The design report

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Wing planform design 3.1.5 The wing shape had to be a new idea. The group decided against a rectangular wing as it would have made the iSpy look ordinary. A wing with curved edges was most suitable to make the iSpy more visually pleasing. A high wing configuration was chosen due to ease of fabrication. It was decided not to have sweep, dihedral or winglets due to the added complexity with fabrication and also due to the fact that the additions to lift would be negligible in low speed flight. According to the initial plan, the wing chord had to be as small as possible. A wing loading of 7 kg/m 2 gave a chord length of 22cm. This was still not very thin but the professor suggested that an aspect of over 10 would be too high. The wing chord had to be increased to bring the aspect ratio close to the suggested figure of 8-9. After a lot of calculations to meet the specified criteria, a chord length of 26cm was chosen. c (variable) b (fixed) AR Area Weight (fixed) W/S 0.21 2.3 11.39909035 0.464072118 3.6 7.75741498 0.22 2.3 10.90212414 0.485226542 3.6 7.419214917 0.23 2.3 10.44845137 0.506295126 3.6 7.110477303 0.24 2.3 10.0326608 0.527277868 3.6 6.827519635 0.25 2.3 9.650206988 0.54817477 3.6 6.567248612 0.26 2.3 9.297243807 0.568985832 3.6 6.327046825 0.27 2.3 8.970494923 0.589711052 3.6 6.104684636 0.28 2.3 8.667152053 0.610350432 3.6 5.898250925 0.29 2.3 8.384794267 0.630903971 3.6 5.706098178 Span 2.3 m Chord 0.26 m Area 0.56 m 2 Wing loading 6.32 kg/m 2 Aspect ratio 9.29 The sizing chosen above met all criteria set by the project guidelines and suggestions by the professor. This however, changed the look of the iSpy meaning that an exact replica of the global flyer wouldn’t be possible.
Empennage design 3.1.6 The dimensions of the vertical and horizontal tail planes were determined using the following equations: Horizontal Surface: Vertical Surface: In order to make these calculations the following assumptions and values were calculated: Mean wing chord (c): 0.26 Wingspan (b): 2.3 Wing Area (c*b): 568986 Volume co-efficient (
Page 1 and 2: EP-UAV Project 2009 iSpy Kate Rietd
Page 3 and 4: Preliminary and Detailed Design 4 S
Page 5 and 6: Executive Summary 1 iSpy is a twin
Page 7 and 8: Design Requirements and Objectives
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: Tail: A symmetric airfoil with a th
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
Page 56 and 57: Landing gear fabrication 5.5 The de
Page 58 and 59: Fabrication of Pod 5.6 Like the fus
Page 60 and 61: Control surface fabrication 5.9 Ail
Page 62 and 63: Note: The weights taken after fabri
Page 64 and 65:
It was here that the first problem
Page 66 and 67:
Flight Test 6.2 The flight test aim
Page 68 and 69:
Appendix 7 Appendix A - AVL files i
Page 70 and 71:
TRANSLATE -0.450 0.384 0.00 # BFIL
Page 72 and 73:
CLARK YM-15 - Re = 250000 Alfa Cl C
Page 74 and 75:
Appendix C - Preparation of materia
Page 76 and 77:
Appendix D - Control surface sizing
Page 82 and 83:
Conceptual Design Preliminary Desig
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The design report

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