1. The Comparative Analysis of Airflow Around a Rocket

3. February 1Begin work on full-scale vehicle and payload. February 15Full-scale vehicle completed. February 21 First test flight of full-scale vehicle March 21Second test flight of full-scale vehicle April 12Rocket ready for launch April 16Rocket Fair/Hardware & Safety check April 19SLI Launch Day

4. 1.First stage burn 2.Stage separation. 3.Booster coasts to its apogee and deploys main parachute. 4.Booster lands safely 5.Second stage motor burn 6.Sustainer reaches apogee, deploys drogue parachute 7.Sustainer descends under drogue parachute to 500ft 8.Main parachute deploys, slowing rocket to safe landing speed of 15-20 fps. 9.Sustainer lands safely.

5. Stable launch of the vehicle Target altitude of one mile reached Smooth stage separation. Proper deployment of all parachutes Safe recovery of the booster and the sustainer

6. Length 158” Diameter6” Liftoff weight38.0 lb. Motor K1275 Redline (54mm) CP117.0” (from nosetip) CG104.26” (from nosetip) Static Margin 3.15 calibers

7. Length 94” Diameter4” Liftoff weight12.7 lb. Motor J540 Redline (54mm) CP79.6” (from nosetip) CG59.0” (from nosetip) Static Margin 5.15 calibers

8. LetterPartLetterPart A Nosecone H Payload Bay B Main Parachute I Payload Electronics C Sustainer E-Bay J Drogue Parachute D Fins K Motor Mount E Transition L Main Parachute F Booster E-Bay M Payload Electronics G Fins N Motor Mount

9. Fins: 1/32” G10 fiberglass + 1/8” balsa sandwich Body: fiberglass tubing, fiberglass couplers Bulkheads: 1/2” plywood Motor Mount: 54mm phenolic tubing, 1/2” plywood centering rings Nosecone: commercially made plastic nosecone Rail Buttons: large size nylon buttons Motor Retention system: Aeropack screw-on motor retainer Anchors: 1/4” stainless steel U-Bolts Epoxy: West System with appropriate fillers

14. BoosterSustainer Flight Stability Static Margin 3.155.15 Thrust to Weight Ratio 6.278.88 Velocity at Launch Guide Departure: 54 mph (launch rail length 144”)

15. Wp - ejection charge weight in pounds. dP - ejection charge pressure, 15psi V - free volume in cubic inches. R - combustion gas constant, 22.16 ft- lbf/lbm R for FFFF black powder. T - combustion gas temperature, 3307 degrees R

16. Ejection charges will be verified in static testing when the vehicle is fully constructed. SectionEjection Charge Booster3.0 g (of FFFF black powder) Sustainer (Drogue)3.0 g Sustainer (Main)2.2 g Stage Separation Charge1.0 g

17. ComponentWeightParachute Diameter Descent Rate Booster399 oz92 in. (main) 17.6fps Sustainer211 oz24 in. (drogue) 49.1 fps Sustainer211 oz60 in. (main) 19.6 fps

18. Tested Components C1: Body (including construction techniques) C2: Altimeter C3: Data Acquisition System (custom computer board and sensors) 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 C13: Second stage separation and ignition electronics/charges

19. Verification Tests V1 Integrity Test: applying force to verify durability. V2 Parachute Drop Test: testing parachute functionality. V3 Tension Test: applying force to the parachute shock cords to test durability V4 Prototype Flight: testing the feasibility of the vehicle with a scale model. V5 Functionality Test: test of basic functionality of a device on the ground V6 Altimeter Ground Test: place the altimeter in a closed container and decrease air pressure to simulate altitude changes. Verify that both the apogee and preset altitude events fire. (Estes igniters or low resistance bulbs can be used for verification). V7 Electronic Deployment Test: test to determine if the electronics can ignite the deployment charges. V8 Ejection Test: test that the deployment charges have the right amount of force to cause parachute deployment and/or planned component separation. V9 Computer Simulation: use RockSim to predict the behavior of the launch vehicle. V10 Integration Test: ensure that the payload fits smoothly and snuggly into the vehicle, and is robust enough to withstand flight stresses.

20. V 1 V 2 V 3 V 4 V 5 V 6 V 7 V 8 V 9 V 10 C 1 PFP C 2 FFF C 3 PPP C 4 FP C 5 FPP C 6 PPP C 7 FP C 8 F C 9 FP C 10 F C 11 FFF C 12 PFF C 13 F

22. Liftoff Weight: 2850 g Motor: I357T, G104T Length: 79 inches Diameter:2in to 3in Stability Margin (both stages): 4.16 calibers Stability Margin (sustainer): 6.50 calibers

23. Test dual deployment avionics Test full deployment scheme Test ejection charge calculations Test separation Test validity of simulation results Test rocket stability

24. Apogee: 2944 ft. – RockSim Prediction:3110 ft. Time to apogee: 13 seconds Apogee events: drogue Sustainer main parachute: Unplanned non- deployment

25. Apogee: 1163 ft. Time to apogee: 8 seconds Apogee events: Main deployment Material failure

26. Apogee events Booster Main Parachute Deployment True apogee

27. DescriptionInitial Point time, altitude End Point time, altitude Descent Rate Sustainer descent with drogue 14s, 2980ft75s, 500ft 40.65 fps Booster velocity at impact (material failure) 11s, 1150 ft16s, 0ft 275fps (not intended)

28. Recorded data Simulation results Apogee = 2944ft Apogee = 3110ft

29. The rocket is stable. We will be able to reach our target altitude Staging works Fiberglass is a must for construction Static ejection charge testing is necessary

31. The sequence of our payload as it goes from flight to the final report.

32. The payload will measure the airflow around the rocket using an array of pressure and temperature sensors. The location of the pressure/temperature sensors are shown in red and obstacles are shown in blue.

33. Sampling rate: 100 times per second Sampling locations: 12 on sustainer and 16 on booster Each sensor package consists of: one pressure sensor one temperature sensor analog/digital converter

34. The sensor package:

35. The "Shepherd“ ( master) Propeller microcomputer drives the two “Sheep” (slave) Propeller microcomputers which collect data from sensor modules located throughout the rocket. The Shepherd Propeller also collects data from the three accelerometers and a pressure sensor.

36. 1.Shepherd instruct all Sheep to collect data 2.Each Sheep read all its sensors 3.After obtaining the data, each Sheep transmits collected data to its Shepherd 4.Shepherd stores the data and repeats the process Data Acquisition, Processing and Storage is done by linked Parallax Propeller Chips (part number P8X32A). Each Propeller chip has 8 independent cores, each core running at 80MHz.

37. The shepherd chip maintains a template in its RAM with the time stamp and a space for the temperature and the pressure data from each sensor.

38. The shepherd also gathers data from a three-axis accelerometer and a pressure sensor. These are used to get accurate atmospheric pressure data and velocity data.

39. The pressure/temperature sensors (2) are located on either side of the obstacle (1), one on the fore end and two on the aft end. 2 1

40. Components 1.Pressure Sensors 2.Battery Pack 3.Altimeter 4.3D Accelerometer 5.Obstacles 6.Temperature Sensors Verification Tests 1.Drop Test 2.Connection and Basic Functionality Test 3.Pressure Sensor Test 4.Scale Model Flight 5.Temperature Sensor Test 6.Durability Test 7.Acceleration Test 8.Battery Capacity Test

41. P=PLANNED F=FINISHED T E S T S 12345678 COMPONENTSCOMPONENTS 1FPP 2FPFF 3FFFF 4PPP 5PP 6FPP

42. 1.Fin 2.Parachute 3.Data Processing and Storage 4.Motor        Sensor package

43. Diagram of the sustainer showing the payload integration. DPS Unit Timer Alt Sensor package

44. Diagram of the Booster showing the payload integration. Fin Tab Fin Motor Alt Parachute DPS&S

45. Commercially available sensors will be used Sensors will be calibrated Extensive ground testing of all electronics

46. Determine the effect of obstacles on the surface of rocket on airflow around the rocket Determine the accuracy of wind tunnel testing

47. Obstacles remain attached to the rocket during flight. Sensors will successfully collect and store measureable data during flight. Data collected is reliable and accurate.

48. Independent Variables – Type and location of obstacles………….…. L – Air density outside of rocket……..……..…. D – Speed of air flow…………………………………. S – Air pressure………………………………………… P – Air temperature………………………………….. T – Acceleration profile…………………………….. X,Y,Z Dependent Variables – Pressure at each sensor………….………….. Y i – Temperature at each sensor…................ T i

49. Identical rocket in wind tunnel and actual flight Identical obstacles on rocket in wind tunnel and actual flight Similar wind speeds in wind tunnel and actual flight of first stage Identical sensors and method of data storage

50. Primary correlations – Yx = f(L) (local pressure vs. location) – Yx = f(S) (local pressure vs. airspeed) – Data from wind tunnel test and actual flight will be compared Further correlations from actual flight – temperature vs. selected independent variables – pressure vs. selected independent variables

51. TestMeasurement TemperatureTemperature will be collected 20 times per second by the sensor array PressurePressure will be collected at least 100 times per second by the sensor array