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The University of North Dakota Flight Readiness Review

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The University of North Dakota Flight Readiness Review

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    1. The University of North Dakota Flight Readiness Review 3/26/2012

    2. Key Design Features Two stage launch system Dual deployment recovery system for sustainer Single parachute recovery for booster Payload located within motor mount section of sustainer airframe

    3. Launch Vehicle Design 2 stage rocket to accommodate the I350 motor Sustainer section is 68.5 in. in length Booster section is 21 in. in length CP = 65.71 in. CG = 57.72 in.

    4. Design Features

    5. Motor Descriptions Sustainer motor – I350R Transparent motor casing This motor is required, as it is the core of our science payload Booster motor – I284W Selected to get the rocket to the desired mile altitude after I350 burn

    6. Flight Stability

    7. Thrust-to-Weight Ratio Thrust to weight ratio for both stages, using booster motor thrust = 22.46 Thrust to weight ratio for sustainer, using sustainer motor thrust = 33.81 Rail exit velocity = 73.08 ft/s

    8. Mass Statement (Sustainer) TOTAL MASS = 10.11 lbs. Nose Cone – 8.7 oz. Fore Airframe – 5.9 oz Coupler/Altimeter Bay – 21.8 oz. Fin Can w/ fins – 36.128 oz Payload – 8.25 oz. Misc mass - 10

    9. Mass Statement (Booster) Interstage coupler – 3.86 oz Air Frame – 9.28 oz Fins – 1.77 oz Motor tube – 4.82 oz Centering rings – 1.88 oz

    10. Parachute Info Duel deployment system for the sustainer 12 inch Drogue at apogee 56 inch Main at 900ft 26 inch booster parachute 1 inch thick rip stop nylon shock cord 15 ft length for drogue harness, 20 ft length for main harness, 15 ft for the booster harness Landing velocity is 23.56 ft/s

    11. Kinetic Energy During descent Fore section – 457.94 ft-lb Aft section – 684.19 ft-lb Booster section – 271.95 ft-lb Upon Landing Nose cone – 4.69 ft-lb Fore airframe – 14.92 ft-lb Fin can – 29.33 ft-lb

    12. Projected Altitude 0-2 mph = 6092.75 ft 3-6 mph = 6072.18 ft 8-14 mph = 5946.82 ft 15-25 mph = 5601.87 ft We believe the RockSim simulation is not entirely accurate, as the delay between sustainer ignition could not be timed properly. Therefore, we believe the rocket will not reach the altitude indicated.

    13. Drift from Launch pad 3-6 mph = 520 ft 8-14 mph = 1366 ft 15-20 mph = 2394 ft Determined by looking at the drift in the RockSim flight simulations

    14. Test Plans and Procedures Test assembly for I350 motor has been assembled Static ground test will be conducted on March 30 Altimeter, power supply, and black powder charge done in subscale tests Dual deployment recovery system tested in subscale and scale launch tests

    15. Flight Test 3rd and final sub-scale launch on March 5 Altitude of 3,744 ft reached Construction on full-scale commenced immediately Full-scale test flight could not be completed by presentation submission due to team and mentor availabilty

    16. Recovery Systems Tests Dual deployment recovery system tested in all 3 sub-scale flights Booster parachute deployment tested in sub-scale flight #3 All recovery systems will be tested in the upcoming full-scale test flight

    17. Requirements Verification Simulations indicate that the science payload will reach an altitude near the 1 mile mark at subsonic speeds The sustainer’s dual deployment recovery system will have a drogue and main chute and will be fully recoverable and reusable The booster will also have a parachute recovery system for a safe and reusable landing The booster and sustainer will both be equiped with a Rocket Hunter

    18. Payload Design 3 cameras Mounted above the I350R Motor Integrated batteries and data storage (microSD) Aimed at distinct quadrants around motor retainer Pointed at mirrors at distances of 14 in, 10 in, and 6 in Allows larger field of view and straight on recording of video

    19. Payload Integration The cameras are epoxied to plywood sections 4 inches in length which form a cross corresponding to that of the motor retainer. The end is capped by and epoxied to a carbon fiber bulkhead The bulkhead is screwed along the motor to the retainer plate using two threaded bolts.

    20. Interfaces with Ground Systems We will not have any in-flight interfaces between the vehicle and the ground. Experimental data from our payload will be retrieved upon recovery of the vehicle.

    21. Payload Requirements Verification The cameras can record video for more than an hour Data will be transferrable to a computer via a USB cable after recovery The centerpiece of the payload, the I350 motor, is a commercially available motor

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