Successfully reported this slideshow.
We use your LinkedIn profile and activity data to personalize ads and to show you more relevant ads. You can change your ad preferences anytime.
Design, Modification and
Fabrication of Small VTOL UAV
Under the guidance of
Prof. Gp-Capt Praveen Khanna, VSM
Akshat Sriv...
Road Map
Arrival at Design
Material Selection
Frame Design on
CATIA
Structural Analysis in
CATIA and ANSYS
Flow Analysis i...
Comparative Study and Design Selection
A) Fixed Wing
B) Rotating Wing
a) Vertical Take off
b) Fixed wing Vertical Take off...
Selected Design Comparison
Scorpid 500 UAV Simple Tilt Rotor Configuration
Quad Rotor Configuration
 MATERIAL SELECTION
 DESIGNING THE FRAME
 COMPONENTS OF THE FRAME
 SHAPE
 PLACEMENT OF ELECTRONIC COMPONENTS
DEFLECTION
PRINCIPAL STRESS
VON MISES STRESS
MAX. SHEAR STRESS
PITCH DIRECTION
YAW DIRECTION
ROLL DIRECTION
CONTROLLING PITCH/ROLL
CONTOLLING YAW
CONTROLLING ALLITUDE
THRUST VS VOLTAGE DROP
VELOCITY VS THRUST DISC LOADING VS PROPELLER RADIUS
ANGULAR VELOCITY VS VOLTAGE DROP
VELOCITY CONTOURS
STATIC PRESSURE CONTOURS
TURBULENT K.E
DYNAMIC PRESSURE
RADIAL VELOCITY
VELOCITY PLOT
PRESSURE PLOT
TOTAL PRESSURE PLOT
 Quad copter booms were made using hollow square cross section
Aluminium bars.
 Central hub for placing control board an...
System Overview of Quadcopter
Electronic components Selection
• Brushless motors:
1800kv and 14.8 Amps
• ESC:
30 A constant current
40 A Burst current
•...
TRANSMITTER
Model: FS-CT6B
Mode: 2
Channel: 6
Frequency band: 2.4GHz
Modulation Type: Spread Spectrum
Software: T6Config.E...
ESC calibration and programming
KK Multicopter Control Board
 Stabilizes the flight.
 Take signal from three gyros(roll ,
pitch , yaw) and feed informat...
Vibration Analysis
 To determine the natural frequencies of
the quad rotor the following Equation for
the Strouhal number...
Vibration Isolation
Passive Isolation
Active Isolation
Vibration Control has been done by:
• Passive Isolators
• Materials...
First Mode
Modal Analysis
Second Mode
Third Mode
Fourth Mode
Fifth Mode Sixth Mode
Seventh Mode Eighth Mode
Future Works
 Improvement of Strength to weight ratio.
 Payload Capacity.
 Additional Integration of Electronic equipme...
Conclusion
 Structural analysis, flow analysis and modal analysis has been done using CATIA and ANSYS
softwares .
 Perfo...
THANK YOU
major project ppt
Upcoming SlideShare
Loading in …5
×

major project ppt

  • Be the first to comment

major project ppt

  1. 1. Design, Modification and Fabrication of Small VTOL UAV Under the guidance of Prof. Gp-Capt Praveen Khanna, VSM Akshat Srivastava (07) Aseem. H .Salim (12) Shaik Ibrahim (37) T Shan (38) Stanley Boswell (40) Tasdeeq Rahim Sofi (44) Submitted by:
  2. 2. Road Map Arrival at Design Material Selection Frame Design on CATIA Structural Analysis in CATIA and ANSYS Flow Analysis in ANSYS Fabrication Testing
  3. 3. Comparative Study and Design Selection A) Fixed Wing B) Rotating Wing a) Vertical Take off b) Fixed wing Vertical Take off A. Two rotor design 1. Transverse rotor design 2. Tilt rotor design ( Bell Boeing V-22 Osprey) B. Three rotor design ( Tricopter) C. Quad copter design • Two rotor design • Quad rotor Design Rotating wing configurations ( Vertical Take-off) Selected the desired configurations Two major configurations of UAV
  4. 4. Selected Design Comparison Scorpid 500 UAV Simple Tilt Rotor Configuration Quad Rotor Configuration
  5. 5.  MATERIAL SELECTION  DESIGNING THE FRAME  COMPONENTS OF THE FRAME  SHAPE  PLACEMENT OF ELECTRONIC COMPONENTS
  6. 6. DEFLECTION PRINCIPAL STRESS VON MISES STRESS MAX. SHEAR STRESS
  7. 7. PITCH DIRECTION YAW DIRECTION ROLL DIRECTION CONTROLLING PITCH/ROLL CONTOLLING YAW CONTROLLING ALLITUDE
  8. 8. THRUST VS VOLTAGE DROP VELOCITY VS THRUST DISC LOADING VS PROPELLER RADIUS ANGULAR VELOCITY VS VOLTAGE DROP
  9. 9. VELOCITY CONTOURS STATIC PRESSURE CONTOURS TURBULENT K.E DYNAMIC PRESSURE
  10. 10. RADIAL VELOCITY VELOCITY PLOT PRESSURE PLOT TOTAL PRESSURE PLOT
  11. 11.  Quad copter booms were made using hollow square cross section Aluminium bars.  Central hub for placing control board and battery are made using square Aluminium plate.  Aluminium bars and Aluminium plates were drilled to hold them together  Landing gears are made using bended plastic tubes and attached at the edges of each booms. FRAME CONSTRUCTION SOLDERING ELECTRONIC COMPONENTS  Soldering has been done on different electronic components for fixing bullet connectors.  Male bullet connectors have been soldered on 3 wires of each motor and female bullet connectors are soldered to 3 wires of ESCs ,which are in turn connected with battery. FABRICATION  Assembly of the frame using nuts and the bolts.  Attaching motor and propeller to the frame using the mount.  Attaching landing gear below each motor using the same nuts and bolts of corresponding motor.  Positioning of the Flight control Board on the top plate using nylon mounts.  Connect the motors and electronic speed control unit to the battery using wire harness and the control board connection to the Flight control board.
  12. 12. System Overview of Quadcopter
  13. 13. Electronic components Selection • Brushless motors: 1800kv and 14.8 Amps • ESC: 30 A constant current 40 A Burst current • Transmitter Flysky CT6B transmitter is used • Reciever Flysky R6B is used • Control board: KK Multicopter- version5.5 • Battery 4400mah 30C is used. • Wire harness
  14. 14. TRANSMITTER Model: FS-CT6B Mode: 2 Channel: 6 Frequency band: 2.4GHz Modulation Type: Spread Spectrum Software: T6Config.EXE
  15. 15. ESC calibration and programming
  16. 16. KK Multicopter Control Board  Stabilizes the flight.  Take signal from three gyros(roll , pitch , yaw) and feed information into Atmega IC.  Take signal from RX and feeds into the IC via aileron, elevator, throttle and rudder pin. Specifications: Functions: Update firmware for Xcopter using kk Multicopter flashing tool.
  17. 17. Vibration Analysis  To determine the natural frequencies of the quad rotor the following Equation for the Strouhal number was used: 𝑆𝑡 = (𝑓∗𝐿)/𝑣 Where, St is the Strouhal number, f is the vortex shedding frequency of the propeller, and v is the velocity of the flow past the propeller. The Strouhal number is an experimentally determined quantity derived in wind tunnel testing and a quantity of 0.2 is acceptable in our project. No. of Blades Length(m) ½ Radius(m) Radius(m) 2 0.018 0.127 0.254
  18. 18. Vibration Isolation Passive Isolation Active Isolation Vibration Control has been done by: • Passive Isolators • Materials used – Rubber paddings – Nylon screws
  19. 19. First Mode Modal Analysis Second Mode Third Mode Fourth Mode
  20. 20. Fifth Mode Sixth Mode Seventh Mode Eighth Mode
  21. 21. Future Works  Improvement of Strength to weight ratio.  Payload Capacity.  Additional Integration of Electronic equipments.  Autonomous Control System.  Improved Range and Endurance.  Design Improvement
  22. 22. Conclusion  Structural analysis, flow analysis and modal analysis has been done using CATIA and ANSYS softwares .  Performance plots and Vibration plots are made using MATLAB.  All electronic components like battery, motors, electronic speed control units were selected as per the requirements and calculations done.  KK Multicopter controller board which forms the heart of the design was integrated to ensure stability to the design with the help of inbuilt Accelerometers and Gyros.  Fabrication process began with the attachment of the various structural frame components like the main spar, four spars, main top plate, and bottom plate.  The integration and the calibration of all electronic speed control units and the multi controller board.  A crucial deficiency was that, the team members did not have experience working from the electronics point of view. Howsoever, a lot of time was dedicated to the study of the working of the electronic components and the way of calibrating each of them.
  23. 23. THANK YOU

×