St. Andrews Team Orion FRR PPT-Modified PM
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Transcript of St. Andrews Team Orion FRR PPT-Modified PM
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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 ShipSurface Sample Analysis-Pitot-Tube Air Speed Factors
Contact: LT. Leonard Johnson- Project Team LeaderPH: (847) 698-0018
E-mail: [email protected]
Video Study of Vehicle Stability Flight ProfilePitot Readings for Velocity and Air Speed
1st test flight, 5216’, 3/9/08!
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Rocket Flight StabilityRocket 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.
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CG-CPCG-CP
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Rail Exit VelocityRail 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
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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 AGLPitot Cruiser RDV was 64ft off the NASA required target altitude.
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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
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Parachute Sizes and Descent RateParachute 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
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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!• 1st test flight successful!
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Scale Model Flight TestScale Model Flight Test
• ½ Scale model flew successfully, with Video!
• 1st Pitotcruiser RDV flight: 3/9/08
• Internal video camera running during flight.
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Dual Deployment of Avionics TestDual 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!
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Ejection Charge Amount Test-CO2Ejection 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!!!
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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!!!
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Nosecone Pitot/Video payloadNosecone 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.
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Nosecone Pitot circuitNosecone 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
MPH Data from 6" Nose vs. Leafblower 1/1/08
-50
0
50
100
150
200
250
1 101 201 301 401 501 601 701 801 901
Time, spls at 0.5sec each
MP
H
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Mission CommanderMission 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!
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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)
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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
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SRV-1Robot- “Scorpio” CapsuleSRV-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
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Payload AssemblyPayload Assembly
• All components of the capsule
• Robot’s G force frame support
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Payload Integration ReadinessPayload Integration Readiness
• Capsule locked inside airframe
• Operation of the door
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Conclusion:Conclusion:Orion has 1 successful flight completed, 5216’, on 3/9/08.
Orion is ready for Huntsville!