St. Andrews Team Orion FRR PPT-Modified PM
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St. Andrews Team Orion FRR PPT-Modified PM

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St. Andrews Team Orion FRR PPT-Modified PM Presentation Transcript

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