Florida A & M University Flight Readiness Review 11/19/2010 Preliminary Design Review 1
Overview Team Summary ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Vehicle Criteria ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Payload Criteria ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Activity Plan ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Conclusion 11/19/2010 Preliminary Design Review 2
Team Summary Team Name: Diamondbacks University: Florida A & M University Location: Tallahassee, Florida Mentors: Team Official: Dr. Clement Allen Propulsion: Terry Zimmerman Solar Physics / X-Ray Astronomy: Dr. Ray O Neal Mathematician: Dr. Bruno Guerrieri Roboticist: Dr. Carl Moore Electronics: Leon Prosper Team Members: Project Manager: Triesha Fagan Solange Artie Ronald Benson John Cannon Karl Hewling Dominique Hubbard Jamie Johnson Lee Andrew Green Jr. Deanna McKenzie Dion Paul Shannon Whyms Maynard G. Yates 11/19/2010 Preliminary Design Review 3
Vehicle Criteria 11/19/2010 Preliminary Design Review 4
Launch Vehicle Summary Material: G10 fiberglass Length : 109 Diameter: 5 Gross Weight: 24.9 lbs Dual Deployment: yes, drogueless Fins: 4 Motor Mount: 54 mm Electronic Bay: 12 Motor Specifications: Loki K350 Bates Recovery System: Redundant Avionics board (w/ kill switch) - (2) MiniAlt/WD Altimeters (Dual Deployment) - (1) Alt15k Altimeter (for official altitude records) Beeline GPS and transmitter system (post-landing rocket recovery) Main Parachute : 84" ripstop nylon conical parachute, ~16" spill hole (Public Missiles, Ltd.) - ¾ Strap Tubular Nylon 11/19/2010 Preliminary Design Review 5
Yellow Electronic Bays Green Bulkhead Couplers/Nosecone Red Bulkheads for main electronic bay Pink Centering Rings
Vehicle Criteria Deliver payload close to a mile (5280 ft.) without exceeding it Recovery System Electronics : redundant and accessible with ability to be locked in position Recoverable/Reusable Shear Pins Landing Velocity Landing Distance GPS Transmitter 11/19/2010 Preliminary Design Review 7
Recovery Subsystem 11/19/2010 Preliminary Design Review 8
Recovery Subsystem: Parachute Determine appropriate mass for a particular landing velocity, given a chute diameter: Chute Diameter (in.) Landing Velocity (ft/s) Mass of Fully Loaded Rocket Chute Diamete r (in.) Landing Velocity (ft/s) Mass of Fully Loaded Rocket Chute Diamete r (in.) Landing Velocity (ft/s) Mass of Fully Loaded Rocket 84 18 11.0937 96 18 14.6051 120 18 22.3738 84 18.5 11.7186 96 18.5 15.4278 120 18.5 23.6341 84 19 12.3606 96 19 16.273 120 19 24.9289 84 19.5 13.0197 96 19.5 17.1407 120 19.5 26.2582 84 20 13.6959 96 20 18.031 120 20 27.622 84 20.5 14.3893 96 20.5 18.9438 120 20.5 29.0204 84 21 15.0997 96 21 19.8792 120 21 30.4533 84 21.5 15.8273 96 21.5 20.8371 120 21.5 31.9207 84 22 16.5721 96 22 21.8175 120 22 33.4226 11/19/2010 Preliminary Design Review 9
Test Plans and Procedures Rocket To test the rocket airframe s ability to withstand the forces applied upon it in flight, multiple rocket launches will be conducted with the subscale and fullscale rocket, with mass objects. Recovery System Dual Deployment Altimeters The dual deployment altimeters will be tested in a pressure tank, along with a digital barometer, in order to verify accuracy of the altimeter readings. The altimeters ability to ignite the charges for the nosecone and parachute will be tested on the ground in the presence of NAR representative GPS Logger GPS Logger will be tested by analyzing and comparing data collected to a digital gps system. Payload The meters will be tested by analyzing their data against commercially available thermometers, barometres, and hygrometers. The on-board computer, Xbee module will be tested for compatibility and abilty to transmit at distance up to a mile. 11/19/2010 Preliminary Design Review 10
Dual Deployment Avionics Test Test 1: Insert lightbulbs into ejection charge holder. Place e-bay in vaccum chamber. Check for flashing of lightbulbs at simulated apogee/descent altitude. Result: Fail, lightbulbs on onlu one side lite up. Test 2: Turn altimeter on listen to the beeps for continuity Result 1: Fail, Light bulbs are loose. Troubleshoot: put tape around base of lightbulb Result 2: Success 11/19/2010 Preliminary Design Review 11
Ejection Charge Amount Test Test 1: Ability of 6 grams of blackpowder to eject nosecone and parachute components Result: Successful deployment of nosecone and parachute Test 2: Ability of 3 grams of blackpowder to eject booster casing Result 1: Fail, charges did not ignite Troubleshoot: Check altimeter wires Result 2: Fail, charges still did not ignite Troubleshoot: ejection charge holder is larger than charges. All holders were replaced. Result 3: Success 11/19/2010 Preliminary Design Review 12
Fullscale Launch Test Results Gross Weight (w/o motor) = 24.9 lbs Altitude: 4046 ft. Arming Altimeters: difficult due to entry hole position, but able to lock Recoverable and Reusable: yes, with repairs Shear Pins : 6, all broke off to let cone go Landing Velocity: 28 ft/s Landing Distance from Pad: 210 ft. GPS Transmitter: Charge Battery/Acquire 11/19/2010 Preliminary Design Review 13
Simulation Sensitivities: Temperature: 80 F,degrees Wind Speed Model: 3-7 mph Wind Turbulence: Some variability Latitude : 220 deg 11/19/2010 Preliminary Design Review 14
0.05 6.65 13.25 19.85 26.45 33.05 39.65 46.25 52.85 59.45 66.05 72.65 79.25 85.85 4500 4000 3500 3000 2500 2000 1500 1000 500 0-500 Altimeter #2 - Altitude (ft.) Altimeter #2 - Altitude (ft.) 4500 4000 3500 3000 2500 2000 1500 1000 500 0-500 Altimeter #2 - Altitude (ft.) Altimeter #2 - Altitude (ft.) 0.05 6.2 12.35 18.5 24.65 30.8 36.95 43.1 49.25 55.4 61.55 67.7 73.85 80 86.15
Rail Exit Velocity at the end of an 8ft. Rail is : 190 ft/s or 129 mph 11/19/2010 Preliminary Design Review 17
Test Launch Schedule Rocket Payload Recovery System 11/19/2010 Preliminary Design Review 18
Payload Criteria 11/19/2010 Preliminary Design Review 19
Payload Experiment and Design 03/21/2011 Payload Experiment & Design 1
The Primary Experiment Rocket video camera used to locate target position. Once the target is located, directions are determined and used for navigation Gazebo simulator. 02/22/2011 Payload Experiment & Design 21
The Secondary Experiment Record Environmental Sensor Readings pressure temperature relative humidity solar irradiance ultraviolet radiation Record Still Images 2 during descent, 3 after landing pictures taken portray the sky toward the top of the frame and the ground toward the bottom of the frame 02/22/2011 Payload Experiment & Design 22
Payload Equipment BoosterVision GearCam Mile High Combo Beeline Mega Deal Alt15K/WD Rev2 logging altimeter minialt/wd logging dual event altimeter Apogee Instruments SU-100 S3-R1-A Solar Radiation detector ulog - The Lil'est Logger Zeiss MiniQuick Telescope 02/22/2011 Payload Experiment & Design 23
Activity Plan 11/19/2010 Preliminary Design Review 24
Educational Engagement Objective: Projects inspire an interest in the Science, Technology, Engineering, and Math (STEM) fields Partner with NSBE A Walk for Education Event FAMU STEM Learning Community 2011 ARTSI Conference 11/19/2010 Preliminary Design Review 25
Educational Engagement A Walk for Education Jack L. McClean Jr. Community Center Engineering Activities for K -12 students Rocket Activity FAMU STEM LC Recruitment Event 2011 ARSTI Student Research Conference Student Oral Presentation Presentation Title: High Altitude Robot Navigation 11/19/2010 Preliminary Design Review 26
Conclusion 11/19/2010 Preliminary Design Review 27
The team was able to design and construct a rocket, and successfully launch a recoverable rocket. Even though our rocket did not land in one piece, we are very proud of our effort, and are in the process of designing and reconstructing another rocket which will land in one piece and reach the 1-mile mark without going over. The second time around will be much less complex than the first time. We look forward to competing in April. 11/19/2010 Preliminary Design Review 28