The design report

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The following data was obtained from the propulsion test. The maximum thrust obtained was 1.424 kg. Since we had to motors, the thrust would be doubled to 2.848 kg. Force (g) Current (A) 1600 1400 1200 1000 800 600 400 200 0 Force in grams rpm Current (Amp) Current drain 119 2405 37.3 0 425 4625 33.37 3.93 637 5344 28.17 9.13 890 6020 23.76 13.54 1124 6833 16.43 20.87 1382 7450 8.8 28.5 1424 7550 7.8 29.5 Propulsion Test (Thrust) 0 1000 2000 3000 4000 5000 6000 7000 8000 Propeller rotation speed (rpm) Figure 3.2.103 - is shows how the thrust increases with increasing rpm 35 30 25 20 15 10 5 0 Propulsion Test (Current Drain) 0 2000 4000 6000 8000 Propeller rotation speed (rpm) Figure 3.2.104 - shows how the current drain increases with increasing rpm
Weight estimation and Centre of Gravity (cg) estimation 3.2.2 Weight Estimation: Estimation of weights was done using the formulae provided to us by Dr. Yu during the conceptual design phase. The formulae used were in imperial units. A conversion factor was used to convert pounds to kilograms. The weight added by glue and wiring were estimated from the aircrafts made by previous batches. Exact measurements of battery and the motor weights were taken from the weighing scale. Weight of the aircraft was then checked using CATIA during the detail design phase. Densities of materials used were inserted into CATIA which then provided us slightly more accurate results. Note that the weights of servos were negligible and hence were included in the wiring. Part Formula Lb Kg Wing 0.14676·Sw 0.4852·ARw 0.7082·(100 t/c) - 0.2210 0.942617 0.42756 Fuselage (x2) 0.07092·(Wm/Hm) 0.04832·L 1.6566 1.77084807 0.803238976 Horizontal tail 0.1570·Sh 0.1939 0.16958158 0.076920509 Vertical Tail (x2) 0.1393·Sv 0.6729 0.22111 0.10029 Landing gear Wto·0.07 0.5555648 0.251998638 Propellers (x2) 3.0346×10 -6·D 3.76468 0.11023 0.1 Glue Wiring Motors (x2) 0.88185 0.4 1.10231 0.5 0.66139 0.3 Batteries (x2) TOTAL weight: (excluding 500 1.98416 0.9 g payload) 8.50689 3.85866 Table 3.2.201 shows the weight estimations during conceptual design phase The centre of gravity positions were measured from the weights obtained during the conceptual design phase. Moment equations were taken from which the estimated centre of gravity was found. The estimated position of the cg was approximately 35% from the leading edge of the wing without placement of batteries and this gave us rough estimates of the battery movement required to keep the aircraft’s CG within the required 25%-30% region. Estimations were also taken from CATIA which gave a cg position at approximately 30% from the leading edge of the wing including the battery and motors but excluding weight added on by wiring, glue, skin and thermal shrink film.
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: Pod Layout 3.1.9 The pod of the air
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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