1. The effect of gravitational stress on the diffusion of liquids. New team SLI 2012

3. February 17Full scale vehicle completed February 18Full scale test flight #1 March 24/25Full scale test flight #2 with payload April 19/20Flight hardware and safety checks April 21Launch day, full scale fight #3 April 28/29Full scale flight #4 (tentative)

5. Event 1: Ignition at 0s, 0ft Event 2: Burnout at 2.24s, 1000ft Coast Event 3: Apogee at 17s, 5252ft Drogue descent Event 4: Main parachute deployment at 84s, 700ft Event 5: Landing at 110s, 0ft Apogee prediction updated based on data from scale model flight (C d = 0.48 ): 5252 ft Apogee prediction updated based on data from scale model flight (C d = 0.48 ): 5252 ft

6. Motor ignition Stable flight Altitude of 5,280 feet AGL reached but not exceeded (most current prediction: 5252ft) Both drogue and main parachute deployed Vehicle returns to the ground safely with minimal damage Safe recovery of the booster

7. CP 83.1” from nosecone CG 65.6” from nosecone Static margin 3.2 calibers Length 108” Diameter 5.5”(body tube), 4”(booster) Liftoff Weight 21.5 lb Motor Aerotech K1050W

8. LetterPart ANosecone BMain Parachute CDrogue Parachute DPayload Bay ETransition FMotor Mount GFins

9. Body: 5.5”/4.0” LOC Precision fiber tubing Fins: 1/32” G-10 fiberglass + 1/8” balsa sandwich Couplers: LOC Precision with stiffeners Bulkheads, centering rings: 1/2” plywood Motor mounts: 54mm Kraft phenolic tubing Nosecone: Plastic nose cone Rail buttons: standard nylon rail buttons Motor retention system: Aeropack screw-on motor retainer Anchors: 1/4" stainless steel U-Bolts Epoxy: Locktite epoxy

10. Length [in] Mass [kg] Diamet er [in] Motor Selection Stability Margin [calibers] Thrust to weight ratio Burn time 1088.95.5, 3.0AT-K1050W3.29.82.5s We selected the AT-K1050W 54mm motor to propel our rocket to but not exceeding an altitude of 5280ft AGL The AT-K1050W motor provides an appropriate thrust to weight ratio for our vehicle (9.8). Mach delay of 4 seconds will be set on both deployment altimeters

12. Apogee at: 5252ft, 17s

13. Max acceleration: 16 Gees

14. Maximum velocity: 520 mph Mach number: 0.72

15. Wind Speed [mph] Altitude [ft] Percent Change in Altitude 052520.00% 552400.10% 1052040.40% 1551681.60% 2051012.80%

16. ParameterValue Flight Stability Static Margin 3.2 Thrust to Weight Ratio9.8 Velocity at Launch Guide Departure (12ft AGL) 68mph

17. Wp - ejection charge weight [g] dP - ejection pressure (15 [psi]) V - free volume [in 3 ] R - universal gas constant (22.16 [ft- lb o R -1 lb-mol -1 ]) T - combustion gas temperature (3,307 [ o R])

18. ParachuteCharge (g) Drogue2.4 Main5.5 Charges will be finalized via static ejection tests. Tests carried out with the scale model indicated that average increase of 30% against calculated values may be needed for GOEX 4F powder.

20. ParachuteDescent Weight (lbs) Parachute Diameter (in.) Descent Rate (ft/s) Kinetic Energy at Impact (ft-lb) Drogue18.751868 N/A Main18.759016 Nosecone 3.6 Body 27.6 Booster 29.0

21. Wind Speed (mph) Drift (ft) Drift (mi) 000 58140.15 1016300.31 1524440.46 2032590.62

22. Tested Components C1: Body (including construction techniques) C2: Altimeter C3: Accelerometer C4: Parachutes C5: Fins C6: Payload C7: Ejection Charges C8: Launch System C9: Motor Mount C10: Beacons C11: Shock Cords and Anchors C12: Rocket Stability

23. Verification Tests V1 Integrity Test: force applied; verifies durability. V2 Parachute Drop Test: tests parachute functionality. V3 Tension Test: force applied to shock cords; tests durability. V4 Prototype Flight: tests feasibility of vehicle with scale model. V5 Functionality Test: tests basic functionality of device on ground. V6 Altimeter Ground Test: simulate altitude changes; verifies preset altitude events fire. V7 Electronic Deployment Test: tests that electronics ignite deployment charges. V8 Ejection Test: tests that deployment charges can deploy parachutes/separate components. V9 Computer Simulation: RockSim predicts behavior of launch vehicle. V10 Integration Test: payload fits smoothly and snuggly into vehicle, and withstands flight stresses.

24. V1V2V3V4V5V6V7V8V9V10 C1 C2 C3 C4 C5 C6 C7 C8 C9 C10 C11 C12

26. Liftoff weight3.6 lb MotorAerotech H250G Length4 ft. 7 in. Diameter2.6” body, 1.5” motor tube Stability Margin3.5

27. Test drogue and main parachute deployment Test flight electronics (altimeters and ejection charges) Test separation of body tubes at ejection Test validity of simulation results Test rocket stability

28. Apogee- 2181ft Rocksim prediction 1900ft Time to apogee- 13s Apogee events Drogue deployment Main event Main parachute deploys at 700ft Main parachute deployed at apogee and drogue at 700 ft (wiring error) Calculated C d :0.48 5252 ft Apogee for full scale vehicle (C d =0.48): 5252 ft

31. On main parachute (from apogee): 21 ft/s After drogue deployment (700 ft): 21 ft/s Due to the error in wiring, the main parachute was deployed by the apogee event and drogue parachute by the set-altitude (700ft) event. We have added a test to our preflight routine to prevent this problem from reoccurring.

32. IssueMitigation Rocket trajectory wasn’t completely straight Fillet fins from inside rocket (loose fin was the cause) Two fins came loose during flightFillet fins from inside rocket (insufficient filleting) Cross-wired the parachutes in electronics bay Double check parachute wiring before flight, verify using audible altimeter reporting Rail button came off while preparing rocket on the pad and removing e-bay for altimeter switch access Have altimeter switches accessible from outside the rocket (through all outside walls)

34. We will investigate the effects of acceleration and vibrations during flight on the diffusion of dye into liquids using digital imaging.

35. Determine the effect of acceleration on the diffusion of dye into liquids Determine the effect of vibrations on the diffusion of dye into liquids

36. Collected data from the camera and accelerometers is accurate Vessels containing liquid do not leak Dye is injected into the liquid correctly Images from camera are received Acceleration is recorded Payload is recovered

37. Battery LED Syringe Sealed petri dish Camera Syringe Sealed Plexiglas vessel Camera LED Battery

39. Selection Rationale Fits inside the payload chamber Waterproof (in case of payload damage) Minimum focus is 1cm (0.4”) Full HD video 1920 x 1080 @ 30fps Sufficient memory/battery capacity Within the budget of our project ($300) Robust design (designed for extreme sports) Selection Rationale Fits inside the payload chamber Waterproof (in case of payload damage) Minimum focus is 1cm (0.4”) Full HD video 1920 x 1080 @ 30fps Sufficient memory/battery capacity Within the budget of our project ($300) Robust design (designed for extreme sports)

40. Rocket Body Coupler Tube Bulkhead

41. Launch and Boost Dye is injected into the solution Camcorder records the diffusion process The experiment chamber is brightly lit using LEDs to prevent any exposure problems during recording

42. The camcorder continues to record the diffusion process until the vehicle reaches apogee. Coast and Apogee Accelerometer records acceleration data.

43. Data Analysis The pictures taken during the flight are analyzed

44. Preflight ground tests  Pictures of Petri dish from overhead camcorder  Water tank pictures from side view Experimental Group Control Group (stationary)

45. Independent variables a Acceleration t Time after dye is released (flight time) Dependent Variables R Rate of diffusion (diffusion front speed) P Pattern of diffusion (qualitative classification)

46. R = f(a) Rate of diffusion in relation to acceleration R = f(t) Rate of diffusion in relation to time after dye is released P = f(a) Pattern of diffusion in relation to acceleration P = f(t)Pattern of diffusion in relation to time after dye is released

47. TestMeasurement Rate of Diffusion Dyed area boundary rectangle expansion Pattern of Diffusion Width to height ratio of dye Color saturation per pixel Voids in dye

48. Voids Boundary rectangle: X pixels by Y pixels Measure color saturation in each pixel

49. CharacteristicMeasurement Average void sizeMeasured in pixels Void scatteringNumber of void areas Color dye spreadClear vs. colored area (in pixels) Directional dye spreadWidth vs. height of color area To quantify the results of our experiment, we have selected the following characteristics to measure. Computerized digital image analysis will be used and we expect to process over 7 billion pixels using a multicore Linux machine.

50. We will use commercially available accelerometers and altimeters The sensors will be calibrated We will do extensive testing on the ground prior to the rocket launch

51. Tested Components C1: Camera C2: Injection C3: Diffusion Vessel

52. Verification Tests V1 Basic Function Test: testing the main functions of the payload V2 Leak Test: verifying that the vessels containing the liquid do not leak V3 Battery Life Test: verifying that the battery life of the camera is long enough to take pictures during the entire diffusion process

53. V1V2V3 C1 C2 C3