fall 2020 midterm abdias josue perez, damian anthony clogher, midterm... · pdf file...

Click here to load reader

Post on 27-Feb-2021




0 download

Embed Size (px)


  • 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


  • 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/

    https://www.servocity.com/servo-winch-pulley-h25t-3f-spline/ https://www.servocity.com/hsr-2648cr-servo/

  • Testing Purpose 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 ●

    ● ●

  • Schedule



    Deploy/Recovery Mechanism

    November December

    Week 6: Determine sensor manufacturing plan Week 7-8: Sensor manufacturing

    Week 9: Sensor Flight testing Week 10: Integrate test results into aircraft design

    Week 6-7: Preliminary design study Week 6-9: Initial Prototype Aircraft manufacturing

    Week 10: design iterations based on sensor testing results

    Week 6-7: Mechanism Conceptual design Week 8-9: Prototype manufacturing

    Week 9: Preliminary design Week 10: Test proof of concept of towing capability

  • Question?

    Team Website: DBF 2021 Rules:

    More Information

    http://projects.eng.uci.edu/projects/2020-2021/design-build-fly https://www.aiaa.org/dbf