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Student Launch Initiative AIAA OC Section STUDENT LAUNCH INITIATIVE 2010 – 2011 AIAA OC SECTION PDR PRESENTATION December 14, 2010 1 Student Launch Initiative AIAA OC Section Agenda Introduction of team members (representing 5 high schools in Orange County California) Mission statement Vehicle • Design • GPS Transmitter • Dual Deployment Recovery System • Propulsion Scientific payload 2 Student Launch Initiative AIAA OC Section Changes since original posting on 11/19/2010 • • • • • • • • Modified slide #9: miles to mph Modified slide #11: fixed mistake, main to drogue Modified slide #15: emphasized separate recovery & payload, fixed spelling Modified slide #19: fixed spelling, added photos Added slide # 3 covering Changes since the first version Added slide #18 covering Testing Added slide #20 covering the WebSite Added slide #24 covering Mile Stones 3 Student Launch Initiative AIAA OC Section Mission Statement We, the M1 team from the AIAA Orange County Section, will construct and launch a rocket that will reach a mile high while testing hard drive latency without exceeding mach. The rocket will include a dual deployment recovery and will remain reusable. 4 Student Launch Initiative AIAA OC Section Vehicle – Black Brant • • • • • • • • • Length 80 inches Diameter 4 inches Material: G-10 Fiberglass (body tubes, couplers, fins) Liftoff Weight: 18.7 pounds Descent Weight: 15.7 pounds Recovery: Dual Redundant Electronics Center of Gravity: 49.85 inches behind the nose tip Center of Pressure: 58.97 inches behind the nose tip Stability Margin: 2.29 5 Student Launch Initiative AIAA OC Section Propulsion • • • • • • Target altitude is 5,280 feet Vehicle must remain subsonic from launch until landing Motor must lift almost 19 pounds of vehicle and payload with GPS Once design was completed launches were simulated using Rocksim Motor selected is Cesaroni K635 Redline This selection gives margin if larger or smaller motor is required Motor K530 K630 K635 K750 K590 Wind (MPH) 0 0 0 0 0 Total Impulse 1414 1681 1973 2362 2415 Rocket Mass (Ounces) 295 286 299 309 307 Maximum Altitude (feet) 3281.73 4399.61 5255.41 6455.77 6767.42 Max Velocity (ft/s) 482.43 592.27 657.76 772.76 724.74 Max Accel (ft/s2) 582.17 582.13 582.18 582.33 652.22 6 Student Launch Initiative AIAA OC Section Cesaroni K635 Redline Pro54 1994K63517A Motor Data Brandname Pro54 1994K635-17A Manufacturer Cesaroni Technology Man. Designation 1994K635-17A CAR 1994-K635-17A Designation Test Date 7/6/2003 Single-Use/Reload/Hybrid Reloadable Motor 54.00 x 488.00 Dimensions mm mm (2.13 x 19.21 in) Loaded Weight 1989.90 g (69.65 oz) Total Impulse 1749.50 Ns Propellant Weight 1281.00 g (44.84 oz) Maximum 728.70 N (163.96 Thrust lb) 656.00 N (147.60 (393.64 lb.s) Burnout Weight 658.40 g (23.04 oz) Avg Thrust Delays Tested 17 - 7 secs ISP 139.30 s Samples per second 1000 Burntime 2.66 s Notes Red Lightning™ lb) 7 Student Launch Initiative AIAA OC Section GPS TRACKING Ground Station Transmitter in Vehicle • • • • Big Red Bee Beeline GPS RF: 17mW on 433.920 MHz Battery and life: 750mAh 10 Hrs Size: 1.25” x 3” 2 ounces • Receiver: Yaesu VX-6R • TNC: Byonics Tiny Track 4 • GPS: Garmin eTrex Legend Beeline receives GPS position • Encodes as AX.25 packet data • Sends as 1200 baud audio on 433.92 MHz VX-6R receives at 433.92 MHz and extracts audio TinyTrack 4 converts audio to digital NMEA location data Garmin displays the digital location data on human screen 8 Student Launch Initiative AIAA OC Section Dual Deployment Recovery • • • • • • • Used to bring down vehicle quickly and minimize drift Smaller drogue parachute deploys at apogee Larger main parachute deploys closer to ground at 900 ft 24 inch drogue: descent rate 79.65 ft/s with 19 pound vehicle 96 inch main: descent rate 19.9 ft/s with 16 pound vehicle Maximum downrange distance is 2500 ft at 10 MPH Wind speed margin is 7 mph (within 2500 ft to 17MPH) Wind (MPH) 0 5 10 15 16 17 18 19 Wind (ft/s) 0.00 7.33 14.67 22.00 23.47 24.93 26.40 27.87 Drogue Range (feet) 0.00 403.26 806.52 1209.78 1290.43 1371.09 1451.74 1532.39 Main Range (feet) 0.00 331.47 662.93 994.40 1060.70 1126.99 1193.28 1259.58 Total Range (feet) 0.00 734.73 1469.46 2204.19 2351.13 2498.08 2645.02 2791.97 9 Student Launch Initiative AIAA OC Section Dual Deployment Electronics • Flight Computer #1 • G-Wiz Partners HCX 56G • 1.10” x 5.50” 45 grams • Accelerometer based altitude • Pyro output at Apogee • Pyro output at 900 ft altitude • 9VDC at 65ma for 3 hour battery life • Separate CPU and Pyro batteries • Safety interlock switch on body tube • Flight Computer #2 • Perfectflite MAWD •0.90” x 3.00” 20 grams • Barometric pressure based altitude • Pyro output at Apogee • Pyro output at 900 ft altitude • 9VDC at 8ma for 28 hour battery life • One battery for both CPU and Pyro • Safety interlock switch on body tube 10 Student Launch Initiative AIAA OC Section Dual Deployment Ejection Charge Ejection charge is measured amount of black powder Black powder sealed in cut-off finger of glove Glove finger contains black powder and electric match Electronics fire electric match via pyro outputs Three shear pins require 35lbs/pin or 105 pounds of force 4” bulkhead has 12.56 square inches of surface area Need a minimum of 8.4 psi – we chose 11psi to give safety margin Main ‘chute uses 1.27 grams of black powder (on-line calculator) • Body tube with the main is 4” diameter x 18” long • Drogue ‘chute uses 0.99 grams of black powder (on-line calculator) • Body tube with the drogue is 4” diameter x 14” long • • • • • • • • 11 Student Launch Initiative AIAA OC Section Launch Simulations • • • • • • • • • Simulations were run using Rocksim Over 100 simulations were run to fine tune vehicle Dimensions, proportions around avionics bay, weights were varied Target was a margin of stability between 2 and 2.5 Once vehicle was designed varied engines to attain 1 mile altitude Verified top speed was still subsonic Verified range at 10MPH wind Determined wind margin (OK to 17MPH) 12 Student Launch Initiative AIAA OC Section Scientific Payload • Hypothesis is that high “G” forces and vibration will dramatically increase the latency time of a hard disk drive • Equipment • Small Linux computer to exercise drive • 2.5” Toshiba hard disk drive (specs allow 200g forces for short time periods • G-Wiz partners HCX flight computer to measure the acceleration • LiIon Batteries and DC-DC converter • Method • Linux script gets a file from the hard drive • The script measures the time that takes • Record the time to the thumb drive • Repeat as fast as possible (approx 100ms) • Control: Run test while stationary and record • Experiment: Run same test at launch 13 Student Launch Initiative AIAA OC Section Payload/Vehicle Integration • Vehicle has a single avionics bay • Everything is located in a single 4” diameter x12” long coupler • Two electronics sleds are separated by two square, milled pieces of aluminum • One sled holds all recovery electronics together with batteries for recovery and scientific payload • Second sled holds the scientific payload • Payload and recovery electronics and power are completely separate 14 Student Launch Initiative AIAA OC Section Risks 5 The Rocket weather cocks 10 The rocket landing in mud 4 The engine “chuffs” 9 The rocket landing 14 The batteries ‘die’ 19 The Main ‘chute in a dangerous area during launch misfires 8 The Linux 3 rocket struggles off Computer isn’t the launch pad working 15 The Drogue ‘chute misfires 20 Tracking device isn’t accurate 25 The altimeter isn’t set to fire the main 30 The battery(s) of ‘chute at the correct our electronics bay height fall out 24 The car running over the rocket 29 No recovery system 13 The Drogue ‘chute fires at the wrong altitude 18 The Main ‘chute fires at the wrong altitude 28 The altimeter isn’t 23 shear pins aren’t set to fire the main put in place ‘chute 27 The black powder blows the rocket apart 26 The electric match doesn’t ignite the black powder 2 The rocket folds upon itself 7 The Payload’s HCX isn’t accurate 12 The engine explodes 17 The altimeter isn’t set to fire the drogue 22 Tracking device ‘chute at correct is damaged in height launch 1 rocket misfires 6 Payload isn’t set up 11 The rockets fin breaking 16 The altimeter isn’t 21 Tracking device set to fire the drogue doesn’t transmit ‘chute radio waves 15 Student Launch Initiative AIAA OC Section Risks Mitigation 5 the design is not over stable 10 Make sure launch 15 double check 20 Make sure site is dry programming on the tracking device altimeter is correct works 4 make sure igniter is all the way in the engine 9 Launch site is 14 use fresh clear of all batteries hazardous materials 3 use the correct size launch rod 8 double check 13 double check 18 double check 23 double check the 28 double check programming before programming on the programming on the rocket before placing programming on the launch altimeter is correct altimeter is correct on the launch pad altimeter is correct 2 body tube and nose cone are fiberglass 7 Make sure device 12 make sure there 17 double check 22 Make sure isn’t damaged is no defects in programming on the Tracking device is engine altimeter is correct secure 1 check continuity 6 double check the payload is set up 11 Use in wall fins 25 double check 30 Tape batteries programming on the and double check altimeter is correct connection 19 double check 24 hope for the best 29 Double-check programming on the our rocket is set up altimeter is correct correctly 27 make sure black powder amount is correct 16 double check 21 double check 26 make sure there programming on the tracking device is on electric match is altimeter is correct touching the black powder 16 Student Launch Initiative AIAA OC Section Safety • Follow NAR and TRA safety rules for launch • Safe material usage restrictions • Safe distance from launch pad • Safe recovery area • Inspection by range safety officer before flight • Follow our check list when preparing for launch • Have fire extinguisher and first aid kit on site • Follow our own (AIAA OC Section Rocketry) safety rules for shop as well as launch (attached to the proposal and the PDR • MSDS referred to as needed and can be found on our web site • Manuals are posted on the web site since they contain set-up information for recovery electronics • Presentation given to all team members with their signature that they attended and understand 17 Student Launch Initiative AIAA OC Section Testing • Learn how to configure the flight computers and test on the “bench” • Set up the flight computers and test with Light Emitting Diodes (LEDs)instead of electric matches • Test the ejection charges • Set up 4” diameter body tubes with volume same as the design and set off the ejection charges - parachutes should eject without damage to the rocket body • Repeat test using the flight computers in simulated flight • Test the battery life Run recovery and payload electronics and validate the batteries will last a minimum of three hours • • Test the GPS • Verify we can receive and decode the signal from the GPS transmitter at distance, and at ground level and 6 feet above ground level • Test functionality of electronic payload • Set up the payload and validate it will run on the “bench” – with vibration from tapping (completed) • Swing the entire payload overhead in a centrifuge-like manner to simkulate “G”s the avionics section would experience during launch – validate data is collected similar to the calculated forces • Test the rocket itself • Build a scale model and fly to test the overall design • Build a full scale model and fly to test the overall design 18 Student Launch Initiative AIAA OC Section Educational Outreach • Girl scout workshop and launch outing in October/November 2010 • Giving presentation to AIAA professional society council meeting with all AIAA members in Orange County invited in January 2011 • • • Newspaper articles • Article in Sunny Hills High School (Fullerton, CA) school paper • Feature article being researched/written for Orange County Register • Local paper in Orange, CA – The Foothills Sentry – will carry article Presentations at Orange County 4H clubs Contacted Discovery Science Center for youth booth – they are featuring space exploration 19 Student Launch Initiative AIAA OC Section Website http://aiaaocrocketry.org/ Contains links to all manuals, MSDS, and design reviews Includes a calendar for important upcoming evens as well as previous meeting dates Includes photos taken during • SLI Team meetings • Girl Scout Events • ROCtober Fest Used as a tool for kids to get information about our SLI team 20 Student Launch Initiative AIAA OC Section Budget - Expenditures Budget summary – full details in PDR Description Unit Costs Totals Scale Vehicle and engines 2.6" Black Brant, engines, parachutes etc. 250 Contingent second rocket just in case first is destroyed 250 $500.00 Vehicle 4" Black Brant, parachutes, adhesive etc. 522 Contingent second rocket just in case first is destroyed 522 $1,044.00 Recovery Flight Computers, wiring, batteries, parachutes etc. 698 Contingent second recovery just in case first is destroyed 698 $1,396.00 Payload Computer, hard drive, accelerometer, batteries etc. 425 GPS System Beeline GPS (70cm), TNC, Garmin, Wiring etc 545 Contingent GPS Rocket Transmitter (Beeline) 300 $845.00 Motors (full sized vehicle) $562.00 5 Grain 54 mm Cesaroni casing, delay drill, 3 motors Educational Outreach Travel, printing, rocket kits etc. 275 $275.00 Travel (16 team members 4 days) Airline, food, hotel, car rental Total Estimated Project Expenses $15,920.00 $20,542.00 21 Student Launch Initiative AIAA OC Section Budget - Income • NASA Grant for SLI teams • Fundraising letters to Southern California Aerospace • Boeing • Raytheon • Northrop Grumman • Lockheed Martin • AIAA Orange County Section • Garage sales • Car Wash 22 Student Launch Initiative AIAA OC Section Timeline 23 Student Launch Initiative AIAA OC Section Milestone Summary October 12, 2010: Proposal November 6, 2010: Girl Scout Launch November 19, 2010: PDR submitted December 18, 2010: Start building Scale Model January 8, 2011: Launch Scale Model January 11, 2011: Presentation to AIAA OC Section January 19-31, 2011: Finalize Full Scale Design January 24, 2011: CDR due February 9-28, 2011: Build Full Scale Rocket March 12, 2011: Launch Full Scale Rocket March 21, 2011: FRR Due March 28-31, 2011: Web-Ex FRR Presentations April 13: Travel to Huntsville April 15: Launch Day 24 Student Launch Initiative AIAA OC Section Challenges • Inconsistency of data • Impulse values are different between Rocksim, Thrustcurve.org and Cesaroni for the same engine • Calculations (formula) vary between tools • On-line calculators give different values than Rocksim • Different versions of Rocksim give different values • Different wind speeds at different levels 25 Student Launch Initiative AIAA OC Section THANK YOU for letting us be a part of SLI 26 Student Launch Initiative AIAA OC Section QUESTIONS & COMMENTS 27