1. Oregon State Rocketry
Team 3011th Intercollegiate Rocket Engineering Competition, Green River, UT

2. 2
Team Structure
Aero &
Recovery Avionics Payload Propulsion
Structures &
Integration

3. Structures & Integration
3
Nosecone Airframe Fin Can
Von Karman
Aluminum tip
Fiberglass body
Composite Bulkheads
Fiberglass Couplers
Carbon Body Tubes
Sandwich Structure Fins
Motor Retainer
Fiberglass Boat Tail
Total Structural Weight: 10.0 lbs Structural Weight Reduction: 45%

4. Structures & Integration
Body Tubes
• 12,000 lb. buckling test
• 45 J impact energy, zippering test
4

5. Fin Can
• Honeycomb core fins
• 5 plies carbon fiber weave
• G10 fiberglass fin edges
• Through-wall attachment
• Aluminum motor retaining assembly
Structures & Integration
5

6. Aero & Recovery: Design
6
CO2
Igniter
Black Powder
Puncture Device
Drogue Chute
Diameter : 22”
Vdescent : 89 ft/s
CD : 3.0
Main Chute
Diameter : 105”
Vdescent : 14 ft/s
CD : 3.1
CO2
Ejection
System

7. Aero & Recovery: Trajectory

8. Propulsion: Design
8

9. Propulsion: Design
9

10. Propulsion: Propellant
Role Ingredient Mass Fraction
Binder HTPB 12%
Fuel Al and Zn 1.5%
Oxidizer AP 80%
10
Ammonium Perchlorate Composite
Propellant

11. Burn Time
5.8 s
Thrust
650 lb
Pressure
917 psi
Impulse
12.6 kN*s
Specific Impulse
190 s
Propulsion: Testing
11
0
200
400
600
800
1000
1200
1400
0 2 4 6
Thrust[lbs],Pressure[psi]
Time [s]
Thrust
Pressure
Static Test Fire Results

12. Payload: Motivation
12
Launch Vehicle Component Recovery

13. Payload: Design
13

14. Testing
14
Payload: Operation
Capsule Electronics

15. Test Flight Results
15
0.0
1000.0
2000.0
3000.0
4000.0
5000.0
6000.0
7000.0
0.00 100.00 200.00 300.00 400.00
Altitude[m]
Time [s]
Flight 1
Flight 2
Test Flight
Apogee
Max Speed
Max
Acceleration
Max Roll Rate
Recovery
Distance
ft
790 /s
1
21,758
1002 mph
11.6 g
°
2.1 mi
°/s
2
22,428 ft
1020 mph
10.1 g
815
2.6 mi
Two Successful Test Flights

16. OSU Rocket Team

17. Backup Slides

18. Aerodynamic Pressure
18
0
10
20
30
40
50
60
70
80
90
100
0 5 10 15 20 25 30 35 40
AerodynamicPressure[kPa]
Time [s]
Flight 1
Flight 2

19. Ballistic Trajectories
19
0
1000
2000
3000
4000
5000
6000
7000
8000
9000
0 10 20 30 40 50 60
Range[m]
Launch Angle [°]

20. 0.0
0.2
0.4
0.6
0.8
1.0
1.2
100 150 200 250 300 350 400 450
DragCoefficient(CD)
Velocity (v) [m/s]
OpenRocket
Flight 1
Flight 2
Additional Flight Data
20
-1000
-800
-600
-400
-200
0
200
0 5 10 15 20 25 30 35 40
AxialRollRate[°/s]
Time [s]
Flight 1
Flight 2

21. Propulsion: Subscale Testing
21
Burn Rate Coefficient Data
a .0228 in/s
n .3396
R2 .9858

22. Propulsion: Propellant
Ingredient Role Mass Fraction
AP Oxidizer 80%
HTPB Binder 12%
DOA Plasticizer 3%
MDI Curative 2%
Al and Zn Fuel 1.5%
CaCO3 Flame Colorant
Trace
MnO2 Burn Property Modifier
Castor Oil Mechanical Properties
Lecithin Viscosity Reducing Agent
Silicon Oil Surfactant
22

23. Test
Condition
Sim
Static
Test
Test
Flight 1
Test
Flight 2
Burn Time
[s]
5 5.8 5.8 6.2
Thrust
[lb]
700 650 660 600
Pressure
[psi]
870 917 Not Collected
Impulse
[kN*s]
15 12.6 13.4 13.9
Specific
Impulse
[s]
250 190 210 210
Propulsion: Fullscale Test Data
23
0
1000
2000
3000
4000
5000
0.0 2.0 4.0 6.0
Thrust[N]
Time [s]
Flight 1
Flight 2
Static Test

24. Old Aero/Recovery Slides
24

25. Aerodynamic Profile: Nose Cone
• Von Kármán Profile
• Worked very well
Aero & Recovery
25

26. Aero & Recovery
Aerodynamic Profile: Fins
• Trapezoidal shape
• Ease of manufacturing
• Good subsonic performance
• Reduce flutter risk
26

27. Aero & Recovery
Parachutes
• Toroidal canopies
CO2 Ejection
27
Parachute Drogue Main
Diameter 22 in 105 in
Descent
Speed
88.5 ft/s 13.7 ft/s
Drag
Coefficient
3.0 3.1
CO2 Canister
Igniter
Black Powder
Puncture Device
Bulkhead
Vents

28. Old Payload Slides
28

29. Payload
Autonomously Guided Ram-Air Parachute
1. Eject from rocket at 23,000 ft
2. Fall under drogue to 3,000 ft
3. Deploy maneuverable ram-air parachute
4. Maneuver to preprogrammed GPS location
29

30. Payload
CAD Model:
30
Payload Capsule Nose cone assembly

31. Payload
Parachute:
• 15 ft2 ram-air canopy
• Made of non-ZP F-111 nylon
• Deployed using Cypres 2 cutters
Parachute Testing:
• Dropped from 2,500 ft above
target location
• The parachute deployed as
expected at ~1,000 ft
• Drogue fall 65 mph
31

32. Payload
Steering:
• Winch servo motors
• Servo rotation depends on wind and
present turning conditions
Steering Testing:
• Deployed parachute manually at 2,800 ft
• Followed preprogrammed left hand box
pattern
• Glide ratio = 0.6
32

33. Payload
Capsule:
• 3D printed with ABS plastic
• Printed in 4 sections for ease of
assembly and printing.
• Added 2 layers of fiberglass to
motor housing
• Steel disks added to increase weight
and lower C.G.
Capsule Testing:
• Survived 90 mph impact test
33

34. Payload
Custom avionics package:
• GPS
• 3D Accelerometer
– ± 16g sensitivity
• Magnetometer
– ± 2 gauss sensitivity
• Gyroscope
– ± 2000 degree/second sensitivity
• Altimeter
– ± .12 hPa relative accuracy
• Live data transmission during flight and recovery
34

35. Payload
Applications of system:
• Surveying
• Rapid Delivery
• Targeted rocket recovery
• Atmospheric investigation
35

36. Payload Deployment Test
36

37. Payload Navigation Test
37

38. 38

39. Two Successful
Test Flights
Test Flight Results
39
Test Flight 1 2
Apogee 21,758 ft 22,428 ft
Max Speed 1002 mph 1020 mph
Max
Acceleration
11.6 g 10.1 g
Max Roll Rate 790°/s 815°/s
Recovery
Distance
2.1 mi 2.6 mi
0.0
1000.0
2000.0
3000.0
4000.0
5000.0
6000.0
7000.0
0.00 100.00 200.00 300.00 400.00
Altitude[m]
Time [s]
Flight 1
Flight 2