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Iowa State University CySLI CDR Presentation

Iowa State University CySLI CDR Presentation. Deployment of Unmanned Aerial Vehicle. Rocket Flight S tability . The proposed vehicle, ready for launch, has the following stability margins - Center of Pressure – 90.4” - Center of Gravity – 78.2” - Stability Margin – 1.59 Calibers.

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Iowa State University CySLI CDR Presentation

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  1. Iowa State University CySLI CDR Presentation Deployment of Unmanned Aerial Vehicle

  2. Rocket Flight Stability The proposed vehicle, ready for launch, has the following stability margins - Center of Pressure – 90.4” - Center of Gravity – 78.2” • - Stability Margin – 1.59 Calibers

  3. Thrust to Weight Motor Selection Using the Cesaroni L-800, we have a thrust to weight ratio of approximately 7. This was calculated from our flight simulation data and the following thrust curve. (The 225lbs of thrust used in the calculation is held for the first 1.5 seconds of the burn)

  4. Rail Exit Velocity The following graph shows the rockets velocity and acceleration up to an altitude of 6ft (length of rail). The rail exit velocity is 49 ft/sec.

  5. Parachute Sizes and Descent Rates Drogue Parachute: 24” Decent Rate: 94 ft/sec Main Parachute: 100” Tac-9(A) Decent Rate: 22.5 ft/sec

  6. Test Plans and Procedures R-DAS Function Test – Verified R-DAS has successfully supplied dual deployment in a real launch situation. Scale Model and PerfectFlite Altimeter Test – Verified Altimeter has successful supplied proper electricity to ejection charges in launch. Payload Test – In Process The payload has been tested for feasibility, but the actual payload has not yet been tested. Static Ejection Charge Test – Not Yet Verified Ejection charges will be ignited inside of upper and lower assemblies Full Scale Vehicle Test – Not Yet Verified Rocket and payload will be tested in full scale launch

  7. Scale Model Flight Test The rocket was launched off of the rail and safely ascended to an altitude of 1241 ft. The altimeter was recovered and was found to have burned both nicrome wires set to burn at apogee and 500 ft.

  8. Dual Deployment Avionics Test Rocket Data Acquisition System: Tested in real launch, performed to specifications Perfectflite MWAD Altimeter: Tested in real launch, performed to specifications

  9. Ejection Charge Amount Test Wp = dP * V / R * T dP - is the ejection charge pressure in psi. R - is the combustion gas constant, 22.16 (ft- lbf/lbm R) for FFFF black powder. T - is the combustion gas temperature, 3307 degrees R for black powder. V - is the free volume in cubic inches. Wp - is the charge weight (mass, actually) in pounds. Calculated ejection charge amout: 5.5 Grams Number of 2-56 Nylon Screws: 6

  10. Payload Integration Feasibility Vehicle ejects deployment bay at apogee (still attached to shock chord) Payload is released near 1000 feet altitude Payload and vehicle decent separately

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