Fall 2020 Midterm Abdias Josue Perez, Damian Anthony Clogher,...
Transcript of Fall 2020 Midterm Abdias Josue Perez, Damian Anthony Clogher,...
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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