This document summarizes a student aircraft design project to design a cargo plane. The objectives are to design a cargo plane to carry 600,000 kg over 4,000 km with a cruise speed of 850 km/h. The preliminary design was completed and included collecting comparative data, selecting parameters, estimating weights, selecting engines and airfoils, and creating a wing layout. Structural analysis was performed on the wing and fuselage.

1. AIRCRAFT DESIGN PROJECT-2…
EVALUATION OF CARGO PLANES…
DHANASEKARAN.K
ELAKKIYA.G

2. OBJECTIVE:
Design a cargo aircraft by comparing the data and
specifications of present aircrafts in this category.
Design Requirements:
Cargo of weight - around 600000 kg
Design range -4000 km
Cruise speed -about 850 km/h.

3. AIRCRAFT POSSESS;
High Wing,
 Tricycle landing gear,
Twin tail arrangement,
Turbofan Engine.

4. DESIGN PROCESS-AN OVERVIEW:
•Conceptual design studies
• Preliminary design studies
• Detail design studies
The preliminary design has been done of
cargo aircraft

5. preliminary design:
Collection of comparative data
 Selection of aircraft parameters
 Preliminary weight estimations
 Selection of Power plant
 Airfoil selection, flaps
 Wing layout
 Critical performance parameters
 3 view diagram

6. V-n Diagram:

7. V-n Diagram…..
IMPORTANT VELOCITIES:
The main velocities that r plotted in the V-n
diagram are:
I.
Stall Velocity
II. Design Maneuvering Velocity
III. Design Cruise Velocity
IV. Design Dive Velocity

8. V-n Diagram…..

9. GUST AND MANEUVERABILITY
ENVELOPES
"outside the envelope”

10. STRUCTURAL ANALYSIS OF
WING
“Box Beam (distributed flange)
concept-built-up or integral
construction”

11. Advantages:
Simpler construction & assembly
 Reduced sealing/jointing problems
 Reduced overall assembly time/costs

12. SPAR:
Front spar at 15% of chord,
Middle spar at 45% of chord and
Rear spar at 70% of chord

13. SPARS

14. FUSELAGE:

15. FUSELAGE STRUCTURAL ANALYSIS

16. STRINGERS:

17. DETAILED DESIGN REPORT