Team 5 Dynamics & Control PDR 2 Presented By: Trent Lobdell Eamonn Needler Charles Reyzer.

Team 5Dynamics & Control PDR 2

Presented By: Trent LobdellEamonn NeedlerCharles Reyzer

AAE 451 – Team 5March 10, 2005 2

Outline Drag Revisited Flight Performance Engine Cooling Sizing X-plots Trim Diagram Elevator Size Feedback Diagram

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

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

AAE 451 – Team 5March 10, 2005 5

Flight Performance

Maximum Climb Angle = 26.77°

1sinT D

W

AAE 451 – Team 5March 10, 2005 6

Flight Performance

2

2 1

Vr

g n

1

cosn

2

2

1g nw

V

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

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

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

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

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

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

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

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

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

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

AAE 451 – Team 5March 10, 2005 17

Feedback Controller

Pitch rate feedback to the elevator Damping ratio for the pitch rate is deficient

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

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)

AAE 451 – Team 5March 10, 2005 20

Summary Drag Revisited Flight Performance Engine Cooling CG Changes X-plots Trim Diagram Elevator Size Feedback Diagram