System Design Review P10232 – UAV Airframe C
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Transcript of System Design Review P10232 – UAV Airframe C
SYSTEM DESIGN REVIEWP10232 – UAV AIRFRAME C
Daniel Graves – Project LeadJames Reepmeyer – Lead EngineerBrian Smaszcz – Airframe DesignAlex Funiciello – Airfoil DesignMichael Hardbarger – Control Systems
Project DefinitionMission Statement:
The goal of the UAV Airframe C project is to provide an
unmanned aerial platform used for an aerial imaging
system. The airframe must support the weight and
interfaces for the designed imaging system. The aircraft
must be operated remotely and be a viable alternative to
current aerial imaging methods. This is a second
generation airframe, expanding on the previously laid
ground work established by the P09232 UAV B Senior
Design Project.
Customer NeedsKey Project Goals: Airframe must be able to carry a fifteen pound payload Easy integration with measurement controls box and
different aerial imaging systems Ability to remotely control aircraft and activate payload Ability for flight communication between aircraft and
ground relay Aircraft provides twenty minutes of flight time for local
area photography Aircraft has the potential to take off and land on site Easy assembly and disassembly of the aircraft for
transportation
Lessons Learned From P09232 The aircraft’s wings sheared off shortly before
impact. The failure was determined to be from the bending stress applied to the wings during the banked turned.
After analysis, it was concluded that the main
fiberglass spar used to support the wing was not selected properly to handle the flight loading.
High bend in the wing during flight inhibited the pilot’s control of the aircraft by reducing the effectiveness of the control surfaces.
Risk AssessmentID Risk Item Effect
Importance Action to Minimize Risk
1 Flight Test Failure
Team fails to meet project deliverable 9
Design aircraft and associated tests correctly. Study weather for optimal test conditions
2
Meeting Project
Deadlines
Project will run behind schedule, or project deliverables are not met 6
Create proper schedules with an appropriate buffer time between dependent actions
3 Component Redesign
Forced project redesign can force the project to run over deadlines 3
Smart aircraft design with proper backing analysis. Compliance with subsystem interface designs.
4 H1N1/Illness Team members can fall behind in work 3 Proper cleanliness and Hygiene
Risk AssessmentID Risk Item Effect
Importance Action to Minimize Risk
5 Build Time Runs Over
Delay in meeting project deliverable, flight testing does not run on schedule 4
Begin build phase early and maintain positive team morale
6 Component
Testing Failure Delay in project deliverable or testing schedule 2
Test parts early and properly design all critical systems
7
Miscellaneous Damages/Theft
Loss of progress and time 3 Ensure all parts are properly stored and secured
8
Budget Increase
Needed
Unable to purchase critical parts needed for aircraft design and build 2
Have budget clearly defined and avoid expensive components where possible
9 Budget Driven
Redesign
Team will have to redesign aircraft systems, increasing time needed for completion 3
Have budget clearly defined and avoid expensive components where possible
Risk AssessmentID Risk Item Effect
Importance Action to Minimize Risk
10 Part Lead Time
Parts required for assembly delay build progress 2
Order parts at the end of MSDI and make sure all parts are ordered
11 Team Member
Injury
Team member can fall behind in work resulting in a progress delay 2
Every team member acts in a responsible manner ensure work is done in a timely manner
12Critical Data
Loss
Component re-design or analysis will need to be repeated 2
All documents are backed up on EDGE
13 Winter Break
Start Up
Ramp up time for project build is longer due to winter break 2
Continue work and project updates during the winter quarter
Control Interfaces (physical)
Control Interfaces (electrical)
Body Structure The structure shall support 15lbs of payload. The structure shall have an accessible payload
bay. The structure shall assemble/ disassemble for
transport. The structure shall resist deformation under
normal operation. The structure shall house the planes power
system and provide a mount for the engine. The structure shall be durable, enabling
multiple flights without servicing.
Airframe Concept Goals Reduce weight of airframe compared to UAV B
Improve aerodynamics
Improve in-flight stability and handling properties
Optimize payload integration and removal
Design airframe to highest “open architecture” capability
http://mae.ucdavis.edu/~EAE127/index_files/1008033.jpg
Airframe Concept Selection Standard monoplane design.
Top mounting wing capability.
Detachable conventional tail section.
Configuration used in small aircraft and
RC trainer planes.
Simple design allows for shorter build
time.
http://www.hooked-on-rc-airplanes.com/images/rc-trainer-planes6.jpg
http://www.excelaviation.ca/index_files/image004.jpg
Airframe Fuselage Concepts Twin-boom
Tandem wing
Canard Style
Flying wing
Delta wing
http://www.spyflight.co.uk/images/
www.viswiki.com/en/Tandem_wing
http://commons.wikimedia.org/wiki/File:Vulcan.delta.arp.jpg
http://advancedaerospacellc.com/jcfly%2015%25.jpg
http://upload.wikimedia.org/wikipedia/commons/4/4a/YB49-2_300.jpg
Airframe Selection Matrix
Monoplane Bi-plane Delta Flying Wing
Tandem Wing
Split Body
Boom Tail
Design 0 - - - - - - - - - Cost (initial) 0 - 0 + - - - - +
Piloting Difficulty 0 - - - - - + 0
Transport 0 + - - - - + Flight Time 0 0 0 ++ + + 0
Payload Flexibility 0 0 - - - ++ - -
Payload Weight 0 0 0 + ++ + 0
Airspeed 0 - + - 0 - 0 Total 0 -3 -3 -4 -2 -3 -1
Airframe Tail Concepts
http://www.flightdesignusa.com/
http://media.photobucket.com/
http://www.aviationspectator.com/
http://farm2.static.flickr.com
Conventional
T-Tail
Cruciform
Twin-Tail
V-Tail
http://en.wikipedia.org/wiki/File:Jetstream31.jpg
Airframe Tail Selection Matrix
Cambered H-Tail V-Tail T-Tail Cruciform
Stability 0 + + - -
Design Difficulty 0 - -- -- --
Weight 0 - + - -
Controllability 0 + - + +
Drag 0 + + 0 0
Flight Envelope 0 0 0 + +
Cost 0 - - - -
Total 0 0 -1 -3 -3
Tail Airfoil Selection Lifting tail will be used to counter wing
moment A low cambered foil will be used to
minimize drag
Airfoil Specifications The airfoil shall provide enough lift to carry the craft. The airfoil shall minimize drag. The wing shall be able to be disassembled. The wing shall be structurally rigid and free of in flight
flutter. The wing shall contain control surfaces. The wing planform area shall be designed such that
wing loading is kept under 20 oz./ft2. The wing shall be structurally sound. The wing shall resist deformation under loading.
Airfoil Selection MatrixHigh Camber- Flat Bottom
High Camber - Under
Cambered Low Camber Reflex Symmetric
Lift 0 + -- -- --
Drag 0 + + - -
Stall Angle 0 + - - 0
Stall Speed 0 + - - 0
Moment 0 - + ++ +
Structure 0 - 0 0 0
Total 0 2 -2 -3 -2
Airfoil Concept Selection Add additional camber compared to last
yearflat bottom under camber design
Increase lift Decreases stall speed Decrease required chord and wingspan
Flat bottom v. Under Camber
NACA-9412
S7055
Airfoil coordinates from UIUC airfoil database
Airfoil Lift comparison
Comparison from the Airfoil Investigation Database, with data taken from the UIUC airfoil database
Airfoil Drag Comparison
Comparison from the Airfoil Investigation Database, with data taken from the UIUC airfoil database
General Comparison
S7055 (10.5%) Flat-Bottomed NACA-9412
Thickness (%) 10.5 11.979Camber (%) 3.548 8.998Trailing Edge Angle (%) 10.876 13.718Lower Surface Flatness 91.63 38.129Leading Edge Radius (%) 1.379 1.671Maximum Lift (CL) 1.203 2.096Maximum Lift Angle-of-Attack (deg) 9 12.5Maximum Lift-to-drag (L/D) 52.646 58.659Lift at Maximum Lift-to-drag 0.942 1.412Angle-of-Attack for Maximum Lift-to-drag (L/D) 5.5 3.5Stall Angle 9.0 12.5
Data from the Airfoil Investigation Database
Airfoil selection Final selection of the airfoil will be based
on XFOIL analysis Using refined weight estimates, a
specific lift requirement may be chosen Planform area will be selected based on
desired wing loading to maintain trainer like flight behaviors
Power restrictions of the selected motor will mandate the specific drag requirements
Launch and Recovery Concept Selection Catapult (or crossbow) style launch
platform Car-top launch setup Removable (leave-behind) Landing Gear Retractable landing gear
http://mm04.nasaimages.org/MediaManager/srvr?mediafile=/Size4/nasaNAS-9-NA/59991/0100743.jpg&userid=1&username=admin&resolution=4&servertype=JVA&cid=9&iid=nasaNAS&vcid=NA&usergroup=Marshall_-_nasa-9-Admin&profileid=41
http://www.uavs.biz/images/catapult_launch.jpg
Landing gear The landing gear shall allow the plane to
taxi and takeoff. The landing gear shall protect the plane
during takeoff, landing, and taxiing. The landing gear shall provide minimal
resistance on a grass runway.
Landing Gear Skids or Skis Floats (Pontoons) 2 or fewer wheels
(combination of wheels and skids)
3 wheels (traditional setup)
More than 3 wheels
http://www.oursbiz.com/Products/b/195/Pitts-S-2A-SP-002--987230.jpg
http://anjo.com/rc/aircraft/dr1/dr1.gear.1.jpg
Landing Gear Layout
http://www.jacksonrcclub.org/images/landing_gear_types.jpg
Landing Gear Selection Matrix
Conventional Tricycle
Skid Plates
Pontoon/Floats Skis
Drag 0 + + - - 0Ground Control 0 0 - - - 0Nose Over 0 ++ - 0 0Ground Loop 0 + - 0 0Cost 0 - + + -Load Handling 0 - + + 0Risk of Prop Damage 0 - - - 0Cargo Protection 0 - - - 0 0Operational Environment Restrictions 0 0 - - - - -Total 0 0 -5 -4 -3
Flight controls The flight control system shall allow the
aircraft to be flown like a basic trainer aircraft.
The control system shall maintain reliable control for at least 20 min.
The control system shall interface with the payload.
Flight Control Actuation Selection
Electric (servo)
Electric (stepper) Pneumatic Hydraulic EHA
Difficulty of Design 0 - - - --
Complexity 0 -- - - --Quick Connect compatible 0 0 -- -- 0
Weight 0 - - -- 0
Power output 0 0 + ++ ++
Maintenance 0 0 - - -
Cost (initial) 0 - 0 - --
Cost (sustained) 0 - 0 - -
Total 0 -6 -5 -7 -6
Propulsion The propulsion system shall provide
power for at least 20 min. The propulsion system shall provide
enough thrust to accelerate to flight speed.
The propulsion system shall be clean and easy to maintain.
The propulsion system shall be reusable.
Propulsion Concept SelectionRC Airplanes Rely on 1 of 3 Types of Propulsion
○ Gas
○ Glow/Nitro
○ Electric
Gas Propulsion Small Gasoline
Powered Engine Typically Two-Cycle Traditional RC
Aircraft Propulsion Method
Longer Flight Time with Gas RC Planes
Glow/Nitro (?) Fuel: Nitrous Oxide (?) Will not be considered for
this project due to fact that it is not manufactured in sizes not large enough for the scope of this project.
Electric Uses Batteries to
Power MotorBrushed DCBrushless DC
Due to Need for Batteries it has a Short Flight Time
Battery Capacity To find the required battery capacity to
operate each motor for 20 minutes the following equation was used:
Gas Critical Analysis
Electric Critical Analysis
All Motors Analyzed Were DC Brushless Two Different Typical Li-Po Battery Packs
Were Used
Propulsion Selection Matrix
Glow/Nitro Gasoline Electric Initial Cost * 0 0 Running Cost 0 0 + Controllability 0 0 + Power * 0 - - Weight 0 0 - -
Design Flexibility 0 0 ++
Fuel/Battery Consumption 0 0 0
20 min Flight Time * 0 0
Vibration 0 0 + Reliability - 0 ++ Maintenance 0 0 ++ Total N/A 0 5
*Glow engines of the size required would need to be a custom made part, as such they are not available for our use
P10232 System Design Concept Monoplane
Electric propulsion?
Standard cambered tail section
Under-cambered airfoil
Rectangular wing section
Top-mounted wing to the airframe
Conventional landing gear
Questions?P10232 TeamDaniel GravesJames ReepmeyerBrian SmaszczAlex FunicielloMichael Hardbarger
https://edge.rit.edu/content/P10232/public/Home