Florida A & M University. Flight Readiness Review. 11/19/2010 Preliminary Design Review
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1 Florida A & M University Flight Readiness Review 11/19/2010 Preliminary Design Review 1
2 Overview Team Summary ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Vehicle Criteria ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Payload Criteria ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Activity Plan ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Conclusion 11/19/2010 Preliminary Design Review 2
3 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
4 Vehicle Criteria 11/19/2010 Preliminary Design Review 4
5 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
6 Yellow Electronic Bays Green Bulkhead Couplers/Nosecone Red Bulkheads for main electronic bay Pink Centering Rings
7 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
8 Recovery Subsystem 11/19/2010 Preliminary Design Review 8
9 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 /19/2010 Preliminary Design Review 9
10 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
11 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
12 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
13 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
14 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
15
16 Altimeter #2 - Altitude (ft.) Altimeter #2 - Altitude (ft.) Altimeter #2 - Altitude (ft.) Altimeter #2 - Altitude (ft.)
17 Rail Exit Velocity at the end of an 8ft. Rail is : 190 ft/s or 129 mph 11/19/2010 Preliminary Design Review 17
18 Test Launch Schedule Rocket Payload Recovery System 11/19/2010 Preliminary Design Review 18
19 Payload Criteria 11/19/2010 Preliminary Design Review 19
20 Payload Experiment and Design 03/21/2011 Payload Experiment & Design 1
21 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
22 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
23 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
24 Activity Plan 11/19/2010 Preliminary Design Review 24
25 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
26 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
27 Conclusion 11/19/2010 Preliminary Design Review 27
28 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
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