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The Comparative Analysis of Airflow Around a Rocket

The Comparative Analysis of Airflow Around a Rocket. Part I: Vehicle. February 1 Begin work on full-scale vehicle and payload. February 15 Full-scale vehicle completed. February 21 First test flight of full-scale vehicle March 21 Second test flight of full-scale vehicle

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The Comparative Analysis of Airflow Around a Rocket

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  1. The Comparative Analysis of Airflow Around a Rocket

  2. Part I: Vehicle

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

  4. Flight Sequence • First stage burn • Stage separation. • Booster coasts to its apogee and deploys main parachute. • Booster lands safely • Second stage motor burn • Sustainer reaches apogee, deploys drogue parachute • Sustainer descends under drogue parachute to 500ft • Main parachute deploys, slowing rocket to safe landing speed of 15-20 fps. • 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 Success Criteria

  6. Full Scale Rocket – Entire Rocket • CP 117.0” (from nosetip) • CG 104.26” (from nosetip) • Static Margin 3.15 calibers Length 158” Diameter 6” Liftoff weight 38.0 lb. Motor K1275 Redline (54mm)

  7. Full Scale Rocket - Sustainer • CP 79.6” (from nosetip) • CG 59.0” (from nosetip) • Static Margin 5.15 calibers Length 94” Diameter 4” Liftoff weight 12.7 lb. Motor J540 Redline (54mm)

  8. Rocket Schematics

  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 Construction Materials

  10. Thrust Curve

  11. Acceleration Profile

  12. Velocity Profile

  13. Altitude Profile

  14. Flight Safety Parameters

  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 Ejection Charge Calculations Wp = dP * V / (R * T)

  16. Calculated Ejection Charges Ejection charges will be verified in static testing when the vehicle is fully constructed.

  17. Parachutes

  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 Verification Matrix

  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. Verification Matrix

  20. Verification Matrix

  21. Scale Model Launch

  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 Scale Model Parameters

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

  24. Apogee: 2944 ft. RockSim Prediction: 3110 ft. Time to apogee: 13 seconds Apogee events: drogue Sustainer main parachute:Unplannednon- deployment Scale Model Flight Results- Sustainer

  25. Apogee: 1163 ft. Time to apogee: 8 seconds Apogee events: Main deployment Material failure Scale Model Flight Results- Booster

  26. Scale Model Flight Data True apogee Apogee events Booster Main Parachute Deployment

  27. Measured Descent Rates

  28. Altitude Profile of Scale Model Simulation results Apogee = 3110ft Apogee = 2944ft Recorded data

  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 Lessons Learned

  30. the payload

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

  32. Data Acquisition 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. Data Acquisition • 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. Data Acquisition The sensor package:

  35. Data connections 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. Data Collection Cycle • Shepherd instruct all Sheep to collect data • Each Sheep read all its sensors • After obtaining the data, each Sheep transmits collected data to its Shepherd • 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. Data processing and storage 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. Data processing and storage 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. Data processing and storage 1 2 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.

  40. VerificationMatrix Verification Tests Drop Test Connection and Basic Functionality Test Pressure Sensor Test Scale Model Flight Temperature Sensor Test Durability Test Acceleration Test Battery Capacity Test Components Pressure Sensors Battery Pack Altimeter 3D Accelerometer Obstacles Temperature Sensors

  41. VerificationMatrix

  42. Sensor package Integration Plan    Fin Tab     • Fin • Parachute • Data Processing and Storage • Motor

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

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

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

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

  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. Payload success criteria

  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………….………….. Yi Temperature at each sensor…................ Ti Variables

  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 Controls

  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 Correlations

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