2007-2008 RIT MAVSystem Review (P08121)

Dr. Jeffrey Kozak – Faculty GuideMichael Reeder – Team LeaderKevin Hand – Lead EngineerTodd Fernandez – MESusan Bieck – MEJeremy Teets – MECody Rorick – MEAdam Bosen – CE

…where the sky is only the beginning……and the ground is likely the end…

Sponsored By:

Re-Introduction of Team Members

Mike ReederKevin Hand

Sue Bieck

Jeremy Teets

Adam Bosen

Todd Fernandez

Cody Rorick

Project Description/Customer Needs

Primary Objective: Create a Micro Aerial Vehicle, expandable in nature for future

RIT research Simple, robust and stable in design Capable of reading back information regarding the vehicle’s

speed, angle of attack, pitch, yaw and roll rates Flight Dynamics competition (held internationally) establishes

target specifications (engineering metrics) Max linear dimension is 80 cm Max weight is 1 kg Required flight time is 4 minutes

Secondary Objective: Compete in international Flight Dynamics competition

Objective of 2007-2008 RIT MAV

Platform design decided upon Engineering metrics/product specifications completed List of components and materials compiled 3-D CAD model of plane created (XFOIL, Pro-E, etc.) Foam model built based on concept generations Experiments designed to test components’ proper functionality Components ordered/in team’s possession Components in possession are in test process Foam plane is built and glide tested

Objective of 2007-2008 RIT MAV

Fully Remote Controlled

Introduction of ControlSystems

Fully Autonomous Flight Achieved

2007-2008 RIT MAV autonomous

autonomous

Flight Information

Microcontroller Tri-axial accelerometers

Differential pressure sensors (AOA, velocity)

Selected Concept

Selected Concept – Airfoil

Selig S1210 airfoil chosen for: Weight range

(500-1000g) Efficiency at

various AOA’s Speed range

(15mph+)

Efficiency vs AOA Study Re=192044

0

20

40

60

80

100

120

-10 -5 0 5 10 15

a (deg)

Cl/C

d Selig S1223

Eppler E62

Selig S1210

Selected Concept – Propulsion System

Esskay 400XT 1.5 oz brushless motor Allows for several prop sizes

to achieve various speeds Thunder Power TP9103

3 cell configuration 910 mAh

**Several props will be bought and tested to determine optimal speed of the MAV**

Selected Concept – MAV Design

MAV design based on: Brainstorming sessions Feasibility analyses Flight dynamics calculations (reference)

Chosen design utilizes Stream-lined cylindrical fuselage Fuselage designed to incorporate airfoil into body Symmetrical rear airfoil

Selected Concept – Flight Dynamics

Flight dynamics calculations led to a series of calculations to determine stability of aircraft

Calculations also aided in determining proper rear tail dimensions Horizontal tail span – 10 in Vertical tail span – 5 in Horizontal & vertical tail chord – 4 in Moment arm of the tail – 17 in

Selected Concept – CAD Generated Model

Selected Concept - Controls

Main component to be used is O-Navi microcontroller Contains angular accelerometer, GPS, among others Use of microcontroller will enable complex information

to be sent to and received from MAV Paparazzi considered for software architecture

Pressure transducers (velocity, AOA) Servos (flight control)

Selected Concept – Design of Experiments

Differential pressure sensor used in conjunction with a pitot tube to determine aircraft velocity

One differential pressure sensor on each wing to determine pressure difference which will yield AOA experimentally

Angular/Linear accelerometers used to determine pitch, roll and yaw of aircraft during flight

LabVIEW, LabVIEW, LabVIEW!!!

Selected Concept – User Interface

Utilize LabVIEW to create interface: Altitude Velocity Pitch Roll Yaw

Example shown

Risk Assessment

Risk MitigationsReviewing of literature None - reviewed papersThrust None - found motorBattery life None - found batteriesStructural damage Fiberglass and carbon fiber (crumple zones)Wind/conditions Stable aircraft (large wingspan)Communication data corruption Communicate using other frequenciesLost aircraft Incorporate emergency tracking?Stability problems Flight dynamics calculations/proper placement of componentsFlying capability Proper use of servos/proper design of ailerons, rudder, etc.Obtaining/building test fixtures Work with professors who may have necessary equipment (windtunnel available)Obtaining all required results Proper design of test fixture to obtain necessary resultsHeat buildup Strategic "venting" of aircraftUnpredictable testing/debugging time frame Start as early as possible once components are obtainedBirds of prey mistaking MAV for a meal Keep fingers crossed (plane is rather large, larger than most birds)Incorporating all components into design Last step procedure - all testing to be completed using test fixtures firstProper testing of airfoil and body design Flight dynamics calculations, wind tunnel testing, glide testsLarge enough team to handle work load None - team is large enoughLarge enough budget to support team Some materials borrowed from Aero TeamStaying in budget once budget is established Some materials borrowed from Aero Team

High Level Risk Assessment with Mitigations

Tentative Bill of Materials (BOM)

Tentative BOM is shown to the right

Impact Technologies has generously donated $1,500.00 to the MAV Senior Design effort for 2008.

Material/Component Quantity Needed Per PlanePressure Transducer 1Differential Pressure Sensor 2Microcontroller 1Camera 1Accelerometers (tri-axial configuration) 2Batteries TBDMotors 1Speed Controllers 2Propellers 1Servos 4Transmitter/Receiver 1Transceiver (Equivalent) 1Radio Crystals TBDFlexible and Rigid Resin TBDStructural Foam (thicker needed) TBDLEDs 1Watch Batteries 1Wires N/AAntenna N/ABalsa Wood TBDFiber Glass TBDPeel Ply ~ 10 square yardsVacuum Bagging Material ~ 10 square yardsCarbon Fiber ~ 10 square yardsMagnets (access doors) TBD

Completed Objectives – MSD I

Platform design decided upon – COMPLETED Engineering metrics/product specifications completed –

COMPLETED List of components and materials compiled – COMPLETED 3-D CAD model of plane created (XFOIL, Pro-E, etc.) –

COMPLETED Foam model built based on concept generations –

COMPLETED (1st run model) Experiments designed to test components’ proper functionality –

WIP Components ordered/in team’s possession – WIP Components in possession are in test process – WIP Foam plane is built and glide tested – WIP (airfoil creation)

Tentative Schedule for MSD II

- Completion of blank plane (red)- Component testing (yellow)- System integration of components (orange)- Integration of system into ground model (green)- Flight tests (light blue and blue)- Base station data retrieval (purple)- MAV system integration (light green)- Completed project flight testing (gray)

Remember…

Q & A