1. Replicating the 1903 Wright Flyer

2. Introduction Sir George Cayley Otto Lilienthal Alphonse Penaud
Conventional configuration
Otto Lilienthal
Airfoil data, first pilot
Alphonse Penaud
Rubber powered models
Octave Chanute
Pratt truss

3. Wright Brothers Control centric approach Wing warping for roll control
First wind tunnel tests
Adverse yaw
Canard for pitch control

4. The Wright approach Wing warping tested on 1899 kite
1901 glider was a disappointment
Wind tunnel testing leads to 1902 glider
First powered flight, 1903

5. Problems in replication
Instability
Pitch, CG behind NP
Spiral mode, Anhedral
Control
Smaller tail volumes
Constructional
Practical limits due to scaling down

6. Strategy

7. Strategy Exploring a/c Making gliders Literature study
Proposed solutions
Making gliders
Material selection
Practical limits on fabrication
Implementation of control mechanisms

8. Propulsion Market survey for Test the setup Contra-rotating pushers
Belts, pulleys and shafts
Engine
Test the setup

9. Glider Specifications
1:12 scaled down model
Wing Span 1.02 m
Length 0.54m
Canard area 6.3% of wing area, m2
Rudder area 0.01 m2
Weight 0.15 Kg
Ballast weight Kg
Wing loading 0.11 kg/m2

10. Glider

11. Glider Experience Material selection
Central carbon fibre box supporting
Wing
Canard and rudder
Engine
Landing gear

12. Central Box

13. Glider Experience Material selection Balsa wood used for Wing ribs
Canard and rudder
Vertical struts

14. Glider Experience Monokote for wing covering
Slotted ribs for front spar
Joints
Strut-spar pin joints replicated
Pins lashed to spars and struts
Rigging with twine thread

15. View of joints

16. Glider Experience Controls Steel wire for wing warping
Flexible joints in rear spar for wing warping
Complete canard moved for pitch control
(unlike original variable camber)

17. Weight estimation Controls part
4 servos + Receiver+ Battery pack + Miscellaneous
160gm gm gm gm =360 gm
Propulsion part
Engine + Mount + Shafts, Belts, Pulleys + Fuel + Misc gm + 150gm+ 300gm+ 250gm+ 65gm =1100 gm
Landing gear = 150gm
Structure part
Carbon fiber composite + Balsa + Misc
450gm gm + 250gm =1000gm
Total Maximum weight = 3 kg
Wing loading with this weight = kg/m2

18. Thrust and Power Estimation
Max thrust required at min Cl/Cd = 12 N
Power required at this Cl/Cd is 120 W
Engine of 250 W at rpm
Two 10X6 props at 8000 rpm give 15 N thrust
Thrust in lbs = 2.83x10-12 x RPM2 x D4 x Cp x (P/29.92) x (528/(460+T))

19. Propulsion Electric motor Less weight No starting problems
Ease of maintenance
Large battery weight (Can be used as ballast)
Lesser heating problems

20. Propulsion Wankel IC engine High power Less fuel weight
Cooling problems ?

21. Propulsion Belt pulley system Propeller shaft mounting replicated
Contra-rotating propellers ?

22. Side view transmission system
9.3 cm
4 cm
11 cm
6 cm
25 cm

23. Front View
23.5 cm
12 cm
5 cm
39.4 cm

24. Unsolved problems Roll-yaw coupling ? Asymmetric yawing moment ?
Pitch SAS using rate gyro?
Tail and canard volumes ?
Anhedral ?
Landing ?
Twisted belt drive ?

25. Belt, Pulleys, Bearings, Propeller
Cost Estimate
Carbon fibre
2000
Balsa
500
Engines
8000
Belt, Pulleys, Bearings, Propeller
2900
Servos
4000
Miscellaneous
Total
17,900

26. Acknowledgements
Prof. K. Sudhakar, IIT Bombay
Dr. H. Arya, IIT Bombay