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Fall 2020 Midterm Presentation
Abdias Josue Perez, Damian Anthony Clogher, Gisselle Orozco, Leo Zheng, Rex Zehao Guo, Sarah-Claire De Luna Santos
● Problem Definition and Objective (by Damian)
● Sensor Design (by Leo)
● Aircraft Design (by Sarah)
● Mechanism Design (by Rex)
● Verification Plan (by Abdias)
● Timeline and Schedule (by Gisselle)
Presentation Outline
DBF Problem Definition
○ Design and Manufacture an aircraft to enter in the 2020-2021 AIAA Design/Build/Fly competition
○ Aircraft is designed to achieve best score overall○ Aircraft will carry and tow a sensor package and complete all mission requirements
■ Mission 1: 3 laps w/ no payload in 5 min■ Mission 2: 3 laps w/ payload(senor in shipping containers) in 5 min■ Mission 3: Deploy and recover sensor in 10 min (as many laps as possible)■ Ground Mission: Load and unload payload in the least time possible
○ Our score analysis shows score is maximized by carrying the max number of sensors or carrying 1 sensor. We decided to carry 1 sensor.
○ Constraints: 200 Wh battery capacity, 5 foot wingspan, sensor must be fully contained, sensor must be at least 4 times longer than its diameter.
Scoring Analysis
Sensor Design ● Mission 3 focused:
○ Maximize sensor weight, sensor length, and number of laps
○ Equipped with 3 LED lights controlled via tow cable● Length
○ Directly related to■ Length of fuselage■ Length of the cable (10 time longer than
sensor length)○ The length of sensor is estimated to be about 20
inches long■ Prevents towing cable to be extremely long
(Further testing needed)■ Prevents fuselage to be too long
● Negatively impact landing gear height
Sensor Design
● Determine power needed when cruising
● finalize max weight of sensor and fastest velocity until we exceed battery capacity constraint (estimated to be 5 lb and 12-14 laps)
● Mission 3 focused:○ Maximize sensor weight, sensor length, and number of
laps○ Equipped with 3 LED lights controlled via tow cable
● Weight○ Ensure sensor does not negatively impact the stability
of the aircraft during deployment○ Adding small lifting surfaces to counteract weight○ Process of sensor weight estimation
■ Given battery constraint and the fact that flights need to be maintained in 10 min, the power needed during cruising is limited
■ Aircraft weight assumed by Ws (Wb + Wst + Ws) [assuming Wst = Wb]
■ Determine velocity of aircraft required to create enough lift from sensor
● Directly related to number of laps■ Combine weight/velocity of aircraft, historical
DBF profile drag coefficient, determine both profile/induced drag by aircraft and sensor
Aircraft Design● Constraints
○ Maximum allowable wingspan: 5ft
○ Takeoff field length: 100ft
○ Must carry: sensor in shipping container, shipping container simulators, deploy and
recovery mechanism
○ Drag & Structural Weight
○ Structural weight determined by sensor weight■ Number of sensors needed to carry
● More sensors = increased weight
○ Expected 12-14 laps with speed of 75 ft/s
● Conventional Monoplane○ 5ft wingspan
○ Weight: 11 lbs■ 3 lb battery. 5 lb sensor, 3 lb structure
○ Max battery capacity: 200 watt-hours
○ Tricycle landing gear configuration■ Avoid interference from tail wheel
○ Tractor propeller configuration■ Reduce interference with sensor deployment
● Still need to be considered○ Single/multiple motors
○ Test stability and control
● Modify plane from last year○ Saves time (the sizing of the
aircraft meets our objective
this year)
○ Add container storage
○ Add deploy and recovery
mechanism
Deploying/Recovery Mechanism Requirement
● Light weight● Easy to install● Need enough torque to retract sensor
Implementing Design● Single continuously rotating servo and winch pulley
○ Produces about 130 oz-inches○ Commercial off the shelf component (easy access)
■ Need to be purchased● 200 inch of tow cable
Still need to be considered● Deployment strategy to ensure not negatively impacting
CG of airplane during deployment● Securely retract sensor to the stowed position● Further testing needed● Hatch door
https://www.servocity.com/servo-winch-pulley-h25t-3f-spline/https://www.servocity.com/hsr-2648cr-servo/
TestingPurpose of testing
● Confirm our assumption○ Sensor drag and lift○ Test sensors with different weights
■ Towed by existing aircrafts○ Cable length limits
● Help revising design iterations○ Deploy/retract mechanism○ Sensor light control○ Sensor lifting surfaces
Goal: figure out maximum senso weight and length that are flyable.
Timeline●
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Schedule
Sensor
Aircraft
Deploy/Recovery Mechanism
November December
Week 6: Determine sensor manufacturing planWeek 7-8: Sensor manufacturing
Week 9: Sensor Flight testingWeek 10: Integrate test results into aircraft design
Week 6-7: Preliminary design studyWeek 6-9: Initial Prototype Aircraft manufacturing
Week 10: design iterations based on sensor testing results
Week 6-7: Mechanism Conceptual designWeek 8-9: Prototype manufacturing
Week 9: Preliminary design Week 10: Test proof of concept of towing capability
Question?
Team Website: <http://projects.eng.uci.edu/projects/2020-2021/design-build-fly>DBF 2021 Rules: <https://www.aiaa.org/dbf>
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