Uninhabited Air Vehicle TeamMulti Purpose UAV

Team Members:Maria Luviano

Roland Chen

Juan Pablo Barquero

Shing Chi Chan

Tom Guyette

Solomon Yitagetsu

Winston Young

Wess Gates

Faculty Advisors:Dr. Chivey WuDr. Helen Boussalis

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Volunteers:Keith BacosaBilly BarriosMichael DoanRama MbeckeOmar Miranda

KOSMOS HERMES 55

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Overview

Objective Aircraft performance Structures Prototype Computational fluid dynamics Flight control system integration Propulsion Budget

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Objective

To design an autonomous, heavy payload, lightweight UAV that is

capable of carrying out multiple missions.

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Aircraft Performance

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Technical Data

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Technical Data

Gross Weight 55 lbs

Wingspan 11 Ft

Length 7 Ft

Payload Weight 10 Lbs

Cruise altitude 3280 Ft

Cruise Speed 73.35 Ft/s

Endurance 3 Hrs

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Lift Curve Slopes and Coefficients

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( ) ( / ) (1 ) cL Aircraft L wing Strakes LC

SC C C

S

Lift curve slope

Aircraft Performance

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Lift to drag ratio (L/D)max = 11

Engine Sizing

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Power Curves

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(PA)max

Vmax

Performance

Vmax = 161 ft/s

Rate of climb♦ (R/C)max = Excess power

W♦ (R/C)max = 34.5 ft/s

Flight velocity for maximum rate of climb

♦ V(L/D)max = (2/ρ)*((K/CD,O)^1/2)*(W/S)

♦ V(L/D)max = 70 ft/s

Maximum climb angle

♦ Sin Θmax = T/W – 1/(L/D)max

♦ Θ = 27 deg.

Flight velocity for maximum angle of attack

♦ Vθmax = Max rate of climb

Sin Θmax♦ Vθmax = 76 ft/s

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Structures

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Aircraft Structures

Aircraft structure is required to support two distinct classes of load♦ Ground load: movement on the ground ( taxiing, landing, and towing)

♦ Air loads: loads during flight by maneuvers and gusts.

Function of structural components:♦ To transmit and resist loads to provide shape and protect passengers,

payload, systems, etc from the environmental conditions found during flight.

Current UAV structural objective:♦ To have a semi-monocoque structure that has “minimal” structural

members.

♦ Have the skin of the UAV to be manufactured with different thicknesses in order to achieve a lighter aircraft weight

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Concepts

Concept 1 – Rib and spar configuration

Concept 2 – Lighter rib and spar configuration

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Concepts

Concept 4 – Structural member with an uniform wing skin thickness

Concept 3 – Rib and spar configuration assembled with an uniform wing skin thickness

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Structural Concept

This approach considers the following:♦ Split the wing in two main sections

Section 1 – have a semi-monocoque structure to absorb most of the loads Section 2 – completely monocoque where the loads decrease

Section 1 – Semi-monocoque structure with skinNASA Grant NNX08BA44A

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Structural Concept

Service panel

Fuselage base plate

Section 1

Section 2

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Next Steps

Optimize wing internal structural concept♦ Use of FEA (Finite Element Analysis)

♦ Decrease size of cross members

Optimize skin thickness Define/design mounting brackets for wing and skin Define mounting points for control surfaces

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Prototype

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Prototype Objectives

Validation of Current Aerodynamics♦ Canard Design

♦ Aerodynamics of the Wing

♦ Balance and Stability

Practice for Possible Fabrication Techniques♦ Multiple Interchangeable Wings

Conventional, Composite, etc.

Identify the Proper Parameters for Control♦ Control Surface optimization

Test Current Landing Gear configuration

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Half Scale Prototype

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Specifications

Dimensions:♦ Length: 45.15 in (1.14 meters)

♦ Height: 17.316 in (0.43 meters)

♦ Wingspan: 63.44 in (1.611376 meters)

Weight: 5-6 pounds (2.26 - 2.72 kilograms)

Propulsion: Electric Motor♦ Propeller Diameter: 12 in (0.30 meter)

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Manufacturing

Fuselage and Canard♦ Cut from Foam

♦ Sand to Final Shape

Wing♦ Version 1

Built up from Balsa and Plywood Covered with film

♦ Future Versions Fiberglass or Carbon Fiber

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Computational Fluid Dynamics

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AVL

Athena Vortex Lattice Written by Mark Drela Computes yawing moments, rolling moments, and stability Models ailerons and flaps Feeds into simulation effort Verify hand calculations

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AVL editor

The Cloud Cap Technology software includes an AVL editor for the end user to try out different AVL configurations. The aerodynamic properties are then shown in the AVL editor window along with the appearance of the wing structure.

Inputting Geometry into AVL

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AVL Model

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AVL Model

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Loading

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Flight Control System Integration

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T60 Piccolo Hardware Integration

Purpose: To learn everything about installing and flying Piccolo in an inexpensive air vehicle so we’ll be ready when our new vehicle is complete.

Work completed: Manual test flight complete (Solomon, Juan, Maria) Communication issues are resolved Piccolo has been fit into fuselage (harder than it sounds!) Piccolo is roughly leveled / squared with fuselage Manual control through Piccolo link is verified Control surfaces are calibrated

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T60 Piccolo Hardware Integration

Work remaining: Test running Ground Station from 12V power inverter Calibrate throttle servo Gather vibration data Test GPS Test comm range Some remaining mechanical maintenance Design Deadman power system

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T60 Piccolo Simulation

Purpose: To tell Piccolo everything it needs to know to pilot the vehicle.

Available from other sources: Masses, some dimensions, AVL model, rough propulsion model

Work remaining: Model in AVL simulator and XFoil Measure squareness angles Measure additional dimensions Re-calculate and measure CG Calculate mass moments of inertia

(easy, but values are rough) Measure moments of inertia?

(complicated / better values)

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Propulsion

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Overview

Engine break in Engine bench test SolidWorks model

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Break in Engine Mount

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Bench Test Design

Three kinds of test will be performed♦ Thrust

♦ RPM

♦ Fuel flow

Test the propeller’s performance

Compare the result Which propellers have

good efficiency

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Strain gage

Side View

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Top View

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Diagonal View

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Instrumentation

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Budget

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New Materials

Total budget $13,500

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Reference

Corke C. Thomas. Design of Aircraft. 2003. Prentice Hall Anderson Jr, John D. Aircraft Performance and Design. Mcgraw Hill 1999 Beer P. Ferdinand, Johnson E. Russell, and Dewolf T. John. Mechanics of Materials.

4th Edition. McGraw Hill. 2003 T.H.G. Megson. Aircraft Structures for Engineering Students. 3rd Edition. Butterworth

Heinenmann. 1999 Raymer, Daniel P, Aircraft Design: A Conceptual Approach. 3rd Edition. AIAA

Education Series 1999 http://www.sierracomposites.com/carbon-fiber-square-tube-with-2-sides-p/cfst284.htm http://dragonplate.com/docs/DPSpecRecTube.pdf http://www.safetycitystore.comhttp://www.bagking.com/Merchant2/merchant.mvc?

Screen=PROD&Product_Code=TDH6&qts=googlebase&qtk=TDH6 http://www.delta7bikes.com/shop-bike.htm Anderson Jr, John D. Aircraft Performance and Design. Mcgraw Hill 1999

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Reference

http://www.powerelectronics.com http://www.sengpielaudio.com/calculator-cross-section.htm http://www.batteryuniversity.com/partone-5A.htm http://www.mpoweruk.com/performance.htm http://en.wikipedia.org/wiki/Torque http://www.copperhillmedia.com/VisualSizer/MotorSizingArticles.html http://www.electricmotors.machinedesign.com/guiEdits/Content/bdeee3/

bdeee3_1.aspx http://rmsmotion.com/resources/step_basics_v1_0.pdf A Comprehensible Guide to Servo Motor Sizing by Wilfried Voss http://www.powerstream.com/Wire_Size.htm http://www.66pacific.com/calculators/wire_calc.aspx AVL. Mark Drela, Harold Youngren. MIT Aero and Astro Cloud Cap Technology user guide, software simulation manual, and checklist

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Thank You

AdvisorsDr. Boussalis

Dr. WuDr. Guillaume

Dr. PhamDr. Liu

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