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1 FRR Presentation 1
2 Presentation Outline # Title Team Introduction Mission Summary Vehicle Overview Vehicle Dimensions Upper Body Section Elliptical Nose Cone Ballast System Payload Housing Structure Booster Section Fins Motor Description Static Stability Margin Mass Statement Recovery System Overview Recovery System Components Recovery Electronics Descent Rates Kinetic Energy Summary Predicted Altitude Landing Radius Testing Overview Test Plans and Procedures Structure Tests Full-Scale Flight Tests March 14, 2013 March 15, 2013 Recovery Tests Structure Requirements Verification SMD Payload Design ADGS ADGS Ground Station ARTCOS Electrical Block Diagram UV Sensor Accuracy Full-Scale Flight Data Full Scale Launch ARTCOS Pictures Payload Integration Interfaces Payload Requirements Verification Public Outreach Progress Educational Outreach Science Olympiad Questions 2
3 Team Introduction Team Manager Dustin Neighbors Lead Enigineer Jake Educational Outreach Janci Structure Todd Electronics Hardware Billy Electronics Software John Historian Jade Taylor Bert Bert Recovery Amber Billy Safety Blake 3
4 Mission Summary Science Mission Directorate Payload Vehicle Recovery 4
5 Vehicle Overview 5
6 Vehicle Dimensions Total Length: 97.5 in Upper Airframe Section: 36.5 in Acrylic Payload Section: 27 in Booster Section: 33 in Outer Diameter: in 6
7 Upper Body Section Dimensions: 36.5 in long in thick (airframe and nosecone) 7
8 Elliptical Nose Cone Dimensions 8.5 in long 4.6 in shoulder Material Fiberglass 8
9 Ballast System Washers Bulkheads Apogee Control 9
10 Payload Housing Structure Dimensions 27 inches long inches thick Material Clear Acrylic 10
11 Booster Section Dimensions 33 in long in wall thickness Materials Fiberglass 11
12 Fins Dimension Root Chord 12 in Tip Chord 2.4 inches Height 4 inches Sweep Length 7.85 inches Sweep Angle 63 Degrees 12
13 Motor Description Cesaroni L1720-WT-P 2.95 in diameter 2.15 second burn time 10.9:1 thrust-to-weight ratio Rail Exit Velocity 81.5 ft/s Total impulse of 831 lb f s ( N s) 656 ft/s max velocity 13
14 Static Stability Margin Center of Gravity inches from the tip of the nose Center of Pressure inches from the tip of the nose Stability margin 9.20 inches or 1.67 calibers of body width 14
15 Mass Statement Mass Summary Section Mass (oz) Mass (lb) Upper Body Payload Housing Booster Total Mass (Launch) Total Mass (Apogee)
16 Recovery System Overview 16
17 Recovery System Components Material 1.9 oz. silicone-coated, reinforced cross-form, rip stop nylon Main Parachute 10 ft diameter Four 10 ft long in wide tubular woven nylon shroud lines 40 ft long in wide tubular Kevlar shock cord Kevlar TAC-9B Bag deployment bag Drogue Parachute 2 ft diameter Four 2 ft long 0.25 in wide tubular woven nylon shroud lines 20 ft long in wide tubular Kevlar shock cord Nomex blanket for protection 17
18 Recovery Electronics Altimeter System Aluminum flashing Featherweight magnetic arming switch Primary & Secondary PerfectFlite Stratologger SL100 Power One 9-volt battery GPS System Transmitter Garmin Astro DC40 Handheld Receiver Garmin Astro
19 Descent Rates Parachute Descent Rate Parachute Size Main 9.95 ft/s 10 ft Diameter Drogue ft/s 2 ft Diameter 19
20 Kinetic Energy Summary Phase Nose Cone and Upper Body Airframe Payload Booster Apogee to Main Deployment (maximum) Main Deployment to Landing (maximum) ft lbf ft lbf ft lbf 14.7 ft lbf ft lbf ft lbf 20
21 Predicted Altitude Wind (mph) Ballast Needed (oz) Simulated Apogee Altitude (ft)
22 Landing Radius Wind (mph) Drift (ft)
23 Testing Overview 23
24 Test Plans and Procedures Static Performance Testing Subscale Flights Full-Scale Flights Pre-Launch Checklists Post-Flight Checklists Timed Assemblies Failure Analysis 24
25 Structure Tests Component Test Date Description Procedure Success Epoxy Hydraulic Press 12/28/2012 Bulkhead epoxied into airframe then pressed Hydraulic press applied force against epoxied attachment Yes; epoxy maxed out the scale at 1500 lbs Fiberglass Bulkhead Strength Hydraulic Press 12/28/2012 Bulkhead was placed under incrementing force Hydraulic press pressed on a block measuring 2-in x 3- in Yes; bulkhead maxed out the scale at 1500 lbs or 250 psi Airframe Testing (Fiberglass and Acrylic) Hydraulic Press 1/4/2013 Airframes were subjected to axial force Hydraulic press pressed on the center of a steel sheet across the circumference of the acrylic and fiberglass airframes Yes; both withstood 1500 pound shock force, and one minute of constant 1500 pound force Fin Test Hydraulic Press 1/5/2013 Eye Bolt Test Test Launch 1/7/2013 Torque applied to fins until compromised Drogue parachute attached to eye bolt in place of u-bolt Fin mount was placed under the hydraulic press and force applied to create torque Prototype vehicle was launched using a custom L667 Yes; fins withstood a maximum of 550 inlbf of torque Yes; eye bolt survived the flight 25
26 Vehicle Requirements Verification SOW Vehicle Requirement Satisfying Design Feature Verification Method 1.1 Payload to One Mile Cessaroni L1720-WT Testing, Analysis 1.2 Official Scoring Altimeter Adept A1E, included in the SMD payload Inspection 1.3 Remain Subsonic Cesaroni L1720-WT Testing, Analysis 1.4 Recoverable and Reusable Successful recovery system 1.5 Maximum of Four Independent Sections 1.6 Prepared at Launch Site within 2 Hours 1.7 Remain Launch-Ready for a Minimum of One Hour feet long 1 inch rail (1010) or 1.5 inch (1515) Vehicle is composed of 3 tethered sections Launch operations and assembly procedures System runtime capability of at least 2 hours 1010 and 1515 rail buttons attached to vehicle body Testing, Inspection, Analysis Inspection Testing, Inspection Testing, Inspection, Analysis Inspection 1.9 Launched by a Standard 12 volt DC Firing System Cesaroni L1720-WT Igniter Testing 1.10 No External Circuitry or Special Equipment to Initiate Launch Motor ignition only requires the 12V DC firing system Inspection 1.11 Use a Commercially Available, Certified APCP Motor Cesaroni L1720-WT Inspection 1.12 Total Impulse will not Exceed 5,120 Newton-seconds Motor total impulse of N-s Inspection 1.15 The full scale vehicle, in final flight configuration, must be successfully launched and recovered prior to FRR Full Scale Test Launch Testing 26
27 Full-Scale Flight Tests 27
28 March 14, 2013 Location Hunewell Ranch, 32.2N, -98.2E, 1309MSL Launch Rod 1010 Wind Speed 15 mph Wind SSW Direction Temperature 75 F Pressure inhg Component Apogee Time to Apogee Time of Flight Drogue Raven 3 Corrupted Data Corrupted Data Corrupted Data Drogue Stratologger 4947ft AGL s s Main Raven 3 Corrupted Data Corrupted Data Corrupted Data Main Stratologger 4935ft AGL s Corrupted Data GPS 4977ft AGL s s 28
29 March 15, 2013 Location Launch Rod Wind Speed Wind Direction Temperature Pressure Hunewell Ranch, 32.2N, E, 1309MSL 10 foot, button 19 mph SSW 80 F 33.2 inhg Component Apogee Time to Apogee Time of Flight Drogue Raven ft AGL 18.96s 72.68s Drogue Stratologger 5282ft AGL 19.60s 73.10s Main Raven ft AGL 18.72s 72.68s Main Stratologger 5269ft AGL 19.65s 74.90s GPS Corrupted Data Corrupted Data Corrupted Data 29
30 Recovery Tests Date Overview Predicted Apogee 26 January February February March March 2013 Hunewell, L585, Prototype 1 Hunewell, L585, Prototype 1 Hunewell, L585, Prototype 1 Hunewell, K510, Prototype 1 Hunewell, K555, Prototype 1 Apogee (Average) Landing Radius 3525ft AGL 3495ft AGL 180ft Yes 3324ft AGL 2957ft AGL 2067ft No 2611ft AGL 2300ft AGL 240ft Yes 2429ft AGL 1856ft AGL 363ft Yes 2358ft AGL 1888ft AGL 1860ft No Success 30
31 SMD Payload 31
32 Design 32
33 ADGS 33
34 ADGS Ground Station 34
35 ARTCOS 35
36 Electrical Block Diagram 36
37 UV Sensor Accuracy 37
38 Full Scale Flight Data Pressure (inhg) dtime (s) Temperature ( o F) dtime (s) Solar Irradiance (W/m 2 ) dtime (s) GPS 38
39 Full Scale Launch ARTCOS Pictures 39
40 Payload Integration 40
41 Interfaces Airframe Couplers Rail Buttons Magnetic Switches Electrical Ignition System Telemetry 41
42 Payload Requirement Verification SOW # Requirement Satisfying Design Feature Verification Method UV Radiation Solar Irradiance Humidity Temperature Pressure SU-100 TSL2561, SP-110 HIH4030 BMP180 BMP180 Lab Testing, Static and Flight Testing, Analysis, Demonstration Data Collection Frequency 16MHz Arduino Mega 2560, Software Lab Testing, Flight Testing, Analysis Post-Landing Data Termination Software 2 Descent Pictures VC0706, Keyfob Video Camera 3 Landing Pictures VC0706, Keyfob Video Camera Lab Testing, Analysis Static and Flight Testing Horizon Orientation ARTCOS Lab Testing, Analysis Onboard Data Storage Micro SD Lab Testing, Static and Flight Testing, Analysis Data Transmission 900MHz XBee Radios Range Testing, Flight Testing GPS LS20031 Lab Testing, Static and Flight Testing, Analysis 42
43 Public Outreach Progress
44 44
45 Science Olympiad 45
46 Questions 46
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