The design report

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Figure 3.2.303 – Stability axis derivative output for zero degree angle of attack. The stability axis derivatives for all values of α also provided us with values of CL and CD that were graphed against each other. This graph was compared to the theoretical graph of CL vs CD and they matched to a reasonable extent.
Figure 3.2.304-Stability axis derivatives AVL was then used to run a steady level flight case with parameters set to meet an average cruise condition. The total weight was set at 3.6kg, α was set to 0°, air density was set to 1.225kg/m 3 , velocity was set to 18ms -1 and the acceleration due to gravity was set to 9.81ms -2 . The resulting loading on the aircraft was plotted as shown in figure 3.2.305. This shows the aerodynamic loading on the exposed surface areas of the wing and empennage. The wingtips showed high loads acting on it and thus it was recommended by the stability team to add strength to this area by implementing a carbon rod or any other suitable method. The team in charge of wing decided to add a ply outline along the leading edge and also a 6mm carbon rod was placed through the ends of the wing. This ensured a stable and strong structure to the high load bearing wing.
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 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 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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