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Saint Andrews “Orion Project II” 2008 Student Launch Initiative Our Rocket will dominate the skies over Huntsville; while ...
Rocket Flight Stability <ul><li>Via Rocksim, the new data has been uploaded and tested. </li></ul><ul><li>Rocksim simulati...
CG-CP
Rail Exit Velocity <ul><li>Rocksim analysis, 6” Diam, 40 lbs loaded with L1300, 10’ rail: </li></ul><ul><li>Rail Departure...
Rocket Specifications and Performance <ul><li>Total length of vehicle……………………………10ft, 9in </li></ul><ul><li>Diameter of ve...
Motor specifications and performance <ul><li>Motor used: L1300 APCP—R </li></ul><ul><li>L = Total Impulse in Newton-second...
Parachute Sizes and Descent Rate <ul><li>Five parachutes: </li></ul><ul><li>1- 36” drogue chute </li></ul><ul><ul><li>78.3...
Test Plans and Procedures <ul><li>Robot: Pilots practicing control via radio/video link </li></ul><ul><li>Pitot tube: 220M...
Scale Model Flight Test <ul><li>½ Scale model flew successfully, with Video! </li></ul><ul><li>1 st  Pitotcruiser RDV flig...
Dual Deployment of Avionics Test <ul><li>Dual Avionics Payload </li></ul><ul><li>Aft: Black Powder 3g </li></ul><ul><li>Fo...
Ejection Charge Amount Test-CO2 <ul><li>Forward Section Ejection, 38 gram cartridges, x2 </li></ul><ul><li>Components of C...
Ejection Charge Amount Test-BP <ul><li>Aft Section Black Powder Ejection Charge section. </li></ul><ul><li>Successfully (s...
Nosecone Pitot/Video payload <ul><li>Circuit integrated fully into nosecone </li></ul><ul><li>½” Plywood Flange epoxied & ...
Nosecone Pitot circuit <ul><li>Same circuit as last year </li></ul><ul><li>Tube to Hose to Sensor to Data Logger </li></ul...
Mission Commander <ul><li>Team Orion is honored to have a passenger! </li></ul><ul><li>Gumby’s safety is mission critical ...
Altimeter Payload Bay <ul><li>All fiberglass for maximum strength </li></ul><ul><li>Double-thickness bulkplates </li></ul>...
Altimeter Bay Main Deployment <ul><li>Black powder for aft deployment, redundant, cartridges bolt to aft bulk plate </li><...
SRV-1Robot- “Scorpio” Capsule <ul><li>First basic design of capsule </li></ul><ul><li>First modified design of Capsule </l...
Payload Assembly <ul><li>All components of the capsule </li></ul><ul><li>Robot’s G force frame support </li></ul>
Payload Integration Readiness <ul><li>Capsule locked inside airframe </li></ul><ul><li>Operation of the door </li></ul>
Conclusion: <ul><li>Orion has 1 successful flight completed, 5216’, on 3/9/08.  </li></ul><ul><li>Orion is ready for Hunts...
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St. Andrews Team Orion FRR PPT-Modified PM

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Transcript of "St. Andrews Team Orion FRR PPT-Modified PM"

  1. 1. Saint Andrews “Orion Project II” 2008 Student Launch Initiative Our Rocket will dominate the skies over Huntsville; while our Payload hunts for valuable data to gather for our experiments. Flight Readiness Review: March 24, 2008 Robotic Deployment & Recovery-Search & Locate Mother Ship Surface Sample Analysis-Pitot-Tube Air Speed Factors Contact: LT. Leonard Johnson- Project Team Leader PH: (847) 698-0018 E-mail: firebrick720@yahoo.com Video Study of Vehicle Stability Flight Profile Pitot Readings for Velocity and Air Speed 1 st test flight, 5216’, 3/9/08!
  2. 2. Rocket Flight Stability <ul><li>Via Rocksim, the new data has been uploaded and tested. </li></ul><ul><li>Rocksim simulations have been run, verifying our rocket’s flight worthiness. </li></ul><ul><li>Test flight on 3/9/08 positively confirmed stability. </li></ul>
  3. 3. CG-CP
  4. 4. Rail Exit Velocity <ul><li>Rocksim analysis, 6” Diam, 40 lbs loaded with L1300, 10’ rail: </li></ul><ul><li>Rail Departure Velocity=35 ft/sec </li></ul><ul><li>Minimum velocity for Stable flight=46ft/sec </li></ul>
  5. 5. Rocket Specifications and Performance <ul><li>Total length of vehicle……………………………10ft, 9in </li></ul><ul><li>Diameter of vehicle airframe…………………….6in </li></ul><ul><li>Liftoff Mass fully loaded………………………….45lbs, 10oz. </li></ul><ul><li>Vehicle stability: positive two caliber (airframe diameter) Separation between CG and CP (center of gravity and center of pressure) </li></ul><ul><li>Thrust to weight ratio……………………………..6.48 : 1 </li></ul><ul><li>Liftoff velocity off launch rail……………………..35 ft/sec </li></ul><ul><li>Maximum velocity during flight…………………..700ft/sec </li></ul><ul><li>Time to Apogee (peak altitude)………………….20.5 sec </li></ul><ul><li>Drogue chute descent Velocity…………………………………………….76ft/sec </li></ul><ul><li>Main parachute deployment at: ………………...800ft AGL (above ground level) </li></ul><ul><li>Descent velocity rate on main chute…………...19.8ft/sec </li></ul><ul><li>G-Forces experienced by rocket and payloads...5.86G’s </li></ul><ul><li>Maximum Altitude achieved at apogee………….5,216ft AGL </li></ul><ul><li>NASA required an apogee of…………………….5,280ft AGL </li></ul><ul><li>Pitot Cruiser RDV was 64ft off the NASA required target altitude. </li></ul>
  6. 6. Motor specifications and performance <ul><li>Motor used: L1300 APCP—R </li></ul><ul><li>L = Total Impulse in Newton-seconds </li></ul><ul><li>1300 = Average Thrust in Newtons </li></ul><ul><li>4.45 Newtons = 1 pound of thrust </li></ul><ul><li>Our motor has an average thrust of 292 pounds </li></ul><ul><li>APCP = Ammonium perchlorate composite propellant – same fuel and oxidizer used on the Space Shuttle Solid Rocket Boosters (SRB’s) </li></ul><ul><li>R = Reloadable motor (motor case can be reused again) </li></ul><ul><li>Manufacturer: Aerotech </li></ul><ul><li>Propellant mass: 2,632g = 5.8lbs </li></ul><ul><li>Total Impulse rating: 4,567 Newton-seconds </li></ul><ul><li>Total Impulse is proportional to the total energy released by the propellant in a propulsion system </li></ul><ul><li>Motor dimensions: 98mm diameter x 443mm length (3.9in diameter x 17.4in length </li></ul><ul><li>Burn time: 3.5 seconds </li></ul><ul><li>Burn time is calculated by dividing the Total Impulse by the average thrust ratings: L=5120 Newton-seconds </li></ul><ul><li>Thrust to weight ratio: 50 : 1 </li></ul>
  7. 7. Parachute Sizes and Descent Rate <ul><li>Five parachutes: </li></ul><ul><li>1- 36” drogue chute </li></ul><ul><ul><li>78.3ft./sec. descent rate </li></ul></ul><ul><li>1- 45” nose cone chute </li></ul><ul><li>19.8ft./sec. descent rate </li></ul><ul><li>1- 45” capsule chute </li></ul><ul><li>19.8ft./sec. descent rate </li></ul><ul><li>1- 120” main chute </li></ul><ul><li>20.8ft./sec. descent rate </li></ul><ul><li>1- 12” safety chute for Mission Cdr. Gumby; </li></ul><ul><li>28.6ft./sec. descent rate </li></ul>Rocket Hunter frequency is 219.719 MHz
  8. 8. Test Plans and Procedures <ul><li>Robot: Pilots practicing control via radio/video link </li></ul><ul><li>Pitot tube: 220MPH leafblower test done </li></ul><ul><li>BP ejection test done </li></ul><ul><li>CO2 ejection test done </li></ul><ul><li>Flight video: successful integration into nosecone! </li></ul><ul><li>1 st test flight successful! </li></ul>
  9. 9. Scale Model Flight Test <ul><li>½ Scale model flew successfully, with Video! </li></ul><ul><li>1 st Pitotcruiser RDV flight: 3/9/08 </li></ul><ul><li>Internal video camera running during flight. </li></ul>
  10. 10. Dual Deployment of Avionics Test <ul><li>Dual Avionics Payload </li></ul><ul><li>Aft: Black Powder 3g </li></ul><ul><li>Fore: Carbon Dioxide (for low temperature, noncorrosive gasses on robot. 38g x 2) </li></ul><ul><li>Dual, redundant altimeters for maximum flight safety. </li></ul><ul><li>Worked perfect, 3/9/08! </li></ul>
  11. 11. Ejection Charge Amount Test-CO2 <ul><li>Forward Section Ejection, 38 gram cartridges, x2 </li></ul><ul><li>Components of CO2-Rouse-Tech, has been test fired twice. </li></ul><ul><li>Successfully ejected main at 800’ on 3/9/08!!! </li></ul>
  12. 12. Ejection Charge Amount Test-BP <ul><li>Aft Section Black Powder Ejection Charge section. </li></ul><ul><li>Successfully (static) tested 2/08. </li></ul><ul><li>Successfully ejected at apogee, 5216’, on 3/9/08!!! </li></ul>
  13. 13. Nosecone Pitot/Video payload <ul><li>Circuit integrated fully into nosecone </li></ul><ul><li>½” Plywood Flange epoxied & screwed in nosecone </li></ul><ul><li>5 bolts hold bulkhead to flange </li></ul><ul><li>Offset center for ease of reaching switches </li></ul><ul><li>Camera below pitot electronics. </li></ul>
  14. 14. Nosecone Pitot circuit <ul><li>Same circuit as last year </li></ul><ul><li>Tube to Hose to Sensor to Data Logger </li></ul><ul><li>Data downloaded to Laptop PC, Excel </li></ul><ul><li>Calibration via 220MPH blower </li></ul>
  15. 15. Mission Commander <ul><li>Team Orion is honored to have a passenger! </li></ul><ul><li>Gumby’s safety is mission critical </li></ul><ul><li>Will have backpack parachute for safety </li></ul><ul><li>Moved to shock cord just forward of main chute. </li></ul><ul><li>A “stunt-double” Gumby flew and was recovered unharmed on 3/9/08! </li></ul>
  16. 16. Altimeter Payload Bay <ul><li>All fiberglass for maximum strength </li></ul><ul><li>Double-thickness bulkplates </li></ul><ul><li>2 x ¼” threaded rods hold it together </li></ul><ul><li>Two redundant altimeters (Missile Works and Ozark) </li></ul>
  17. 17. Altimeter Bay Main Deployment <ul><li>Black powder for aft deployment, redundant, cartridges bolt to aft bulk plate </li></ul><ul><li>CO2 for foreward deployment, redundant, Rouse Tech., bolted to fore bulk plate </li></ul><ul><li>Pyrodex combustion forces piston pin into CO2 cartridge </li></ul>
  18. 18. SRV-1Robot- “Scorpio” Capsule <ul><li>First basic design of capsule </li></ul><ul><li>First modified design of Capsule </li></ul><ul><li>Final design of Capsule in airframe </li></ul><ul><li>Successfully ejected from airframe by CO2 2/08. </li></ul><ul><li>Prototype successfully ejected at 800’ on 3/9/08 </li></ul>
  19. 19. Payload Assembly <ul><li>All components of the capsule </li></ul><ul><li>Robot’s G force frame support </li></ul>
  20. 20. Payload Integration Readiness <ul><li>Capsule locked inside airframe </li></ul><ul><li>Operation of the door </li></ul>
  21. 21. Conclusion: <ul><li>Orion has 1 successful flight completed, 5216’, on 3/9/08. </li></ul><ul><li>Orion is ready for Huntsville! </li></ul>
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