Maximizing Fixed Wing UAV Flight Time Through Computer Simulation. Thousand Oaks High School AP Research STEM

Transcription

1 Maximizing Fixed Wing UAV Flight Time Through Computer Simulation Thousand Oaks High School AP Research STEM

2 Background UAV = Unmanned Aerial Vehicle Drone Quadcopter = Helicopter Fixed wing = Airplane

3 Problems Most UAVs short flight time Around +/- 30 minutes Lowers applicability

4 Experience and Idea Homebuilt models Aerodynamic design Electronic systems Applicability

5 Introduction - Applications Government Military Police Surveillance 3D Mapping Disaster Mapping Crop Surveys

6 Introduction - Aerodynamics Airfoil = shape of wing Required for lift and aero flight Thickness = Camber NACA 2411

7 Introduction - Electronics Brushless motor > Brushed Less friction Propellor ESC (Speed controller)

8 Introduction - Electronics Lithium Polymer Battery High energy density Lightweight Scalable (sizes)

9 Introduction - ECALC Online motor database All electronics for UAV Motor brands Returns values in speedometer graphs Flight time Thrust to weight ratio Simulation example

10 Introduction - XFLR5 NACA airfoils Wing design Airflow and viscous fluid dynamic analysis Virtual wind tunnel Simulation example

11 Objectives and Research Question Design UAV for surveillance, police, military Flight time minutes Thrust to weight > 1:1 Stable, simple

12 Hypothesis ECALC = minute flight time XFLR5 = stable delta design with NACA 2411

13 Materials Computer ECALC Simulation XFLR5 Simulation website (for CG calculation)

14 Methods - ECALC Set motor to Scorpion HKIII Control all variables Change prop size and pitch Record returned FT and TW data for each prop size Increase battery size for large TW Data table example

15 Methods - XFLR5 Aircraft shape = delta wing Center of gravity 115mm leading edge (from CG website) Run analysis -5 to 15 degrees angle of attack at 35 mph set speed

16 Results - ECALC Raw ECALC Data

17 Results - ECALC Propellor data (20 inch)

18 Results - XFLR5 3D analysis and airflow diagram Cp Static data

19 Results - XFLR5 CL vs CD CL vs Alpha (AoA) Cm vs Alpha (AoA) CL/CD vs Alpha (AoA)

20 Results - XFLR5 Pitching Moment Stable: negative slope X-intercept = negative Further Analysis

21 Discussion 65.8 minute flight time. More efficient than higher Kv motor 1.08:1 thrust to weight ratio = low, still applicable Change battery 20,000 mah High FT with higher TW Custom Electronics

22 Discussion Predictable Cp results at diff. AoA Smooth airflow Stability analysis for negative x intercept

23 Sources of Error ECALC: Simulation: controlled Missing a prop setup Value input Actual aircraft weight XFLR5: Simulation: controlled Analysis not real life situation Data accuracy through stability analysis

24 Conclusion Hypothesis proved correct 65.8 min :1 Valid for surveillance etc. Further work Stability analysis Build

25 Further Work Stability analysis Test airframe Different scenarios Self stable airfoil Acts as balancing force Custom Acts as tail wing

26 Further Work Build test model and wind tunnel Small scale Large scale flyable Electronics from ECALC Symmetrical flight pattern

27 Acknowledgements Mr. Ed Hammerslag Mr. Scott Davis Dr. Nikki Malhotra Mr. Jeff Lewis Mrs. Tasha Beaudoin

28 Maximizing Fixed Wing UAV Flight Time Through Computer Simulation Thousand Oaks High School AP Research STEM

29 References Gabriel, D. L., Meyer, J., & Plessis, F. D. (2011, September 15). Brushless DC Motor Characterisation and Selection for a Fixed Wing UAV. IEEE Review. Kostić, Č. L., & Rašuo, B. P. (2016). AERODYNAMIC AIRFOIL AT CRITICAL ANGLES OF ATTACK. Military Technical Courier / Vojnotehnicki Glasnik, 64(3), doi: /vojtehg (n.d.). Basic Design of Flying Wing Models. From: (n.d.). XFLR5 and Stability Analysis. From: