APPROACH [*]

Ours is a mid-wing monoplane aircraft, with a 5º angle of sweep and a moderate to low aspect ratio. The wing is modeled in CATIA and it’s completely parameterized, allowing us to make any adjustment easily.

510 mm

1035 mm

330 mm

NACA 4412

17.- FUSELAGE



LENGTH ESTIMATION [*]

The length of the fuse was estimated in taking into account the need of a nose to have an appropriate CoG, and trying to respect the «flying wing» shape.

DIAMETER ESTIMATION [*]

The diameter was estimated based in the necessary equipment for the assigned mission. The fuselage was created in CATIA using a conic technique, and it’s completely parameterized, allowing us to adapt it easily.

700 mm

300 mm


AERO REFINEMENT

19.- PROFILE SELECTION


[*] For further information see document: UAS-CDR-AX-15006-A – Aero Design Refinement.xlsx

WING PROFILE SELECTION [*]

NACA 4412 satisfies requirements of:· Easy to build (flatter bottom)· Maximum volume available· High value of CL

· High lift to drag ratio (~ 57)

Max camber of 4% of chord, located at 40% from leading edge. Max thickness 12%.

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1-0.05

0

0.05

0.1

0.15

NACA4412

Why not others?

· NACA 2415 and NACA 4415 airfoils have higher drag coefficients due to their increased thickness to chord ratio.

· NACA 006 and NACA 009 do not provide space enough for all the components to allocate.

· NACA 2412 has lower CL and lift to drag ratio in comparison with NACA 4412

20.- AERODYNAMIC DRAG



FUDGE FACTORS [*]

PARTIAL & OVERALL AIRCRAFT CD0 [*]

WING: FFWING = 0,96

FUSELAGE: FFFUSE = 3,3

WING: CDo = 0,009

FUSELAGE: CDo = 0,006

20.- AERODYNAMIC DRAG



INDUCED DRAG & POLAR [*]

The curve polar shows the relationship between the lift on an aircraft and its drag:

Zero-lift drag: Parasite drag of complete aircraft that exists at its zero-lift angle of attack

Subsonic regime

CD = Cdo|Total + K·CL2

= 0,015 + 0,078·CL2

Induced Drag: Pressure drag caused by the creation of wing tip vortices (induced lift) of finite wings


CONTROL & STABILITY

22.- C.o.G. POSITION


[*] For further information see document: UAS-CDR-AX-15007-A – C.o.G. and Stability.xls

C.o.G. POSITION [*]

25.- STABILITY CONCLUSIONS


STABILITY CONCLUSIONS [*]

• In a Flying wing vehicle, the C.o.G must be positioned forward from the C.o.P.• The C.o.G is located 0,29 meters behind the plane tangent to the nose of the vehicle and the aerodynamic center wing is located 0,41 meters.

[*] For further information see document: UAS-CDR-AX-15007-A – C.o.G. and Stability.xls

• The negative sign of the pitching moment of the airfoil and the equipment distribution of the vehicle assure its own stability (a deeper analysis will be required to stablish the stability margin).


REFINED GEOMETRY

PERFORMANCES SUMMARY (REFINED)

In the later aerodynamic study, the contribution of the fuselage is taken into account. Thus, the wing loading will vary :

PERFORMANCE V (m/s) W/S (Kg/m2) T/W CLIMB ANGLE (°) TURN ANGLE (°)

STALL 7,5 35,4 0,11 --- ---

CRUISE 19,4 87,9 0,07 --- ---

CLIMB 8,3 243,5 0,58 30 ---

DESCENT 13,9 2796,6 -0,42 30 ---

MAINT. TURN 11,1 627,5 0,08 --- 10

DATA FOR REFINED DESIGNThe wing parameters after the refined design are shown in the following table:

26.- REFINED DESIGN

[*] For further information see document: UAS-CDR-AX-15008-A – Refined Design.xlsx


W (kg) W/S T/W S (m2) b (m) Cr (m) Ct (m) ʎ A Ʌ (°)

3,3 37,1 0,11 0,87 1,96 0,56 0,33 0,6 4,4 5

26.- REDEFINED DESIGN


ENGINE & PROPELLER CHECK [*]

Comparing the initial estimated Thrust with the maximum thrust needed (in stall performance):

WING GEOMETRY CHECK [*] After the aerodynamic refinement, the wing parameters are:


Maximum Thrust needed: 26,5 N

Estimated Thrust: 34,6NSimilar aircrafts: Thrust and 13x6.5 propellerThe engine&propeller are able to satisfy the

mission



FUSELAGE DIMENSIONS CHECK [*]

Fuselage Dimensions from Preliminary Sizing required a notorious adjustment after reviewing CoG status.

No need.


REFINED DESIGN FINAL DATA [*]

.



FINAL CONCLUSIONS


Wide nose to keep the payload safe inside

Cover to access the equipment easily

Wide wings to support the payload’s weight

Transparent bottom cover withbig FOV for laser and camera

• System design fulfills all mission requirements and specs.• Design team has identified opportunities for improvement mission capabilities.• Design team considers PDR goals have been achieved, and request approval to continue with current configuration for next design stages.


SCHEDULE

TASKFEB MAR APR MAY

TOTAL1 2 3 4 1 2 3 4 1 2 3 4 1 2 3 4

SIMILAR A/C ANALYSIS 16 8 2 26

REQ. & MISSION DEF. 8 12 4 4 28

SYSTEMS DEFINITION 2 12 8 8 30

PRELIMINARY DESIGN 4 8 8 8 2 4 4 38

CAD (PRELIMINARY) 8 8 12 8 8 4 48

AERO REFINEMENT 2 4 6 4 4 20

STABILITY 2 8 4 2 16

CAD (REFINED) 8 10 18

TOTAL 64 64 64 32 224

27.- SCHEDULE


SCHEDULE FEBRUARY - MAYThe number of hours dedicated to each task are shown next:

Engineering Hours Spent: 224h. Assuming 75€/MH (Man Hour) the Overall Cost of this Project up to this point is 16,8 k€.


THANK YOU!

Uas-15008-a-slides for PDR

Engineering

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