The design report

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The aircraft design phases went fairly smooth and there were no issues that could not be solved with advice from professors and senior students. Analyses on all aspects were conducted in various ways as progress into the design phases continued using numerical methods during initial stages and then more complex methods were used. CATIA was a major component during design and it was also used to estimate weights and CG position. Applications such as AVL had to be used to estimate the aircraft’s stability and aerodynamic performance in later stages of design where equations were not satisfactory due to design complexities. Fabrication of the aircraft was done in a shorter time frame than design itself but workload was manageable and the results were rewarding. A few obstacles we did come across were easily overcome with determination and hard work by the team. Weight estimations did not pan out as it was initially calculated and some errors in calculations were later brought to our attention. Landing gears gave some trouble during tests due to lack of strength and stability of the front right wheel but it was not a major issue and easily overcome by the pilot’s experience. Figure 1.05 Figure 1.06 Wing sweep and other complications were discarded due to the fact that they do not aid in increasing performance and the only real value they had was to increase aesthetics. It was in everyone’s interest to add a quarter circular shaped edges to the wing to ensure that the design stayed above other simple twin fuselage designs. The project was undertaken and completed successfully in the given time frame with the allowed materials completing all given tasks, although the weight limit exceeded. This was expected due to the design itself and the fact that there were two batteries, extra wiring, two motors and two fuselages which was a key point in this design.
Design Requirements and Objectives 2 The EPUAV project had a set of guidelines and mission objectives as a pathway for the successful completion of the project. Objectives To understand the process of aircraft design and developments To integrate or motivate to gain the knowledge of aerodynamics, structures, propulsion, flight dynamics etc. To develop student skills solving engineering problems To cultivate engineering teamwork Requirements Performance Endurance T >11 minutes Maximum level flight speed Vmax>18 m/s Minimum level flight speed Vmin
Page 1 and 2: EP-UAV Project 2009 iSpy Kate Rietd
Page 3 and 4: Preliminary and Detailed Design 4 S
Page 5: Executive Summary 1 iSpy is a twin
Page 9 and 10: Initial Sizing 3.1.2 Estimating air
Page 11 and 12: Airfoil design 3.1.4 Wing: Before t
Page 13 and 14: Tail: A symmetric airfoil with a th
Page 15: Empennage design 3.1.6 The dimensio
Page 19 and 20: Pod Layout 3.1.9 The pod of the air
Page 21: Weight estimation and Centre of Gra
Page 26 and 27: Figure 3.2.303 - Stability axis der
Page 30 and 31: CAD definition of the concept 3.2.5
Page 32 and 33: Figure 3.2.505: The vertical tail F
Page 34 and 35: Preliminary and Detailed Design 4 S
Page 36 and 37: Figure 4.1.109 Figure 4.1.110 The c
Page 38 and 39: Material type was chosen for each c
Page 40 and 41: The nose section of the fuselage co
Page 42 and 43: This part of the fuselage is the mo
Page 44 and 45: Empennage structure 4.1.3 Prelimina
Page 46 and 47: An ‘L’ shaped support was also
Page 48 and 49: Landing gear 4.1.5 Initial stages o
Page 50 and 51: Pod Structure 4.1.7 Figure 4.1.701-
Page 52 and 53: Fuselage fabrication 5.2 Since ther
Page 54 and 55: The servo holder plates in front of
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Landing gear fabrication 5.5 The de
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Fabrication of Pod 5.6 Like the fus
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Control surface fabrication 5.9 Ail
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Note: The weights taken after fabri
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It was here that the first problem
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Flight Test 6.2 The flight test aim
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Appendix 7 Appendix A - AVL files i
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TRANSLATE -0.450 0.384 0.00 # BFIL
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CLARK YM-15 - Re = 250000 Alfa Cl C
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Appendix C - Preparation of materia
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Appendix D - Control surface sizing
Page 82 and 83:
Conceptual Design Preliminary Desig
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The design report

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