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The Effect of Acceleration on the Crystallization of Sodium Acetate

PROJECT HOT ICE. The Effect of Acceleration on the Crystallization of Sodium Acetate. Part I: Vehicle . December 7 Begin work on scale model January 4 Scale model completed January 13 Scale model test flight February 15 Full scale vehicle completed February 22 Sustainer test flight

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The Effect of Acceleration on the Crystallization of Sodium Acetate

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  1. PROJECT HOT ICE The Effect of Acceleration on the Crystallization of Sodium Acetate

  2. Part I: Vehicle

  3. December 7 Begin work on scale model January 4 Scale model completed January 13 Scale model test flight February 15 Full scale vehicle completed February 22 Sustainer test flight March 15 Two stage rocket test flight March 22 Payload test flight April 15 – 16 Rocket fair and safety check April 17 – 18 SLI launch weekend Major Milestone Schedule

  4. Flight Sequence • First stage burn, reaction starts • Stage separation • Booster coasts to its apogee and deploys drogue parachute • Booster deploys main parachute • Booster lands safely • Second stage motor burn • Sustainer reaches apogee, deploys drogue parachute • Descent under drogue • Main parachute deploys, slowing rocket to safe landing speed • Sustainer lands safely

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

  6. Entire Vehicle • CP 70” (from nosetip) • CG 93” (from nosetip) • Static Margin5.75 calibers Length 120” Diameter 4” Liftoff weight 21 lbs (9 kg) Motor K1100T

  7. Sustainer • CP 51” (from nosetip) • CG 63” (from nosetip) • Static Margin 3calibers Length 82” Diameter 4” Liftoff weight 14 lbs (6 kg) MotorsAT-K1100T (booster), AT-J1299N (sustainer)

  8. Vehicle Schematics

  9. Fins: 1/32” G10 fiberglass + 1/8” balsa sandwich Body: fiberglass tubing, fiberglass couplers Bulkheads: 1/2”plywood Motor Mounts: 54mm phenolic tubing, 1/2” plywood centering rings Nosecone: commercially made plastic nosecone Rail Buttons: standard nylon rail 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 Plan

  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 Plan

  20. Verification Matrix

  21. Part II: Payload

  22. Determine the effect of acceleration on the crystallization from the supersaturated sodium acetate (CH3COONa) solution Determine the effects of impurities (dopes) on the crystallization of sodium acetate under high and low accelerations Payload Objectives

  23. Crystallization will initiate at ignition Sensors will successfully obtain temperature and acceleration data through flight Collected data are accurate Payload Success Criteria

  24. 1a. Reaction initiation at ignition 1b. Ignition, data acquisition 2. The second stage ignition and data acquisition 3. Data saved into non-volatile memory 4. Apogee, parachute deploys 5. Data downloaded and analyzed 6. Crystals examined 7. The final report is written. Experiment Sequence

  25. Our payload will be entirely in our sustainer Two identical payload modules, each module consisting of four crystallization vessels, cooling system and data acquisition electronics Preliminary Integration Plan

  26. Payload consists from two encapsulated modules, each module housing four reaction vessels Payload fits snugly in the body tube Payload wiring is hidden inside the modules Payload vents align with fuselage vents Payload Integration Plan Vents Reactor vessels Fan

  27. A fan is located at the end of each reactor chamber. The chamber will have a set of eight holes in each end to allow airflow. The moving air will maintain ambient temperature inside the payload compartments Ambient Temperature Regulation

  28. A hypodermic needle filled with the seed crystals is attached to the plunger of the solenoid When the solenoid is activated, the needle will puncture the membrane covering the glass reactor vessel and the seed crystals will enter the supersaturated solution Reaction Activation System

  29. Data Acquisition

  30. Sampling Locations: 20 thermistors per Reactor Vessel* Accelerometers/altimeters in the Electronics Bay Sampling Rate: Thermistor are sampled at 50Hz frequency Accelerometer samples at 100Hz per second with 8 times oversampling Altimeter samples at 100Hz with 8x oversampling *Thermistors are located along the vessel where we expect the most change will occur Data Acquisition

  31. The payload will measure the temperature along each reactor vessel using an array of thermistors Ambient temperature inside each payload module will be also monitored and recorded Master flight computer will provide timeline, altitude and acceleration information Data Acquisition

  32. Each reactor vessel has a dedicated printed circuit board (PCB) for data acquisition Data are sent to the Master Flight Computer Storage System (MFCSS) MFCSS logs the data in a non-volatile memory Data Acquisition

  33. Independent Variables C Pure sodium acetate solution (no impurities) I1 Concentration of impurity number 1 I2 Concentration of impurity number 2 I3 Concentration of impurity number 3 A Acceleration D Direction of reaction initiation Dependent Variables R Reaction Rate S Crystal Structure Deformities T Temperature of Reaction Variables

  34. Cooling method inside rocket Amount of sodium acetate solution Thermistors used Initiation method Controls

  35. R = f (I ) Reaction rate in relation to impurities R = f (A) Reaction rate in relation to acceleration R = f (D) Reaction rate in relation to direction of initiation S = f (I ) Crystal deformities in relation to impurities S = f (A) Crystal deformities in relation to acceleration S = f (D) Crystal deformities in relation to direction of initiation T = f (I ) Temperature profile of reaction in relation to impurities T = f (A) Temperature profile of reaction in relation to acceleration T = f (D) Temperature profile of reaction in relation to direction of initiation Correlations

  36. Commercially available sensors will be used Sensors will be calibrated Extensive testing will be done on ground Instrumentation and Measurement

  37. Test and Measurement

  38. Tested Components C1: Vessel C2: Reaction Activation Subsystem C3: Super Saturated Sodium Acetate Solution C4: Sensor Attachment Unit C5: Reaction Temperature Monitoring Subsystem C6: Reactor Chamber Ambient Temperature Sensor C7: Acceleration/Altitude Recording Subsystem C8: Cable Data Transfer C9: Fans C10: Power and Fan Activation Subsystem C11: Analog to Digital Conversion Subsystem C12: Master Flight Computer and Data Storage Subsystem Verification:Components

  39. Verification Tests V1. Drop Test V2. Connection and Basic Functionality Test V3. Pressure Sensor Test V4. Scale Model Flight V5. Temperature Sensor Test V6. Stress Test V7. Acceleration Test V8. Battery Capacity Test Verification: Tests

  40. Verification Matrix

  41. 4 inch tubing justification Minimum possible diameter for experiment Existing ejection and deployment data for 4 inch tubing Maximum possible diameter for vehicle to reach 1 mile with 2,560Ns total impulse limit Reviewer Feedback Response

  42. Questions Any questions?

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