1. Aircraft Design Process

2. Overview Design process Design reasoning Problems solving
construction methods and specifications
Flight test
DESIGN
BUILD
FLY

3. Design Process DESIGN Conceptual Design Preliminary Design
Mission
Requirements
Computational estimation
Conceptual
Design
Computational estimation
Preliminary
Design
Rebuild
Detailed design & construction
Flight-testing

4. Critical Specifications
DESIGN
Critical Specifications
Blended wing/body aircraft
10 cc engine
Remote controlled by human pilot
Must carry payload of four Dick Smith Gravy packets (1.6kg total weight)
Aspect ratio ≥ 2.0
Project cost ≤ $1000

5. Desirable Specifications
DESIGN
Desirable Specifications
Highest possible wing loading
Minimum take-off weight
Minimum planform area
Stable flight in all conditions

6. Configuration studied Standard boxwing C-wing Closed box-wing
DESIGN
Configuration studied
Standard boxwing
C-wing
Closed box-wing

8. Computational Design Solid Works – airframe design, weight and balance
Desktop Aerodynamics – aerodynamic prediction
Flight Sim – flight simulation and performance estimation

9. Box-wing configuration advantages
DESIGN
Box-wing configuration advantages
Minimal planform area
End caps improve wing strength
Fully effective upper wing surface
less run way area

10. Tractor configuration Move C.G forward
DESIGN
V-tail selected
Ease of construction
Comparatively light
Tractor configuration
Move C.G forward
Propeller intake clear of wing interference

11. DESIGN
INITIAL DESIGN
Upper wing constructed from ply spar and balsa ribs, surfaced with solar film
Foam core lower wing surfaced with balsa sheet an solar film
V-tail made up from balsa sticks and fibre-glassed to 12mm diameter carbon boom

12. DESIGN
INITIAL DESIGN
Bulkheads fore and aft of payload made from light ply
Firewall located and set at specific angle relative to wings
Steel wire (3mm) folded and cut for undercarriage

13. Detailed design and construction Detailed calculations were completed
BUILD
Detailed design and construction
Detailed calculations were completed
Design continually modified as practical problems arose during construction

14. BUILD

15. Problems Faced and Fixed
DESIGN
Problems Faced and Fixed
PROBLEM
Structural joints introduced weak points
SOLUTION
Structure rebuilt with 6:1 ratio joints

16. Tail boom replaced, aluminium plate
DESIGN
PROBLEM
Weak materials
SOLUTION
Tail boom replaced, aluminium plate
undercarriage

17. Rebuilt fuselage with more efficient payload
DESIGN
PROBLEM
Too large frontal area
SOLUTION
Rebuilt fuselage with more efficient payload
configuration
front

18. Chord and span increased
DESIGN
PROBLEM
Wing area too small
SOLUTION
Chord and span increased

19. Fuselage not strong enough
DESIGN
PROBLEM
Fuselage not strong enough
SOLUTION
Fibre-glassed fuselage surfaces

20. BUILD
REVISED DESIGN
Wings constructed by a hot-wire cut foam core, surrounded with balsa sheeting
Spar laminated from 2 pieces of 3mm birch ply wood with carbon fibre between them
V-tail of slightly increased area was fibre-glassed to a 7/8” diameter carbon tube

21. BUILD
REVISED DESIGN
Wing/Body fillets sculpted from foam and fibre-glassed for strength and durability
1.5o right side thrust and 1.5o down thrust were built into the engine mount
4mm Aluminium undercarriage bought-off-shelf and re- shaped to suit aircraft

23. Specifications Span: 1.4m Length:1.5 Area: ~ 0.58m2 (900in2) Mass:4 Kg
BUILD
Specifications
Span: 1.4m
Length:1.5
Area: ~ 0.58m2 (900in2)
Mass:4 Kg
Engine: Thunder Tiger 61 Pro (10c.c.)
Servos: 5
Channels: 5

24. Test flight FLY Pre-flight Ground Run Engine Adjust mixture
First Flight
Zero payload flight
Adjust trim for straight flight

25. Test flight FLY Second Flight Confirm trimming Third Flight
Confirm flight characteristics with payload
Fuel consumption check
Fly actual circuit

26. Thankyou