vehicle dimensions, materials, and justifications static stability margin plan for vehicle safety...
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Atomic Aggies
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Vehicle dimensions, materials, and justifications Static stability margin Plan for vehicle safety verification and testing Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview Drawing/Discussion of each major component and
subsystem Baseline payload design Payload
Overview
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Main Body: 5.5 inch diameter Blue Tube chosen for strength, price, low weight
Nosecone: Polycarbonate Ogive 1/8” plywood fins chosen for availability of material Overall length: 117.14 inches Approximate Loaded Weight: 34.36 lb.
Vehicle Specifications Team Leader/Vehicle Design: Stacie Benally
Vehicle Design: Valentin Lopez
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Static Stability Margin
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Atomic Aggies will follow NAR High-Power Rocketry Safety Code.
Proper use of personal protective equipment will be used when handling hazardous materials during construction of the rocket.
Ejection Ground Test will be done before every pre-competition launch.
Safety Checklist will be used to ensure that the rocket is safe to fly.
At least one subscale flight and one full scale flight will be done prior to competition.
SafetySafety Officer: Crystal Escamilla
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Manufactory EngineClass/Model
Diameter (mm)
Length (in)
Burn Time (s)
Impulse (N-s)
Avg. thrust(N)
RockSim Altitude (ft.)
Loki L930-LW 75 19.6 4.17 3285 794.6 5600
Motor Selection & Justification
• Motor is flexible for variances in atmospheric conditions
• At breezy winds simulations show 24 oz. of ballast will meet the required altitude of 5280 ft. and at calm wind conditions simulations show 28 oz. of ballast is required to meet the altitude of 5280 ft.
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Thrust-to-Weight Ratio & rail exit Velocity
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Subscale test launch:◦ Planned launch on November 17
Full scale test launch:◦At least one test launch is planned for January 26◦Combining the data from the full scale launch as well
as the subscale launches we plan on having a flawless competition launch
◦A possible second test launch is planned if needed
Launch, Test Plan Overview
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Drogue Parachute: Elliptical Custom 24” diameter Decent Rate: 75 ft/s
Main Parachute: Iris Ultra 96” diameter Decent Rate: 16.53 ft/s
Duel Deployment Recovery SystemCrystal Escamilla & Edgar Gonzalez
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Recovery Subsystem Flight Details & Specifications
Apogee Decent/Drogue Decent/Main
Weight (lbs) 25.875 lb 25.875 lb 25.875 lb
Velocity (ft/s) .0164 ft/s 75 ft/s 16.53 ft/s
Kinetic Energy (ft lbf) Section 1 -698.758 ft-lbSection 2 -434.724 ft-lbSection3 -1048.14 ft-lb
Section 1 -27.95 ft-lbSection 2 -17.46 ft-lbSection3 -41.92 ft-lb
24” Drogue parachute Deployments @ Apogee
96” Main Parachute Deployment @ 500ft
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Avionics Bay
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Payload DesignScientific Design Leader: Jon
PinckleyLayout Leader: Sean Brooks
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Payload Integration/Testing
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Sensors Controller
DE0-NANO BOARD
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Funding Educational Engagement
Project Plan Update
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Questions from Panel?