1. Critical Design Review February 2, 2015
University of North Dakota Frozen Fury
Critical Design Review
February 2, 2015

2. General Vehicle Dimensions
Sofiane
Center of Gravity: inches
Center of Pressure:
Safety Margin: 1.76
Length: 105 inches
Diameter: inches
Mass: 26.2 lbs

3. Critical Flight and Payload Systems
Different subsystems of the rocket

4. Materials and Justifications
Airframe – carbon fiber
Superior strength to weight ratio
Ease of workability
Fins – birch plywood in carbon fiber
Combines the strength of both materials for a more rigid, strong, and lightweight fin
Bulk-Head/Centering ring – 0.5 inch birch plywood
Cabinet quality grain, few knots, and locally available
In addition to having access to these materials, members of our team have experience with them

5. General Vehicle Dimensions
Location of Launch Lugs (inches)
Fin Dimensions (mm)
Location of Centering Rings (inches)

6. Materials and Justifications
Fins
Symmetric shape and quantity allows for ease of construction, trapezoidal shape limits potential damage to fins upon landing
Diameter
6” diameter allows for ease of assembly and plenty of workspace.
Also allows for better utilization of scrap components, and expansion of internal components if necessary
Fins below the bottom of the rocket typically take much more damage than the trapizoidal design.

7. General Vehicle Dimensions
A simple, factory made, reliable nose cone
Nose Cone Dimensions (mm)

8. Materials and Justifications
Nosecone
Will be purchased to insure proper functionality
West Systems Epoxy
Used to bind the above materials together as well as some hardware (bolts, nuts, threaded rods) Be

9. Parachute Attachment Bulkhead
Mention about the black powder connection
Bulkhead Dimensions (inch)

10. Parachutes Parachute type Parachute size Harness Type Harness Length
Descent Rate
Drogue
36 in
ripstop nylon
5ft
62 ft/s
Main
115 in
16.08 ft/s
Payload
58 in
22.47 ft/s

11. Deployment of Parachutes

12. Flight Analysis
Total motion vs. Time

13. Drift Analysis at 5 mph

14. Drift Analysis at 10 mph

15. Drift Analysis at 15 mph

16. Drift Analysis 20 mph

17. Drag Coefficient at 5 mph
Drag Analysis
Drag Coefficient at 5 mph

18. Rocket in Horizontal Position
AGSE Design
ElectricalBox
Ignition Insertion System
Linear Actuator
Kyle
Payload System
Rocket in Horizontal Position

19. Lifted Rocket Position
Rocket in 5° to vertical Position

20. Frame
Square Tube Iron

21. Basic electrical schematic
Electrical Box
Basic electrical schematic
Arduino board
Jeff
All components for the AGSE will be housed in the black box that is on the frame.

22. Claw With Pan/Tilt Bracket
Servo to open and close claw
Another servo to tilt claw
Claw assembly (in)
Claw assembled by the team

23. Belt/Slider Rail
Slider with belt assembly (in)

24. Payload Acquisition System
Payload acquisition assembly (in)

25. Belt/Slider Rail
Slider assembled by the team

26. Linear actuator has stall torque of 240 lbs.
Actuator Position
Rocket actuator assembly (in)
Linear actuator has stall torque of 240 lbs.

27. Ignition Insertion System
Kyle
Side view of the ignition system

28. Wire Funnel Mounted to the rail
Will help guide the ignition wire into the rocket motor
Ignition system funnel (in)

29. Wire Extension Assembly
1, 16 tooth gear is driven by 51 RPM motor
2, 32 tooth gears spin rubber wheels
Steel housing
Will be mounted on rail
Ignition system gearbox (in)

30. Wire Spool Housing Steel housing for spool
Ignition wire is coiled around spool
Mounted to rail
Ignition system wire spool (in)

31. Final Design Changes to be Made
If the stability of the rocket on the rail becomes an issue, there will be guides added to the rail.
A counter weight will be added to the end of the rail behind the wire spool to alleviate motor stress of the actuator.

32. Design Justifications
Sofiane

33. Selection and Justification
Baseline Motor
Selection and Justification
Manufacturer:
AeroTech
Mfr. Designation:
K480W
Motor Type:
reload
Diameter:
54.0 mm
Length:
57.9 cm
Total Weight:
2078 g
Average Thrust: N
Maximum Thrust: N
Total impulse: Ns
Burn Time:
4.3s
Justifications
54.0 mm diameter allows for easy downscaling
Black Max Propellant provides the high visibility tracking of dense black exhaust

34. Motor Selection: Aerotech K480W
Aerotech K480W Thrust per second

35. Thrust-to-Weight Ratio

36. Avionics Dual deployment system
Two Perfect Flight altimeters used as a backup system
Measures barometric pressure
“Mach” delay for safety
Deploys drogue parachute at apogee
Deploys main parachute at ft AGL and payload parachute at 1000ft AGL

37. Avionics: Altimeter Bay

38. Altimeter Bay Schematics

39. Payload Securing Payload Compartment 3-D View
Payload Compartment Rear View

40. Sequence Code
Jeff

41. Sequence Code

42. Declaration of Switches and Pins
Code
Declaration of Switches and Pins

43. Initialization of Switches and Pins
Sequence Code
Initialization of Switches and Pins

44. Declaration of Switches and Pins
Code
Starting Positions
Declaration of Switches and Pins

45. Code
Claw Actions

46. Code
More Claw Actions

47. Code
AGSE Actions

48. Code
AGSE Actions

49. Success Criteria for AGSE
Payload acquisition
Payload is in the launch vehicle and secured
Rocket Erection
Rocket is lifted to a position of 85 degrees from the horizontal
Wire Insertion
Wire is fully inserted in motor and no accidental charge ignites motor

50. Success Criteria for Launch Vehicle
Rocket launch
Reaching an altitude of 3000 feet at apogee.
Rocket recovery
The recovery system deploying properly at the appropriate altitude and recovering the rocket on the ground such that it is deemed reusable for future launches
Payload
The payload should be ejected from the rocket at 1,000 feet and return to the ground with its own parachute.

51. Rocket Flight Static Margin
Rocket Flight Stability
in Static Margin Diagram
The center of gravity is forward of the center of pressure (closer to the nosecone)
Rocket Flight Static Margin
10.855
Center of Pressure in
Center of Gravity in
Kinetic Energy
ft-lbs
Drogue
Main Parachute
68.17
Payload Parachute
70.29
Jacob

52. Vehicle Safety
The minimum rod speed that ensures a stable flight is generally between 30 fps (20 mph) to 45 fps (30 mph).
Exit rail velocity: 69.5 ft/s
A pair of rail beads will be used to ensure the rocket reaches adequate speed off of the rail while maintaining proper orientation

53. Plan for Vehicle Safety Verification and Testing
Critique
Score 1/5
1 = Bad
5 = Good
Comments
Is this design safe? 4
This design will allow for ease of construction and eliminate safety concerns associated with more complex construction methods
Is this design limiting?
Altitude is expected to be reached and the design will accommodate larger motors and payload components
Does this design meet the requirements of the payload/rocket?
This current rocket design satisfies the requirements for the projected payload.
Will this design land safely? Parachute sizes, impact absorbing design?
The current size rocket and parachutes have the rocket descending rapidly under drogue, but slowing to under 25 ft/s under main.
Does this design maximize performance? 3
The rocket has been designed to accommodate the payload as well as larger motors as the design is refined.
Are the materials selected the best for this scenario?
Carbon fiber is a strong yet lightweight material that we have had success with in years prior. Past experience with phenolic tubing has yielded structural failure.
Any additional comments?
Conduct additional tests and review plan to ensure continued safety

54. Educational Engagement
Physics Day at UND - November 12, 2014
This is a program for local middle school to high school students to learn about the many different facets of physics.
Gave a presentation about rocketry
Introduced them to the USLI program and shared our past history with the competition
200 students attended

55. Educational Engagement
Outreach at Grand Forks area middle school
Our team is still in the process of scheduling a date to visit the local middle schools.
Give a brief lecture about rocketry
We will build and launch balloon rockets
Have a Q & A session about rocketry
Expect to reach about students.

56. Educational Engagement
UND Physics and Astronomy Talk -February 23rd.
In an hour long talk, we will detail rocketry throughout the ages and hold a demonstration of our current AGSE. The average attendance for these talks is students and other interested parties.

57. Vehicle Testing
Two sub-scale launches were performed to verify the recovery system and the main design (fins, nosecone).
There were minor complications in each of the launches.
Nate

58. Length ratio of subscale I: Length ratio of subscale II :
Scale Launches
Length ratio of subscale I:
1:1.75
Length ratio of subscale II :
1:1.4
Fins ratio:
1:2.25
Diameter ratio:
1:2

59. Motor and parachutes Aerotech 1211W-M Parachutes:
Total Impulse: 460 N/s
Motor Diameter: 1.5 in
Motor Length: 9.82 in
Parachutes:
Drogue: 30 inches
Main parachute: 28 inches
Payload Parachute: 36 inches

60. Subscale Launch I Rocket: Length: 60.875 inches Diameter: 3 inches
Mass with motors: 28.2 ounces
Stability Margin: 1.3

61. Subscale Launch I Simulation
Apogee: 2815 ft Maximum velocity: 930 ft/s

62. Subscale Launch I Flight
Apogee: 2811 ft.
Deployment of
Time (s)
Altitude (ft)
Velocity (mph)
Drogue
13.65
2804 15
Main parachutes
71.90
600 35

63. Flight I Complications
Lack of space
Increased charge
Weakened bond

64. Subscale Launch II Rocket: Length: 73.75 inches Diameter: 3 inches
Mass with motors: 31.9 ounces
Stability Margin: 2.37

65. Subscale Launch II Simulation
Apogee: 2801 ft Maximum velocity: 881 ft/s

66. Subscale Launch II Flight
Apogee: 2621 ft.
Deployment of
Time (s)
Altitude (ft)
Velocity (mph)
Drogue
13.6
2619 18
Main parachutes
62.05
600 35

67. Flight II Complications
Obstruction when preparing break pin’s holes
Slight wobble during launch
Parachute Complications

68. Near-Future Work In the coming weeks, the team will be working on:
For the AGSE: Cutting the frame and welding it Building of Ignition and lifting system Finishing the payload acquisition system Positioning of the different switches Implementing the electrical system
For the rocket: Ordering of the rocket cylinders Building of the Fins Building of the Payload securing
Kyle

69. Questions?