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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
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
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
Liftoff weight 21 lbs (9 kg)
Liftoff weight 14 lbs (6 kg)
Body: fiberglass tubing, fiberglass couplers
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
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)
Ejection charges will be verified in static testing when the vehicle is fully constructed.
C1: Body (including construction techniques)
C3: Data Acquisition System (custom computer board and sensors)
C7: Ejection charges
C8: Launch system
C9: Motor mount
C11: Shock cords and anchors
C12: Rocket stability
C13: Second stage separation and ignition electronics/charges
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
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.
Determine the effects of impurities (dopes) on the crystallization of sodium acetate under high and low accelerations
Sensors will successfully obtain temperature and acceleration data through flight
Collected data are accurate
Payload Success Criteria
Two identical payload modules, each module consisting of four crystallization vessels, cooling system and data acquisition electronics
Preliminary Integration Plan
Payload fits snugly in the body tube
Payload wiring is hidden inside the modules
Payload vents align with fuselage vents
Payload Integration Plan
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
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
20 thermistors per Reactor Vessel*
Accelerometers/altimeters in the Electronics Bay
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
Ambient temperature inside each payload module will be also monitored and recorded
Master flight computer will provide timeline, altitude and acceleration information
Data are sent to the Master Flight Computer Storage System (MFCSS)
MFCSS logs the data in a non-volatile memory
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
D Direction of reaction initiation
R Reaction Rate
S Crystal Structure Deformities
T Temperature of Reaction
Amount of sodium acetate solution
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
Sensors will be calibrated
Extensive testing will be done on ground
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
C10: Power and Fan Activation Subsystem
C11: Analog to Digital Conversion Subsystem
C12: Master Flight Computer and Data Storage Subsystem
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
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