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

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Presentation on theme: "University of North Dakota Frozen Fury Critical Design Review February 2, 2015."— Presentation transcript:

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

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

3 Critical Flight and Payload Systems Different subsystems of the rocket

4  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 Materials and Justifications

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

6 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 Materials and Justifications

7 Nose Cone Dimensions (mm) General Vehicle Dimensions

8  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) Materials and Justifications

9 Parachute Attachment Bulkhead Bulkhead Dimensions (inch)

10 Parachutes Parachute typeParachute sizeHarness TypeHarness LengthDescent Rate Drogue36 inripstop nylon5ft62 ft/s Main115 inripstop nylon5ft16.08 ft/s Payload58 inripstop nylon5ft22.47 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 Analysis Drag Coefficient at 5 mph

18 AGSE Design Rocket in Horizontal Position Payload System Linear Actuator Ignition Insertion System Electrical Box

19 Lifted Rocket Position Rocket in 5° to vertical Position

20 Square Tube Iron Frame

21 Electrical Box Basic electrical schematic Arduino board 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 Actuator Position ●Linear actuator has stall torque of 240 lbs. Rocket actuator assembly (in)

27 Ignition Insertion System 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 ● 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. Final Design Changes to be Made

32 Design Justifications

33 Justifications  54.0 mm diameter allows for easy downscaling  Black Max Propellant provides the high visibility tracking of dense black exhaust 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 Baseline Motor Selection and Justification

34 Motor Selection: Aerotech K480W Aerotech K480W Thrust per second

35 Thrust-to-Weight Ratio Thrust to weight ratio 7.75:1

36  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 3000 ft AGL and payload parachute at 1000ft AGL Avionics

37 Avionics: Altimeter Bay

38 Altimeter Bay Schematics

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

40 Sequence Code

41

42 Code Declaration of Switches and Pins

43 Sequence Code Initialization of Switches and Pins

44 Code Declaration of Switches and Pins Starting Positions

45 Code Claw Actions

46 Code More Claw Actions

47 Code AGSE Actions

48 Code AGSE Actions

49  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 Success Criteria for AGSE

50  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. Success Criteria for Launch Vehicle

51 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 Center of Pressure in Center of Gravity in Kinetic Energyft-lbs Drogue Main Parachute68.17 Payload Parachute70.29

52  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 Vehicle Safety

53 CritiqueScore 1/5 1 = Bad 5 = Good Comments Is this design safe?4This design will allow for ease of construction and eliminate safety concerns associated with more complex construction methods Is this design limiting? 4 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? 4This current rocket design satisfies the requirements for the projected payload. Will this design land safely? Parachute sizes, impact absorbing design? 4The 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? 3The 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? 4Carbon 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 Plan for Vehicle Safety Verification and Testing

54  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 Educational Engagement

55  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. Educational Engagement

56 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. Educational Engagement

57  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. Vehicle Testing

58 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 Scale Launches

59 Aerotech 1211W-M ● 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 Motor and parachutes

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

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

62 Subscale Launch I Flight Deployment ofTime (s)Altitude (ft)Velocity (mph) Drogue Main parachutes Apogee: 2811 ft.

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

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

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

66 Subscale Launch II Flight Deployment ofTime (s)Altitude (ft)Velocity (mph) Drogue Main parachutes Apogee: 2621 ft.

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

68 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 Near-Future Work

69 Questions?


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