The design report

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Pod Structure 4.1.7 Figure 4.1.701-Pod detail design The internal structure of the pod is made fairly simple with only three circular rings. There is a plate going through the centre of the circular ribs to hold the structure together and to let the 4 blocks sit on it. The 4 longerons helped to straighten the structure of the pod too. The 4 brown blocks shown in figure () had holes running through them to ensure that the pod had three different positions to move. This is another way we can adjust the position of the cg with. Wing rib extensions will be outside the pod and they will be held together with two 110mm bolt. The yellow plate at the bottom with a big hole is for the camera to sit on. The lens of the camera would be placed on top of the hole. The hole was deliberately made bigger to avoid any obstruction of the camera’s sight. Payload arrangement 4.1.8 The pod was the designated payload. A spy camera was placed near the front to capture in flight video according to the mission. Additional weight was to be placed inside the pod to make sure total payload weight is 500 grams. The additional weights were to be placed just underneath the cg position so as to not to affect it. The weights could also be placed in the fuselages as balancing weights if the cg position was to be altered. The position of the pod could be changed as different holes could be used to screw the pod onto the wing. This design idea meant that 3 different positions of the pod were possible underneath the wing. This could also be used to alter the cg position if required. The additional weights were to be stuck on with double sided tape. Figure 4.1.701 shows a detailed view of the structure of the payload holder
Structural Analysis 4.2 It is common practice in aircraft projects to check the integrity of the structure. The group was introduced to NASTRAN to check whether the internal structure created in CATIA would be able to carry the loads in flight. Due to time limitations, this couldn’t be done. The group had to rely on advice from experienced teaching assistants and the professor. The structure was discussed and with minor changes, the professor was confident that it would be able to carry the calculated loads. Later on during fabrication and testing, it was discovered that the structure was reliable and caused no problems at all. Fabrication 5 Preparation for materials 5.1 The laser cutting machine available in the laboratory read .dxf files. All individual CAD parts had to be converted to .dxf format in CATIA and then all components had to be arranged in AutoCAD according to the type of material they were to be cut from. All components were converted to .dxf files and then sorted according to material type. Ply, pawlonia and balsa sheets were sorted for cutting. Carbon, ply and pine rods were also sorted and selected. All tools were collected and placed in one section of the lab. Superglue, AB glue and white glue were to be used for different purposes. The group faced many problems in terms of limitation of available materials which meant that every time an alternative had to be found. Rod, screw hole sizes had to be continuously changed in the CAD parts due to this. Refer Appendix C Figure 5.1.01
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 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 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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