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CySLI

CySLI. Iowa State University Controlled Decent Video Reconnaissance Vehicle (CDVRV) . Vehicle Properties. Dimensions, Materials/Justifications, Stability. Vehicle Design. Dimensions: Length – 104” Diameter – 7.7” Weight – 46 lbs. Vehicle Design.

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CySLI

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  1. CySLI Iowa State University Controlled Decent Video Reconnaissance Vehicle (CDVRV)

  2. Vehicle Properties Dimensions, Materials/Justifications, Stability

  3. Vehicle Design Dimensions: Length – 104”Diameter – 7.7”Weight – 46 lbs

  4. Vehicle Design The following three simulations are of a Cesaroni L1115. Simulation 1: 0-2 mph wind Simulation 2: 3-7 mph wind Simulation 3: 8-14 mph wind

  5. Vehicle Design Max. Altitude – 5411.0ftMax. Velocity – 587.5ft/sMax. Acceleration – 225.5ft/s^2 For a Simulation with Calm Winds of 0-2 mph

  6. Vehicle Design Stability Parameters: CP – 80.3”CG – 51.0”Stability Margin – 3.8 Calibers

  7. Recovery System • Location: Payload Bay • Deployment of drogue parachute at apogee using black powder charge. • Using 48 inch drogue parachute • Deployment of main parachute using black powder charge at 500ft • Using two 96 inch main parachutes

  8. Ejection Charges 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. Wp~5 grams in upper body tube. Wp~5 grams in lower body tube.

  9. Electronics Rocket Data Acquisition System Perfectflite MAWD Altimeter

  10. Vehicle Design • SAFETY • Prior to launch(es), all vehicle systems will be thoroughly inspected • Motor casing – cracks, security • Retention fittings – cracks, security • Coupler fit • Shear pin installation • Security of bulkheads • Avionics - security • Recovery integration • Fin security (through-the-wall) • Launch Controller – Will be tested statically

  11. Test Plans and Procedures R-DAS Function Test – Previously Successful R-DAS has successfully supplied dual deployment in prior launch situations. PerfectFlite Altimeter Test – Previously Successful Altimeter has successful supplied proper electricity to ejection charges in prior launches. Payload Test – In Process Measures for testing the payload will begin upon the construction of the payload. Current methods for testing are in development. Static Ejection Charge Test – Not Yet Verified Ejection charges will be ignited inside of upper and lower assemblies Scale Vehicle Test – Not Yet Verified Rocket will be tested in a scale launch in early January 2012. Construction has begun and will be completed shortly after Winter Break.

  12. Motor Selection Properties/Justification, Thrust-to-Weight Ratio, Safety

  13. MOTOR SELECTION Cesaroni L1115 Properties: Avg. Thrust – 1119 NTotal Impulse – 5015 Ns Burn Time – 4.5 s Thrust-to-Weight ratio – 5.46

  14. Payload Safety, Testing

  15. Structural Design • The payload will be a quadcopter that will deploy from the rocket at apogee with the camera and nose cone attached to it.

  16. Structural Design • The electronics for the stability of the quadcopter, the camera, and the camera controls will be located in a secure structure on the under side of the quadcopter • There will be a parachute attached to the quadcopter. This will be used to guarantee the quadcopter will be in the upright position for flight. It will also serve as a redundant system for any unfortunate failures.

  17. Control Method • Two servos will control the pan and tilt of the camera allowing a full range of motion • Radio control from ground station for the quadcopter and the camera control • Live video feed will be transmitted to the ground so that the control station will be able to direct the camera.

  18. Testing • System Simulation • Payload Only Testing • Scaled Model Testing of Rocket • Full Scale Tests of Rocket • Results

  19. Safety • Black powder redundant – Ensure proper and consistent deployment of Drogue and Main using two altimeters to ensure parachute deployment. • All recovery components will be tested on ground (static) to ensure proper configuration and to check for redundancy. • Electronics will be tested without charges to ensure proper functionality • Charges will be tested by using a mass slightly smaller than calculated and carefully moving up if necessary • All personnel will stand clear during all tests, and a countdown will be announced

  20. Question AND ANSWER

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