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The Effect of Acceleration on the Crystallization of Sodium Acetate
PROJECT HOT ICE
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Part I: Vehicle
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• 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 – 18SLI launch weekend
Major Milestone Schedule
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1. First stage burn, reaction starts
2. Stage separation
3. Booster coasts to its apogee and
deploys drogue parachute
4. Booster deploys main parachute
5. Booster lands safely
6. Second stage motor burn
7. Sustainer reaches apogee, deploys
drogue parachute
8. Descent under drogue
9. Main parachute deploys, slowing
rocket to safe landing speed
10. Sustainer lands safely
Flight Sequence
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• 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
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Length 120”Diameter 4”Liftoff weight 21 lbs (9 kg)Motor K1100T
CP 70” (from nosetip)CG 93” (from nosetip)Static Margin 5.75 calibers
Entire Vehicle
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Length 82”Diameter 4”Liftoff weight 14 lbs (6 kg)Motors AT-K1100T (booster),
AT-J1299N (sustainer)
CP 51” (from nosetip)CG 63” (from nosetip)Static Margin 3 calibers
Sustainer
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Letter Part Letter PartA Nosecone H Payload Bay
B Main Sustainer Parachute I Booster Drogue Parachute
C Sustainer E-Bay J Drogue Sustainer Parachute
D Sustainer Fins K Sustainer Motor Mount
E Interstage coupler L Booster Main Parachute
F Booster E-Bay M Payload Electronics
G Booster Fins N Booster Motor Mount
Vehicle Schematics
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• 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
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Thrust Curve
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Acceleration Profile
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Velocity Profile
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Altitude Profile
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Booster SustainerFlight Stability Static Margin 5.75 3.00
Thrust to Weight Ratio
11.53 20.43
Velocity at Launch Guide Departure:
68 mph(launch rail length 144”)
Flight Safety Parameters
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Wp - ejection charge weight in pounds. dP - ejection charge pressure, 15psiV - 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
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Ejection charges will be verified in static testing when the vehicle is fully constructed.
Section Ejection ChargeBooster (Drogue) 2.0 g (of FFFF black powder)
Booster (Main) N/A (The main uses an ARRD for deployment)
Sustainer (Drogue) 1.6 g
Sustainer (Main) N/A (The main uses an ARRD for deployment)
Stage Separation Charge 0.8 g
Calculated Ejection Charges
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Component Weight Parachute Diameter
Descent Rate
Booster 62 oz. 12 in.(drogue)
53 fpsBooster 62 oz. 36 in.
(main)18 fps
Sustainer 199 oz. 24 in.(drogue)
48 fpsSustainer 199 oz. 60 in.
(main)19 fps
Parachutes
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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
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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
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V 1 V 2 V 3 V 4 V 5 V 6 V 7 V 8 V 9 V 10
C 1
C 2
C 3
C 4
C 5
C 6
C 7
C 8
C 9
C 10
C 11
C 12
C 13
Verification Matrix
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Part II: Payload
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• 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
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• Crystallization will initiate at ignition
• Sensors will successfully obtain temperature and acceleration data through flight
• Collected data are accurate
Payload Success Criteria
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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
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• 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
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• 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 PlanReactor vesselsVents
Fan
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• 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 TemperatureRegulation
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• 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
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Data Acquisition
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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
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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
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• 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
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• 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
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• Cooling method inside rocket• Amount of sodium acetate
solution• Thermistors used• Initiation method
Controls
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• 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
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• Commercially available sensors will be used
• Sensors will be calibrated
• Extensive testing will be done on ground
Instrumentation and Measurement
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Test Measurement Temperature Temperature will be
collected 50x per second by each sensor
Acceleration Acceleration will be collected 100x per second with 16x oversampling
Test and Measurement
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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
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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
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V 1 V 2 V 3 V 4 V 5 V 6 V 7 V 8
C 1
C 2
C 3
C 4
C 5
C 6
C 7
C 8
C 9
C 10
C 11
C 12
Verification Matrix
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• 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
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Questions
Any questions?