MAE 155A Aerospace Engineering Design I

MAE 155A Aerospace Engineering Design I

Team FirestormJoshua T. Hu, Project Manager

Brandan York, Chief Engineer

Michael Basic, Project Engineer

Aaron Pebley, Project Engineer

Proposal #2

Dr. James D. Lang, Project Advisor

Outline of Presentation

• Scope

• Design Timeline

• Design Factors

• Mission Profile

• Design Approach

• Initial Designs

• Decision Matrix

• Final Design

• Compliance Matrix

• Aerodynamics, Structures, Stability, Subsystems, Supportability, Cost Analysis

• Conclusion and Future Work Needed

Scope

• To develop and recommend an unmanned aerial vehicle (UAV) for the Royal Australian Air Force (RAAF).

• Design must be viable and affordable compared to manned aircraft concepts.

• UAV is to be similar to Joint Strike Fighter (JSF) in performance.

Design Timeline

ID Task Name Start Finish

1 MAE 155A Design Project Thu 1/10/02 Thu 3/14/02

2 RFP #1 Requirements - Individual Thu 1/10/02 Tue 1/29/02

3 RFP #2 Requirements - Team Tue 1/29/02 Thu 3/14/02

4 Formation of Team Tue 1/29/02 Tue 1/29/02

5 Configuration Layouts Wed 1/30/02 Tue 2/5/02

6 Initial Concept Calculations Wed 2/6/02 Thu 2/14/02

7 Design Downselection Fri 2/15/02 Sun 2/17/02

8 Interim Report and Presentation Preparation Mon 2/18/02 Wed 2/20/02

9 Written and Oral Interim Reporting Thu 2/21/02 Thu 2/21/02

10 Detailed Concept Calculations Fri 2/22/02 Mon 3/4/02

11 Cost and Supportability Analysis Tue 3/5/02 Fri 3/8/02

12 Final Report and Presentation Preparation Sat 3/9/02 Wed 3/13/02

13 Final Project Presentation Thu 3/14/02 Thu 3/14/02

2/21

3/14

12/9 12/30 1/20 2/10 3/3 3/24 4/14 5/5December January February March April May

Design Factors

• Good Aerial Combat Performances for 2 Missions

• Mission #1-Defensive Counter Air Mission

• Mission #4-Offensive Counter Air Mission

• Ease of Manufacturing

• Low Cost

• Modular Payload

• Stealth

• Variable Geometry Wings

Mission Profile

Design Approach

• Jetfighter

• Variable Geometry vs. Fixed Wings

• V-Tail vs. Conventional

• Fuselage Geometry

• 2-D Vector Nozzles

• Inlet Styles

Initial DesignsDesign #1 – Michael Basic

Initial DesignsDesign #2 – Joshua T. Hu

Initial DesignsDesign #3 – Aaron Pebley

Initial DesignsDesign #4 – Brandan York

Initial DesignsDesign #5 – Joshua T. Hu

Initial DesignsDesign #6 – Brandan York

Decision Matrix

Config. 1 Config. 2 Config. 3 Config. 4 Config. 5 Config. 6

Wo + - + - + -Performance + + + + - +Stealth - - + - + -Fuel Usage + + + + + +Mission 1 & 4 Compatibility + + + + - +Is it practical to build model? + + + + - +

Final Design

60 ft

38 ft.

23 ft.

7 ft.

TOGW - 25125 lbs Fuel weight - 9170 lbsT/W - 1.19 (takeoff), .588(combat)L/D - 14(unswept), 12(swept), 7(dash)W/S - 70(takeoff), 35.8(combat)Max Mach 1.6Wetted area/Wing area = 4.8

Compliance Matrix

M i s s i o n# 1 D C A

M i s s i o n# 2 H i -

H i - H i - H i

M i s s i o n# 3 H i - L o -

L o - H i

M i s s i o n# 4 O C A

M i s s i o n# 5 I S R

P a y l o a d + - - + +M i s s i o n R a d i u s + - - + -M a x i m u m M a c h + + + + +

S t e a l t h + + + + +M a x . I n s t a n t a n e o u s

T u r n R a t e+ + + + +

T a k e o f f / L a n d i n gD i s t a n c e - 8 0 0 0 f t

+ + + + +

AerodynamicsCdo vs Mach

0.02

0.03

0.04

0.05

0.06

0 0.5 1 1.5 2

Mach #

Cdo

Lift Curve Slope Vs. MACH #

0

0.5

1

1.5

2

2.5

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

MACH #

CLalp

ha

K vs MACH #

0

0.05

0.1

0.15

0.2

0.25

0 0.5 1 1.5 2

MACH #

K

AerodynamicsCL vs Mach

0

1

2

3

0 0.5 1 1.5 2

MACH #

CL

CD vs MACH

00.10.20.30.40.5

0 0.5 1 1.5 2

MACH #

CD

CL/CD vs MACH

0

5

10

15

20

0 0.5 1 1.5 2

MACH #

CL/C

D

Ps vs. Mach Chart

Ps vs MACH

0

100

200

300

400

500

600

700

0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8

MACH

C.G. Movement

C.G. Movement of Firestorm UAV

15000

17000

19000

21000

23000

25000

21 23 25 27 29

C.G. Location (ft)

Gro

ss W

eigh

t (lb

)

22.5 27.5

Forw

ard

C.G

. Lim

it

Aft.

C.G

. Lim

it

Takeoff

Land

Materials and Structures

-Main structural components made of either titanium or RTM composites

-Wing skins made of carbon/epoxy thermosetcomposites (except the leadingand trailing edges)

V-n Diagram

-10

-8

-6

-4

-2

0

2

4

6

8

10

12

14

16

18

0 100 200 300 400 500 600 700 800 900 1000 1100 1200

Velocity (Mph)

N (lo

ad fac

tor)

Np = 16.7g

Vc = 1.2M (813 mph)

Nn = -8g

Vs curve

Inverted VsCurve

Vs = 141 mph

Vmax = 1.6M

(1084 mph)

Stall speed@ 16.7g = 578mph

Subsystem

Avionics

Fuel Tanks

Subsystem

Avionics

Landing Gears

Modular Payload

Afterburning Low Bypass Turbofan

C.G. Location

2-D Vector Nozzle

Subsystem

Variable Geometry Armpit Air Inlets w/ Channel-Type Boundary Layer Diverter

Supportability

• Off the shelf parts to save cost and training

• Similar swing wing mechanism as F-14 Tomcat

• Same avionics as JSF

• Same powerplant as JSF

• Same internal carriage as JSF

• Same landing gear as JSF

Cost Analysis

• Required Life Cycle Cost (LCC) for 100 aircraft < $10 Billion

• Firestorm UAV LCC for 100 aircraft = $6.3 Billion Requirement Met!

Cost Comparison Flyaway Cost LCC Savings50 Aircraft-Baseline $3.5 Billion $4.4 Billion 0100 Aircraft $4.5 Billion $6.3 Billion 30%500 Aircraft $9.7 Billion $18.5 Billion 76%

Conclusion and Future Work Needed

• Initial design phase over

• Design factors achieved (low cost, stealth, etc…)

• Further trade studies of T/W and W/S

• Detailed study of vector nozzles

• Aircraft mockup

• Wind tunnel testings

Conclusions and Further Work Needed (cont.)...

• Perform FEA

• Build and fly test vehicle