Download - Team 5 Dynamics & Control PDR 2 Presented By: Trent Lobdell Eamonn Needler Charles Reyzer
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Team 5Dynamics & Control PDR 2
Presented By: Trent LobdellEamonn NeedlerCharles Reyzer
![Page 2: Team 5 Dynamics & Control PDR 2 Presented By: Trent Lobdell Eamonn Needler Charles Reyzer](https://reader036.vdocument.in/reader036/viewer/2022062407/56649d425503460f94a1de9d/html5/thumbnails/2.jpg)
AAE 451 – Team 5March 10, 2005 2
Outline Drag Revisited Flight Performance Engine Cooling Sizing X-plots Trim Diagram Elevator Size Feedback Diagram
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AAE 451 – Team 5March 10, 2005 3
Drag Buildup
Parasite Drag Buildup#
1
i i
p
compi i f wet
Di ref
K QC SC
S
Sref = reference area [ft2]Cf = skin friction coefficientK = form factorQ = interference factor
Component CDp
Wing: 0.0168Fuselage: 0.0051Horiz. Tail: 0.0152Vert. Tails: 0.004Booms: 0.0109Wheels: 0.0269Struts: 0.0003Misc: 0.004CDp: 0.0831
Total Drag:CDp: 0.0831CDi: 0.0038CDtot: 0.087Drag: 0.3447 lbf
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AAE 451 – Team 5March 10, 2005 4
Flight Performance
Take-off Distance: 16.29 ft
Landing Distance: 22.48 ft
2
max 0.7
1.44
TO
TOTO
L TO V
WS
SC g T D W L
2
max 0.7
1.69
L
LL
L L V
WS
SC g D W L
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AAE 451 – Team 5March 10, 2005 5
Flight Performance
Maximum Climb Angle = 26.77°
1sinT D
W
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AAE 451 – Team 5March 10, 2005 6
Flight Performance
2
2 1
Vr
g n
1
cosn
2
2
1g nw
V
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AAE 451 – Team 5March 10, 2005 7
Flight Performance
Turning Radius: 35 ft (DR&O)Bank Angle: 34.82°Turn Rate: 0.8 deg/s
Turning Radius: 10.92 ft (Limit)Bank Angle: 65.85°Turn Rate: 2.57 deg/s
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AAE 451 – Team 5March 10, 2005 8
Engine Cooling
MountHoles
Shaft Outlet
Vent Ram Scoop
Airflow
Front View Side View
Foam Melting Temperature: 194° F
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AAE 451 – Team 5March 10, 2005 9
Gyro Selection
Specifications: 3.5 to 12 volts 0.85 oz 1.6"x1.5"x0.65“ Remote Gain Control Available at Hobby-Lobby ® $ 89.90
Ikarus R/C Gyros
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AAE 451 – Team 5March 10, 2005 10
Sizing Solidifications
Error noticed with original gyro selection0.85 oz << 3 ozOriginal gyro thought to be needed was 3 ozAlternative foundPlane sized with Lithium PolymerCG code updated
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AAE 451 – Team 5March 10, 2005 11
Sizing Updated
CG code changes made• Locations originally
done as percentage of plane length
• Lithium-Polymer Batteries Selected
• Weights better refined
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AAE 451 – Team 5March 10, 2005 12
H-tail X-plot CG curve found
using traditional CG calculations which account for H-tail and V-tail
AC curve found using Roskam equation
0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 20.8
1
1.2
1.4
1.6
1.8
2
2.2X-Plot for Horizontal Tail
Tail Area [sq ft]
Loca
tion
(nor
mac
lized
abo
ut C
MA
C)
xcg
xN
xacw
Desired SM
))/1(*)/(**)/(1(
))/1(*)(*)/(**)/((
ddSSCC
ddxSSCCxx
HHLL
acHHLLacac
WBH
HWBHWB
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AAE 451 – Team 5March 10, 2005 13
Detailed Specifications
Vertical Tail (each)
Horizontal Tail
Misc.
Area 0.11 ft2 0.25 ft2 SM = 0.15
Height/Span 0.73 ft 0.583 ft Xcg = 0.62 ft
Chord 0.4 ft 0.429 ft Xn = 0.728 ft
AR 4.84 1.360 Total Weight = 0.88 lbf
Weight 0.01 lbf 0.019 lbf
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AAE 451 – Team 5March 10, 2005 14
Trim Diagram
Raymer Equations and Tables, p. 490-501
Made Assumptions to find Cmcg
Plain flapped surface changes zero-lift angle of attack
])()1)([(hhh OLwhwLL iiiCC
htotal Lw
hhwLL CS
SiCC
][
)()()( pcg
w
pt
w
cgachLhmfusfmmacwcgLm xxqS
FZ
qS
TxxC
Sw
ShCCCxxCC
hfewcg
ff
L
LOL
C
C
1
..cos)(9.0 LHref
flappedairfoil
f
lf
f
L
S
SCK
C
00 0 01
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AAE 451 – Team 5March 10, 2005 15
Trim Diagram
-0.2 0 0.2 0.4 0.6 0.8 1 1.2-0.25
-0.2
-0.15
-0.1
-0.05
0
0.05
Trim Diagram for Cf/C = 0.5
CLtotal
Cm
cg
-30
-25
-20
-15
-10
-5
0
5
= 6 = 0
e
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AAE 451 – Team 5March 10, 2005 16
Elevator Size
Based upon trim diagram, cf/c = 0.5 chosen
With 2 inches clearance for uninterrupted deflection, elevator span ~ 0.8 ft
Elevator chord = 0.5*h-tail-chord ~ 0.21 ft Elevator area = 0.171 ft2
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AAE 451 – Team 5March 10, 2005 17
Feedback Controller
Pitch rate feedback to the elevator Damping ratio for the pitch rate is deficient
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AAE 451 – Team 5March 10, 2005 18
Block Diagrams
0.3465- 2068s- 418.5s- 735.5s- 31.79s s
018-3.395e- 0.04058s- 3718s- 7180s- 321.5s-
)(
)(2345
234
s
sq
1Gyro RatePitch
1ServoElevator
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AAE 451 – Team 5March 10, 2005 19
Root Locus
Damping Ratio without Feedback = 0.21
Desired Damping Ratio = 0.35 - 1.3
Damping Ratio with Feedback = 0.70
(k= 1.67)
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AAE 451 – Team 5March 10, 2005 20
Summary Drag Revisited Flight Performance Engine Cooling CG Changes X-plots Trim Diagram Elevator Size Feedback Diagram