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