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: [email protected]Video Study of Vehicle Stability Flight Profile Pitot Readings for Velocity and Air Speed 1 st test flight, 5216’, 3/9/08!
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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.
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.
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
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
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!
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.
Dual Deployment of Avionics TestDual Deployment of Avionics Test