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University of Colorado
Cranked Arrow Planform Better low-speed performance
than standard delta Easier to manufacture than
Ogee wing
Sears-Haack Fuselage Minimizes shockwave drag
Tail-less Design Significant drag reduction Yaw supplied by thrust
vectoring Roll and pitch both supplied by
elevons (elevators + ailerons)
Nose Inlet Simplifies duct design Requires less extensive wind
tunnel testing / CFD modeling
Aerospace engineering Sciences
Flight Computer
30%
11%
6%
19%
11%
22%
Fuselage
Wings
Landing Gear
Engine
Electrical
Fuel & Fuel SystemTotal Weight = 50 kg
Mass Breakdown
NI sbRIO Specifications 8.2''x5.6''-Size 110-3.3V Digital I/O 32-Analog Inputs 292 g-Mass 400 MHz-Processing
Speed 256 MB-Internal Storage
Fully Autonomous System Integration of Controls and
Sensors Controls Every Aspect of
Flight
Aerodynamics
Carbon fiber wings and fuselage
High strength
Low weight
Composite molds
CNC’d female molds
Entire UAV out from two molds
Carbon fiber
Resuable Molds
Manufacturing
Aircraft shall achieve supersonic flight Aircraft shall be under 50 kg Aircraft shall meet all requirements for FAI speed record Aircraft shall incorporate a fluidic thrust vectoring system
for yaw control Aircraft shall meet all requirements for testing at EAFB or
similar facility
Testing
Use fluidic injection to critically choke flow and provide thrust vectoring in nozzle
Create prediction models for secondary flow properties required to maintain critical throat area
Verify/augment models with physical test data collected through modification on the SWIFT supersonic tunnel
Use as 1- D nozzle choking as proof of concept for later thrust skewing nozzle
Modify SWIFT supersonic wind tunnel Manual pressure control out of
reservoir tank Secondary line pressure and mass flow
controlled electronically Secondary line injected at throat of test
nozzle
Thrust Vectoring Using almost all carbon fiber composite. 3g limit and 100 kPa duct pressure with
safety factor of 1.25 Wings have a spar and rib structure At end of inlet duct, max allowable stress of
2280 MPa, max predicted of 2000 MPa
Structures
Wind Tunnel Testing at Air Force Academy in Summer 2011
Subsonic, Transonic and Supersonic Testing
Mach 0.3 – 1.8
Custom afterburning turbojet engine
Centrifugal compressor for good compression on small scale
Incorporating afterburner significantly increases thrust
Propulsion
"Design and construct a supersonic unmanned aerial vehicle that will break the world UAV speed record and utilize a fluid injection thrust vectoring control system."
Mission Statement
Project Requirements
Mission Profile
Project Advisers : Dr. Ryan Starkey & Joseph Tanner
Programming in LabVIEW GUI Based, Reusable Code
0 50 100 150 200 250 300 350-7000
-6000
-5000
-4000
-3000
-2000
-1000
0
1000
Velocity (m/s)
Mom
ent (
N*m
)
Pitch Moment (Take off)
width = 10cm
width = 20cmwidth = 30cm
Elevons Length : 0.50 m Width : 0.05 m
Take off speed : 54 m/s (105 knots) Landing speed : 40 m/s (78 knots)
Pitching moment : 25 Nm @ CL0 = 0.01
Aircraft parametersCharacteristics Dimensions
Fuselage Length 1.87 m
Wing Span 1.25 m
CG Location 0.84 m
AC Location 0.75 m
Main Gear Position 0.70 m
Note : Dimensions measured from the nozzle exit
2 3 4 5 6 7
x 105
0
5
10
15
20
25
30
Regulator Pressure (Pa)
Mas
s flo
w r
atio
(%)
Mass flow ratio vs Primary Flow Pressure
Fre
estr
eam
mdo
t (kg
/s)
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.08
0.09
0.1
0.11
2 3 4 5 6 7
x 105
1
2
3
4
5
6
7
8
9
10
Regulator Pressure (Pa)
Flui
d In
ject
ion
Dis
tanc
e R
equi
red
for C
hoki
ng (m
m)
Injection Distance vs Regulator Pressure
Free
stre
am m
dot (k
g/s)
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.08
0.09
0.1
0.11
Controls