university of florida cdr presentation
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University of Florida CDR Presentation. Outline. Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work. Vehicle Design. Nose cone and 4 main sections Avionics Bay is fixed inside upper airframe and Mid Airframe - PowerPoint PPT PresentationTRANSCRIPT
Slide 1Outline
Avionics Bay is fixed inside upper airframe and Mid Airframe
Body diameter is 5.455”
Static Stability Diagram
The center of pressure (CP) is located 86 from the tip of the rocket nose.
The center of gravity (CG) is located 78 from the tip of the rocket nose.
The maximum diameter of the rocket is 5.455. These dimensions result in a static margin of 1.45, which is within the range desired (between 1 and 2).
CG
CP
Tube Construction
All three airframes (upper, mid, and lower) will be made of phenolic tube wrapped in a composite mixture of two layers of 4 ounce fiberglass and Aeropoxy. The first body tube has already been made, as shown below
Upper Airframe
45” long, 7.79 lbs. (w/ contents)
From bottom: contains top of avionics bay, payload, payload drogue, rocket drogue, nose cone insert
Avionics Bay
Phenolic tube with 0.5” birch ply bulkheads
Serves as coupler for Main Airframe – Upper Airframe joint, therefore it does not add length to the rocket
Screws into both of these airframes to prevent separation
Avionics Bay
All-thread provides structural support
Easy-to-use thumb nuts to wire igniter outputs and hook up ejection charges
1/8” G-10 fiberglass serves as platform for electronics mounting
Contains two redundant PerfectFlite Altimeters (each powered by their own 9-volt battery), a GPS, and a transceiver (powered by a 9-Volt battery)
Mid Airframe
30” long, 3.47 lbs
From bottom: contains rocket main parachute and bottom of avionics bay
Lower Airframe
30” Long, 9.07 lbs, 3 Fins
From Bottom: Contains 54mm motor mount, three centering rings, and motor retention
Motor Retention
Aluminum sleeve with indention and snap ring groove
Motor thrust ring pushes on aluminum indention instead of phenolic tube
Motor Choice
The motor has been changed to the Loki L1400 because of the unavailability of the AMW L1300
Characteristics of the L1400
Total Impulse: 2850.6 Ns (175.6 Ns greater than L1300)
Peak Thrust: Officially 2710.5 N, but RockSim reports 1906.4 N, large discrepancy
Burn Time: 2.0 s (same as L1300)
Performance w/ Rocket
Thrust-to-Weight Ratio: 11.1
L1400 Thrust Curve
Folds up while inside upper airframe
A torsional and tensional spring in each leg creates a sprawling motion once payload is deployed
Wheels allow easy vertical sliding of payload
Rests in “shoes” during flight, which are fixed to inside of Upper Airframe
Tube is made out 1/8” T6-6061 Aluminum, with an outside diameter of 3.25”
Legs are made out of 1/16” Aluminum U-Channel
*Note* - video cameras, parachute compartment, and payload lid not shown in this drawing
Payload Electronics
Contains two redundant R-DAS Tiny altimeters that control the payload’s main parachute deployment and record all sensor data. Each R-DAS Tiny has its own 11.1V flight battery
Contains two analog temperature and two analog humidity sensors
Contains a GPS and transceiver powered by the batteries on their respective boards
Similar structural design as the Avionics Bay
Two video cameras attached to the outside of the payload bay
Payload Lid
Payload Wiring Schematic
Descent Rate: Undetermined
Redundant PerfectFlite altimeters will control the rocket’s dual deployment
Redundant R-DAS Tiny altimeters will control the payload’s dual deployment
The payload will use streamers as a drogue to prevent shading of the solar and UV sensors
5/8” tubular nylon will connect all sections of both rocket and the payload to their respective parachutes
Outline
Test section: 12”x12” cross-section, 24” long
Experiment 1 - Fins With Varied Paint Combinations
Fin 1 – Control Fin
Experiment 2 – Fins With Varied Shape Combinations
Fin 1 – Control Fin
Fin 5 – Rounded LE
Fin 6 – Tapered TE
Wind Tunnel Results
8.48%
0.3171
Greatest Reduction in drag from the rounded LE, tapered TE fin
The tapered TE fin showed no drag reduction at all.
The fins that were painted but not glossed showed higher drag reduction that the glossed fin
Drag Coefficient calculation assumptions:
There is a linear relationship between compressor speed and airspeed
The structure holding the fins produced negligible drag in addition to the fin.
For higher accuracy, the drag from the test structure needs to be accounted for and the speed airspeed needs to be calibrated properly
Recovery System Testing
Hooked up Christmas lights as imitation igniters
Placed altimeter inside avionics bay
Extracted air from the tube and both Christmas bulbs lit up after air was passed back into the tube and air pressure was restored
The data was checked to ensure that the igniters were fired at the correct altitude
Subscale ejection charge testing
The first charge needed to eject the payload at least 15 feet from the rocket without causing overwhelming stress on any components
The second charge needed to eject the lower airframe at least 15 feet from the rocket without causing overwhelming stress on any components
Three grams of black powder met the criteria of both charges, and worked successfully in the subscale test flight
Payload Testing
Temperature and humidity sensor testing complete by seeing change in voltage in varying temperature and humidity climates
GPS and XBEE are now functioning correctly with the software on the ground after much trial and error
Vibrations Testing
Are modal frequencies within gust spectrum?
What mode shapes result from stiffness/mass distribution?
Ground vibration test (GVT)
Soft support was bungee
2 lb force actuator
Vibrations Testing
Experimental setup
Found variety of mode shapes
Similar to 2 beams cantilevered around high stiffness near avionics bay
Mode shapes indicated tip deflections were not large even with pounds of force
No additional stiffness seems required for flight safety during short portions of flight with high dynamic pressure
Outline
18 mph winds, 10° launch angle
88.5” length, 3” diameter, 8.75 pounds
The Gorilla I235 motor was used, and the same motor retention concept for the full scale was used
Successful dual deployment and payload separation, rocket’s main parachute deployed at 300 feet to avoid excessive drift
Payload contained only a main parachute that was deployed at apogee, which resulted in excessive drift of the payload
The payload spun at a relatively fast rate while descending, which could be an issue for our full scale payload which will need to take quality video and land without turning over; a swivel bolt has been considered to mitigate this problem
Subscale Static Test
Created our own static test stand
Tested the I235 to input into our MATLAB program to simulate subscale flight
We also plan to test our full scale motor
33
Time (s)
Thrust (pounds)
Maximum altitude from the PerfectFlite was 890 feet
The main parachute was deployed at 300, as can be seen from the graph below
The main chute descent rate calculated from this data was about 20 ft/s, which is in the desired range
Subscale Flight 1 - Altitude vs. Time
0.05 0.1 0.15000000000000016 0.2 0.25 0.30000000000000027 0.35000000000000026 0.40000000000000008 0.45 0.5 0.54999999999999993 0.60000000000000053 0.6500000000000008 0.70000000000000062 0.75000000000000078 0.8000000000000006 0.85000000000000064 0.90000000000000024 0.95000000000000062 1.0000000000000002 1.0500000000000003 1.1000000000000003 1.1500000000000015 1.2000000000000004 1.2500000000000004 1.3000000000000005 1.3500000000000005 1.4000000000000006 1.4500000000000006 1.5000000000000007 1.5500000000000007 1.6000000000000019 1.6500000000000019 1.7000000000000008 1.7500000000000009 1.8000000000000009 1.8500000000000021 1.9000000000000021 1.95 00000000000022 2.0000000000000009 2.0500000000000007 2.1000000000000005 2.1500000000000004 2.2000000000000002 2.25 2.2999999999999998 2.3499999999999988 2.3999999999999977 2.4499999999999993 2.4999999999999987 2.549999999999998 9 2.5999999999999988 2.6499999999999986 2.6999999999999984 2.7499999999999982 2.799999999999998 2.8499999999999979 2.8999999999999977 2.9499999999999975 2.9999999999999973 3.0499999999999972 3.099999999999997 3.1499999999999972 3.1999999999999966 3.2499999999999982 3.2999999999999972 3.3499999999999961 3.3999999999999937 3.4499999999999957 3.4999999999999947 3.5499999999999954 3.5999999999999948 3.649999999999995 3.6999999999999948 3.7499999999999951 3.7999999999999945 3.8499999999999943 3.8999999999999937 3.949999999999994 3.9999999999999938 4.0499999999999936 4.0999999999999925 4.1499999999999915 4.1999999999999895 4.2499999999999929 4.2999999999999927 4.3499999999999925 4.3999999999999915 4.4499999999999922 4.499999999999992 4.5499999999999918 4.5999999999999917 4.6499999999999915 4.6999999999999895 4.7499999999999911 4.7999999999999909 4.8499999999999908 4.8999999999999906 4.9499999999999904 4.9999999999999902 5.0499999999999901 5.0999999999999899 5.1499999999999897 5.1999999999999895 5.2499999999999893 5.2999999999999892 5.349999999999989 5.3999999999999888 5.4499999999999904 5.4999999999999893 5.5499999999999883 5.5999999999999881 5. 6499999999999879 5.6999999999999877 5.7499999999999893 5.7999999999999874 5.8499999999999872 5.899999999999987 5.9499999999999904 5.9999999999999893 6.0499999999999874 6.0999999999999863 6.1499999999999861 6.199999999999986 6.2499999999999893 6.2999999999999874 6.3499999999999854 6.3999999999999853 6.4499999999999895 6.4999999999999893 6.5499999999999874 6.5999999999999854 6.6499999999999844 6.6999999999999842 6.7499999999999885 6.7999999999999838 6.8499999999999837 6.8999999999999835 6.9499999999999833 6.9999999999999831 7.0499999999999829 7.0999999999999828 7.1499999999999826 7.1999999999999815 7.2499999999999822 7.2999999999999821 7.3499999999999819 7.3999999999999817 7.4499999999999824 7.4999999999999813 7.5499999999999812 7.599999999999981 7.6499999999999808 7.6999999999999806 7.7499999999999813 7.7999999999999803 7.8499999999999801 7.8999999999999799 7.9499999999999824 7.9999999999999813 8.0499999999999794 8.0999999999999908 8.1499999999999808 8.1999999999999904 8.2499999999999822 8.2999999999999847 8.3499999999999925 8.3999999999999986 8.449999999999994 8.4999999999999964 8.5499999999999865 8.5999999999999961 8.6499999999999897 8.6999999999999975 8.7499999999999893 8.7999999999999989 8.8500000000000014 8.9000000000000021 8.9500000000000011 9.0000000000000018 9.0500000000000025 9.1000000000000014 9.1499999999999968 9.2000000000000011 9.2499999999999964 9.3000000000000025 9.3500000000000068 9.4000000000000021 9.4500000000000028 9.5 9.5500000000000007 9.6000000000000014 9.6500000000000021 9.7000000000000011 9.7500000000000036 9.8000000000000043 9.8500000000000068 9.9000000000000057 9.9500000000000064 10.000000000000007 10.050000000000017 10.100000000000009 10.150000000000009 10.20000000000001 10.250000000000012 10.30000000000002 10.350000000000021 10.400000000000016 10.450000000000022 10.500000000000014 10.55000000000002 10.600000000000016 10.650000000000016 10.700000000000017 10.75000000000002 10.80000000000002 10.850000000000026 10.90000000000002 10.950000000000022 11.000000000000021 11.050000000000022 11.100000000000023 11.150000000000023 11.200000000000021 11.250000000000025 11.300000000000026 11.350000000000026 11.400000000000027 11.450000000000029 11.500000000000028 11.550000000000029 11.60000000000003 11.650000000000032 11.700000000000031 11.750000000000032 11 .800000000000034 11.850000000000044 11.900000000000034 11.950000000000044 12.000000000000036 12.050000000000036 12.100000000000037 12.150000000000039 12.200000000000038 12.250000000000039 12.300000000000049 12.350000000000053 12.40000000000005 12.450000000000051 12.500000000000044 12.55000000000005 12.600000000000044 12.65000000000005 12.700000000000045 12.750000000000046 12.80000000000005 12.850000000000056 12.90000000000005 12.950000000000054 13.00000000000005 13.05000000000005 13.100000000000051 13.150000000000052 13.200000000000053 13.250000000000053 13.300000000000054 13.350000000000056 13.400000000000055 13.450000000000056 13.500000000000057 13.550000000000059 13.600000000000058 13.650000000000059 13.70000000000006 13.75000000000006 13.800000000000066 13.850000000000071 13.900000000000064 13.95000000000007 14.000000000000064 14.050000000000066 14.100000000000065 14.150000000000066 14.200000000000067 14.250000000000069 14.30000000000007 14.350000000000072 14.40000000000007 14.45000000000007 14.500000000000071 14.550000000000072 14.600000000000071 14.650000000000073 14.700000000000069 14.750000000000075 14.800000000000075 14.850000000000076 14.900000000000077 14.950000000000077 15.000000000000078 15.050000000000079 15.10000000000008 15.15000000000008 15.200000000000081 15.250000000000082 15.300000000000082 15.350000000000092 15.400000000000084 15.450000000000086 15.500000000000085 15.550000000000086 15.600000000000087 15.650000000000087 15.700000000000088 15.750000000000089 15.800000000000098 15.850000000000099 15.900000000000096 15.950000000000101 16.000000000000092 16.050000000000093 16.100000000000094 16.150000000000095 16.200000000000092 16.250000000000096 16.300000000000097 16.350000000000097 16.400000000000087 16.450000000000099 16.500000000000099 16.5500000000001 16.600000000000101 16.650000000000105 16.700000000000102 16.750000000000103 16.800000000000104 16.850000000000104 16.90000000000 0102 16.950000000000106 17.000000000000107 17.050000000000107 17.100000000000108 17.150000000000126 17.200000000000109 17.25000000000011 17.300000000000111 17.350000000000115 17.400000000000112 17.450000000000113 17.500000000000114 17.550000000000114 17.600000000000115 17.65000000000013 17.700000000000117 17.750000000000117 17.800000000000118 17.8500000000001 33 17.900000000000119 17.95000000000012 18.000000000000121 18.050000000000125 18.100000000000133 18.15000000000013 18.200000000000124 18.250000000000124 18.300000000000125 18.350000000000133 18.400000000000126 18.450000000000127 18.500000000000128 18.550000000000132 18.600000000000133 18.65000000000013 18.700000000000127 18.750000000000128 18.800000000000132 18.850000000000133 18.900000000000126 18.950000000000127 19.000000000000128 19.050000000000136 19.100000000000136 19.150000000000137 19.200000000000127 19.250000000000139 19.300000000000139 19.35000000000014 19.400000000000126 19.450000000000127 19.500000000000142 19.550000000000143 19.600000000000144 19.650000000000144 19.700000000000127 19.750000000000146 19.800000000000146 19.850000000000147 19.90000000000013 19.950000000000149 20.000000000000149 20.05000000000015 20.100000000000151 20.150000000000151 20.200000000000152 20.250000000000153 20.300000000000153 20.350000000000154 20.400000000000137 20.450000000000156 20.500000000000156 20.550000000000157 20.600000000000158 20.650000000000158 20.700000000000159 20.75000000000016 20.800000000000161 20.85000000000016 1 20.900000000000162 20.950000000000163 21.000000000000163 21.050000000000164 21.100000000000165 21.150000000000183 21.200000000000166 21.250000000000167 21.300000000000168 21.350000000000168 21.400000000000169 21.45000000000017 21.500000000000171 21.550000000000171 21.60000000000019 21.65000000000019 21.700000000000173 21.750000000000174 21.800000000000175 21.85000000000019 21.900000000000176 21.950000000000177 22.000000000000178 22.050000000000178 22.10000000000019 22.15000000000019 22.20000000000018 22.250000000000181 22.300000000000185 22.35000000000019 22.400000000000183 22.450000000000184 22.500000000000185 22.550000000000185 22.60000000000019 22.65000000000019 22.700000000000188 22.750000000000188 22.800000000000193 22.85000000000019 22.900000000000187 22.950000000000188 23.000000000000192 23.050000000000193 23.100000000000193 23.150000000000194 23.200000000000188 23.250000000000192 23.300000000000196 23.350000000000197 23.400000000000187 23.450000000000188 23.500000000000199 23.5500000000002 23.6000000000002 23.650000000000201 23.700000000000202 23.750000000000203 23.800000000000203 23.850000000000204 23.900000000000187 23.950000000000202 24.000000000000206 24.050000000000207 24.100000000000207 24.150000000000208 24.200000000000209 24.25000000000021 24.30000000000021 24.350000000000211 24.400000000000212 24.450000000000212 24.500000000000213 24.550000000000214 24.600000000000215 24.650000000000215 24.700000000000216 24.750000000000217 24.800000000000217 24.850000000000218 24.900000000000219 24.95000000000022 25.00000000000022 25.050000000000221 25.100000000000225 25.15000000000023 25.200000000000223 25.250000000000224 25.300000000000225 25.350000000000225 25.400000000000226 25.450000000000227 25.500000000000227 25.550000000000228 25.600000000000232 25.65000000000023 25.700000000000227 25.750000000000227 25.800000000000232 25.850000000000232 25.900000000000226 25.950000000000227 26.000000000000227 26.050000000000232 26.100000000000236 26.150000000000237 26.200000000000227 26.250000000000227 26.300000000000239 26.350000000000239 26.400000000000226 26.450000000000227 26.500000000000242 26.550000000000242 26.600000000000243 26.650000000000244 26.700000000000227 26.750000000000242 26.800000000000246 26.850000000000247 26.90000000000023 26.95000000000023 27.000000000000249 27.050000000000249 27.10000000000025 27.150000000000251 27.200000000000252 27.250000000000252 27.300000000000253 27.350000000000254 27.400000000000237 27.450000000000252 27.500000000000256 27.550000000000257 27.600000000000257 27.650000000000258 27.700000000000259 27.750000000000259 27.80000000000026 27.850000000000261 27.900000000000244 27.950000000000262 28.000000000000263 28.050000000000264 28.100000000000264 28.150000000000265 28.200000000000266 28.250000000000266 28.300000000000267 28.350000000000268 28.400000000000269 28.450000000000269 28.50000000000027 28.550000000000271 28.600000000000271 28.65000000000029 28.700000000000273 28.750000000000274 28.800000000000274 28.850000000000275 28.900000000000276 28.950000000000276 29.00000000000 0277 29.050000000000278 29.100000000000293 29.15000000000029 29.20000000000028 29.250000000000281 29.300000000000281 29.350000000000293 29.400000000000283 29.450000000000284 29.500000000000284 29.550000000000285 29.600000000000293 29.65000000000029 29.700000000000287 29.750000000000288 29.800000000000288 29.850000000000293 29.900000000000286 29.950000000000287 30.000000000000288 30.050000000000292 30.1000000000002 93 30.150000000000293 30.200000000000287 30.250000000000288 30.300000000000296 30.350000000000296 30.400000000000286 30.450000000000287 30.500000000000288 30.550000000000299 30.6000000000003 30.650000000000301 30.700000000000287 30.750000000000302 30.800000000000303 19 29 38 38 48 57 57 76 76 95 95 115 115 134 153 163 172 182 191 210 210 230 230 249 249 268 287 287 307 307 307 326 326 345 365 365 365 384 394 403 403 423 423 433 442 461 461 461 481 481 500 500 500 519 519 539 539 539 558 558 578 578 578 597 597 597 617 617 617 636 636 636 655 655 655 675 675 675 694 694 694 694 714 714 714 724 733 733 733 743 753 753 753 763 772 772 772 772 782 792 792 792 792 812 812 812 812 812 822 831 831 831 831 831 841 841 851 851 851 851 851 851 861 861 870 870 870 870 870 870 870 880 880 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 831 694 900 890 890 890 890 890 890 890 900 900 890 890 890 890 890 890 910 910 920 890 890 890 890 890 890 890 890 890 870 870 861 851 851 851 851 851 851 890 890 851 851 831 831 851 851 851 831 812 822 831 841 831 812 812 802 812 812 812 792 792 772 772 772 772 772 772 772 753 753 753 753 763 753 753 753 753 753 733 724 714 714 714 714 704 694 694 694 694 694 694 685 675 675 675 655 655 646 636 646 636 636 617 617 617 617 617 597 578 578 578 568 558 558 558 539 539 539 529 519 519 519 500 481 500 481 481 481 481 461 461 461 452 442 442 442 423 423 423 423 423 423 423 423 403 403 384 375 365 365 365 345 345 345 345 345 423 413 326 307 307 307 307 297 307 307 297 307 297 287 287 287 287 287 287 287 287 287 287 278 268 268 268 268 268 268 268 268 268 268 268 268 268 268 268 268 249 249 249 249 249 249 249 249 249 249 249 249 240 249 240 230 230 230 230 230 230 230 230 230 230 230 230 230 230 220 220 210 210 210 210 210 210 210 210 210 210 210 210 210 210 210 201 210 201 210 210 210 210 201 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 182 191 182 182 182 172 172 172 172 172 172 172 172 172 172 172 172 172 172 172 172 172 163 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 144 144 134 134 134 134 134 134 134 134 134 134 134 134 134 134 125 125 125 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 105 115 115 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 86 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 67 76 76 57 67 57 57 57 57 57 57 57 57 57 57 57 57 48 48 48 38 38 38 38 38 38 38 38 38 38 38 38 38 38 38 38 29 29 29 19 19 19 19 19 19 19 19 19 19 19 19 19 19 10 19 0 10 0 0
Time (seconds)
Future Work
Flight Simulations
MATLAB 2DOF
MATLAB has been updated to include downrange motion of the rocket
Downrange motion is only affected by launch angle; no angle of attack
Better reflection of physical system
Still lacks:
Drag Coefficient
Lack of knowledge of the true coefficient of drag prevents accurate simulation. True for RockSim and MATLAB
In order to achieve a better estimate of the drag coefficient, the max altitude of the MATLAB 2DOF was matched to the max alt. of the subscale launch altimeter data
Full Scale Max Altitude Optimization
Ran RockSim model at various wind conditions with the L1400
Found that, to minimize downrange drift, the launch angle into the wind should increase by one degree for every mph of wind
Found the additional mass needed to reach a mile depending on the launch angle
On launch day, once launch conditions are known, the additional mass needed will be added with modeling clay in between the top two centering rings (near the center of gravity), then the top centering ring will be screwed in place
Launch Angle (°)
Mass added to achieve mile (oz)
0
0
5668
26
0
5
5663
26
0
10
5647
25
5
0
5620
23.5
5
5
5589
21.5
5
10
5545
18.5
10
0
5479
14
10
5
5424
10
10
10
5356
5
15
0
5252
15
5
5178
15
10
5091
Outline
Future Work
Educational Engagement
Presented to 150 5th graders at Hidden Oak Elementary School for one hour
PowerPoint presentation taught students about the basics of rocketry, how to get involved, and how to remain safe
Three model rockets were launched to give the students an first-hand example of rocketry
Educational Engagement
Presented to sixty 4th-8th graders at Millhopper Montessori School (private school) for one hour
Similar presentation to the one at Hidden Oak, but the subscale rocket was also shown
Like at Hidden Oak, three model rockets were launched in a nearby field for the students to see
Educational Engagement
Educational Engagement
Engineering-Fair
This department wide event occurs on February 22nd and 23rd and brings in elementary, middle, and high school students from the local area to teach them about engineering
The USLI team plans on sharing a booth at this fair with AIAA and will teach students the basics of rocketry and what to do in school to better their chances at getting into UF
Aerospace Day
UF AIAA chapter brings together middle school students from around the local area to build gliders, bottle rockets, and small model rockets
The USLI team will provide support in model rocket building and launching and will also launch some higher power rockets to influence the students to pursue engineering studies. Date is uncertain
Industry
Presented to three SpaceX employees
Used PowerPoint to describe the work done over the past two years, and what the team is working towards
Showed the subscale rocket, our static test stand, and the data from the wind tunnel experiments
Also plan to present to Northrop Grumman representatives in late February
Outline
MATLAB model will be extended to 3DOF
More altimeter data collected from second subscale launch and full scale rocket launch to adjust coefficient of drag
Continued wind tunnel testing to compare experimental CD values with RockSim CD values
Compare with RockSim for various wind speeds
RockSim and MATLAB models compare to launch data. Best-fit determined
Payload Testing
Sensor conversion constant verification
Solar cell has range of 430 to 1100 nm. Test the voltage to W/m2 conversion constant
UV sensor voltage to W/m2 conversion constant (1.962)
Sensor-to-RDAS configuration
R-DAS Tiny altitude testing
Will be tested with second subscale flight and compared with PerfectFlite altimeter
Video camera vibration testing
Full scale ejection charge ground testing
Need parts to be ejected at least 15 feet apart from each other without significantly damaging components
Payload streamer descent rate verification
Need a descent rate between 50 and 100 ft/s
Payload bay separation testing
Sliding in and out of upper airframe, legs springing out
Payload landing testing
With horizontal motion, rotation, and tilt angles
R-DAS & GPS testing in Avionics Bay and Payload Bay
Static Motor Testing
The L1400 will be tested on a different test stand provided by our mentor, Jimmy, which is capable of such large motors
This will test our ignition method
This will help verify which motor characteristics that should be trusted- the official one provided by the NAR or the one provided by RockSim
The motor will also be tested with the retention device connected, just in case it effects the exhaust flow at all
UF Rocket Team Timeline
Start Date Avionics Testing Subscale rocket construction Presentation to Middle School Presentation to El ementary School Recovery Testing Subscale Launch 1 Flight Analysis 1 Full Scale construction Payload bay construction Sensor Testing CDR due Subscale Launch 2 Flight Analysis 2 Static Motor Testing Payload bay Ejection Testing Full Scale Launch 1 Full Scale Launch 2 Flight Analysis 3 FRR due Travel to Huntsville Launch Day PLAR Due 40501 40501 40512 40514 40547 40551 40551 40552 40552 40552 40567 40586 40586 40587 40587 40614 40621 40614 40623 40646 40649 40672 Duration
Nov 19-Dec 8
Nov 19-Jan 7
Mar 21
Apr 13
Apr 16
May 9
Avionics Testing Subscale rocket construction Presentation to Middle School Presentation to Elementary School Recovery Testing Subscale Launch 1 Flight Analysis 1 Full Scale construction Payload bay construction Sensor Testing CDR due Subscale Launch 2 Flight Analysis 2 Static Motor Testing Payload bay Ejection Testing Full Scale Launch 1 Full…
Avionics Bay is fixed inside upper airframe and Mid Airframe
Body diameter is 5.455”
Static Stability Diagram
The center of pressure (CP) is located 86 from the tip of the rocket nose.
The center of gravity (CG) is located 78 from the tip of the rocket nose.
The maximum diameter of the rocket is 5.455. These dimensions result in a static margin of 1.45, which is within the range desired (between 1 and 2).
CG
CP
Tube Construction
All three airframes (upper, mid, and lower) will be made of phenolic tube wrapped in a composite mixture of two layers of 4 ounce fiberglass and Aeropoxy. The first body tube has already been made, as shown below
Upper Airframe
45” long, 7.79 lbs. (w/ contents)
From bottom: contains top of avionics bay, payload, payload drogue, rocket drogue, nose cone insert
Avionics Bay
Phenolic tube with 0.5” birch ply bulkheads
Serves as coupler for Main Airframe – Upper Airframe joint, therefore it does not add length to the rocket
Screws into both of these airframes to prevent separation
Avionics Bay
All-thread provides structural support
Easy-to-use thumb nuts to wire igniter outputs and hook up ejection charges
1/8” G-10 fiberglass serves as platform for electronics mounting
Contains two redundant PerfectFlite Altimeters (each powered by their own 9-volt battery), a GPS, and a transceiver (powered by a 9-Volt battery)
Mid Airframe
30” long, 3.47 lbs
From bottom: contains rocket main parachute and bottom of avionics bay
Lower Airframe
30” Long, 9.07 lbs, 3 Fins
From Bottom: Contains 54mm motor mount, three centering rings, and motor retention
Motor Retention
Aluminum sleeve with indention and snap ring groove
Motor thrust ring pushes on aluminum indention instead of phenolic tube
Motor Choice
The motor has been changed to the Loki L1400 because of the unavailability of the AMW L1300
Characteristics of the L1400
Total Impulse: 2850.6 Ns (175.6 Ns greater than L1300)
Peak Thrust: Officially 2710.5 N, but RockSim reports 1906.4 N, large discrepancy
Burn Time: 2.0 s (same as L1300)
Performance w/ Rocket
Thrust-to-Weight Ratio: 11.1
L1400 Thrust Curve
Folds up while inside upper airframe
A torsional and tensional spring in each leg creates a sprawling motion once payload is deployed
Wheels allow easy vertical sliding of payload
Rests in “shoes” during flight, which are fixed to inside of Upper Airframe
Tube is made out 1/8” T6-6061 Aluminum, with an outside diameter of 3.25”
Legs are made out of 1/16” Aluminum U-Channel
*Note* - video cameras, parachute compartment, and payload lid not shown in this drawing
Payload Electronics
Contains two redundant R-DAS Tiny altimeters that control the payload’s main parachute deployment and record all sensor data. Each R-DAS Tiny has its own 11.1V flight battery
Contains two analog temperature and two analog humidity sensors
Contains a GPS and transceiver powered by the batteries on their respective boards
Similar structural design as the Avionics Bay
Two video cameras attached to the outside of the payload bay
Payload Lid
Payload Wiring Schematic
Descent Rate: Undetermined
Redundant PerfectFlite altimeters will control the rocket’s dual deployment
Redundant R-DAS Tiny altimeters will control the payload’s dual deployment
The payload will use streamers as a drogue to prevent shading of the solar and UV sensors
5/8” tubular nylon will connect all sections of both rocket and the payload to their respective parachutes
Outline
Test section: 12”x12” cross-section, 24” long
Experiment 1 - Fins With Varied Paint Combinations
Fin 1 – Control Fin
Experiment 2 – Fins With Varied Shape Combinations
Fin 1 – Control Fin
Fin 5 – Rounded LE
Fin 6 – Tapered TE
Wind Tunnel Results
8.48%
0.3171
Greatest Reduction in drag from the rounded LE, tapered TE fin
The tapered TE fin showed no drag reduction at all.
The fins that were painted but not glossed showed higher drag reduction that the glossed fin
Drag Coefficient calculation assumptions:
There is a linear relationship between compressor speed and airspeed
The structure holding the fins produced negligible drag in addition to the fin.
For higher accuracy, the drag from the test structure needs to be accounted for and the speed airspeed needs to be calibrated properly
Recovery System Testing
Hooked up Christmas lights as imitation igniters
Placed altimeter inside avionics bay
Extracted air from the tube and both Christmas bulbs lit up after air was passed back into the tube and air pressure was restored
The data was checked to ensure that the igniters were fired at the correct altitude
Subscale ejection charge testing
The first charge needed to eject the payload at least 15 feet from the rocket without causing overwhelming stress on any components
The second charge needed to eject the lower airframe at least 15 feet from the rocket without causing overwhelming stress on any components
Three grams of black powder met the criteria of both charges, and worked successfully in the subscale test flight
Payload Testing
Temperature and humidity sensor testing complete by seeing change in voltage in varying temperature and humidity climates
GPS and XBEE are now functioning correctly with the software on the ground after much trial and error
Vibrations Testing
Are modal frequencies within gust spectrum?
What mode shapes result from stiffness/mass distribution?
Ground vibration test (GVT)
Soft support was bungee
2 lb force actuator
Vibrations Testing
Experimental setup
Found variety of mode shapes
Similar to 2 beams cantilevered around high stiffness near avionics bay
Mode shapes indicated tip deflections were not large even with pounds of force
No additional stiffness seems required for flight safety during short portions of flight with high dynamic pressure
Outline
18 mph winds, 10° launch angle
88.5” length, 3” diameter, 8.75 pounds
The Gorilla I235 motor was used, and the same motor retention concept for the full scale was used
Successful dual deployment and payload separation, rocket’s main parachute deployed at 300 feet to avoid excessive drift
Payload contained only a main parachute that was deployed at apogee, which resulted in excessive drift of the payload
The payload spun at a relatively fast rate while descending, which could be an issue for our full scale payload which will need to take quality video and land without turning over; a swivel bolt has been considered to mitigate this problem
Subscale Static Test
Created our own static test stand
Tested the I235 to input into our MATLAB program to simulate subscale flight
We also plan to test our full scale motor
33
Time (s)
Thrust (pounds)
Maximum altitude from the PerfectFlite was 890 feet
The main parachute was deployed at 300, as can be seen from the graph below
The main chute descent rate calculated from this data was about 20 ft/s, which is in the desired range
Subscale Flight 1 - Altitude vs. Time
0.05 0.1 0.15000000000000016 0.2 0.25 0.30000000000000027 0.35000000000000026 0.40000000000000008 0.45 0.5 0.54999999999999993 0.60000000000000053 0.6500000000000008 0.70000000000000062 0.75000000000000078 0.8000000000000006 0.85000000000000064 0.90000000000000024 0.95000000000000062 1.0000000000000002 1.0500000000000003 1.1000000000000003 1.1500000000000015 1.2000000000000004 1.2500000000000004 1.3000000000000005 1.3500000000000005 1.4000000000000006 1.4500000000000006 1.5000000000000007 1.5500000000000007 1.6000000000000019 1.6500000000000019 1.7000000000000008 1.7500000000000009 1.8000000000000009 1.8500000000000021 1.9000000000000021 1.95 00000000000022 2.0000000000000009 2.0500000000000007 2.1000000000000005 2.1500000000000004 2.2000000000000002 2.25 2.2999999999999998 2.3499999999999988 2.3999999999999977 2.4499999999999993 2.4999999999999987 2.549999999999998 9 2.5999999999999988 2.6499999999999986 2.6999999999999984 2.7499999999999982 2.799999999999998 2.8499999999999979 2.8999999999999977 2.9499999999999975 2.9999999999999973 3.0499999999999972 3.099999999999997 3.1499999999999972 3.1999999999999966 3.2499999999999982 3.2999999999999972 3.3499999999999961 3.3999999999999937 3.4499999999999957 3.4999999999999947 3.5499999999999954 3.5999999999999948 3.649999999999995 3.6999999999999948 3.7499999999999951 3.7999999999999945 3.8499999999999943 3.8999999999999937 3.949999999999994 3.9999999999999938 4.0499999999999936 4.0999999999999925 4.1499999999999915 4.1999999999999895 4.2499999999999929 4.2999999999999927 4.3499999999999925 4.3999999999999915 4.4499999999999922 4.499999999999992 4.5499999999999918 4.5999999999999917 4.6499999999999915 4.6999999999999895 4.7499999999999911 4.7999999999999909 4.8499999999999908 4.8999999999999906 4.9499999999999904 4.9999999999999902 5.0499999999999901 5.0999999999999899 5.1499999999999897 5.1999999999999895 5.2499999999999893 5.2999999999999892 5.349999999999989 5.3999999999999888 5.4499999999999904 5.4999999999999893 5.5499999999999883 5.5999999999999881 5. 6499999999999879 5.6999999999999877 5.7499999999999893 5.7999999999999874 5.8499999999999872 5.899999999999987 5.9499999999999904 5.9999999999999893 6.0499999999999874 6.0999999999999863 6.1499999999999861 6.199999999999986 6.2499999999999893 6.2999999999999874 6.3499999999999854 6.3999999999999853 6.4499999999999895 6.4999999999999893 6.5499999999999874 6.5999999999999854 6.6499999999999844 6.6999999999999842 6.7499999999999885 6.7999999999999838 6.8499999999999837 6.8999999999999835 6.9499999999999833 6.9999999999999831 7.0499999999999829 7.0999999999999828 7.1499999999999826 7.1999999999999815 7.2499999999999822 7.2999999999999821 7.3499999999999819 7.3999999999999817 7.4499999999999824 7.4999999999999813 7.5499999999999812 7.599999999999981 7.6499999999999808 7.6999999999999806 7.7499999999999813 7.7999999999999803 7.8499999999999801 7.8999999999999799 7.9499999999999824 7.9999999999999813 8.0499999999999794 8.0999999999999908 8.1499999999999808 8.1999999999999904 8.2499999999999822 8.2999999999999847 8.3499999999999925 8.3999999999999986 8.449999999999994 8.4999999999999964 8.5499999999999865 8.5999999999999961 8.6499999999999897 8.6999999999999975 8.7499999999999893 8.7999999999999989 8.8500000000000014 8.9000000000000021 8.9500000000000011 9.0000000000000018 9.0500000000000025 9.1000000000000014 9.1499999999999968 9.2000000000000011 9.2499999999999964 9.3000000000000025 9.3500000000000068 9.4000000000000021 9.4500000000000028 9.5 9.5500000000000007 9.6000000000000014 9.6500000000000021 9.7000000000000011 9.7500000000000036 9.8000000000000043 9.8500000000000068 9.9000000000000057 9.9500000000000064 10.000000000000007 10.050000000000017 10.100000000000009 10.150000000000009 10.20000000000001 10.250000000000012 10.30000000000002 10.350000000000021 10.400000000000016 10.450000000000022 10.500000000000014 10.55000000000002 10.600000000000016 10.650000000000016 10.700000000000017 10.75000000000002 10.80000000000002 10.850000000000026 10.90000000000002 10.950000000000022 11.000000000000021 11.050000000000022 11.100000000000023 11.150000000000023 11.200000000000021 11.250000000000025 11.300000000000026 11.350000000000026 11.400000000000027 11.450000000000029 11.500000000000028 11.550000000000029 11.60000000000003 11.650000000000032 11.700000000000031 11.750000000000032 11 .800000000000034 11.850000000000044 11.900000000000034 11.950000000000044 12.000000000000036 12.050000000000036 12.100000000000037 12.150000000000039 12.200000000000038 12.250000000000039 12.300000000000049 12.350000000000053 12.40000000000005 12.450000000000051 12.500000000000044 12.55000000000005 12.600000000000044 12.65000000000005 12.700000000000045 12.750000000000046 12.80000000000005 12.850000000000056 12.90000000000005 12.950000000000054 13.00000000000005 13.05000000000005 13.100000000000051 13.150000000000052 13.200000000000053 13.250000000000053 13.300000000000054 13.350000000000056 13.400000000000055 13.450000000000056 13.500000000000057 13.550000000000059 13.600000000000058 13.650000000000059 13.70000000000006 13.75000000000006 13.800000000000066 13.850000000000071 13.900000000000064 13.95000000000007 14.000000000000064 14.050000000000066 14.100000000000065 14.150000000000066 14.200000000000067 14.250000000000069 14.30000000000007 14.350000000000072 14.40000000000007 14.45000000000007 14.500000000000071 14.550000000000072 14.600000000000071 14.650000000000073 14.700000000000069 14.750000000000075 14.800000000000075 14.850000000000076 14.900000000000077 14.950000000000077 15.000000000000078 15.050000000000079 15.10000000000008 15.15000000000008 15.200000000000081 15.250000000000082 15.300000000000082 15.350000000000092 15.400000000000084 15.450000000000086 15.500000000000085 15.550000000000086 15.600000000000087 15.650000000000087 15.700000000000088 15.750000000000089 15.800000000000098 15.850000000000099 15.900000000000096 15.950000000000101 16.000000000000092 16.050000000000093 16.100000000000094 16.150000000000095 16.200000000000092 16.250000000000096 16.300000000000097 16.350000000000097 16.400000000000087 16.450000000000099 16.500000000000099 16.5500000000001 16.600000000000101 16.650000000000105 16.700000000000102 16.750000000000103 16.800000000000104 16.850000000000104 16.90000000000 0102 16.950000000000106 17.000000000000107 17.050000000000107 17.100000000000108 17.150000000000126 17.200000000000109 17.25000000000011 17.300000000000111 17.350000000000115 17.400000000000112 17.450000000000113 17.500000000000114 17.550000000000114 17.600000000000115 17.65000000000013 17.700000000000117 17.750000000000117 17.800000000000118 17.8500000000001 33 17.900000000000119 17.95000000000012 18.000000000000121 18.050000000000125 18.100000000000133 18.15000000000013 18.200000000000124 18.250000000000124 18.300000000000125 18.350000000000133 18.400000000000126 18.450000000000127 18.500000000000128 18.550000000000132 18.600000000000133 18.65000000000013 18.700000000000127 18.750000000000128 18.800000000000132 18.850000000000133 18.900000000000126 18.950000000000127 19.000000000000128 19.050000000000136 19.100000000000136 19.150000000000137 19.200000000000127 19.250000000000139 19.300000000000139 19.35000000000014 19.400000000000126 19.450000000000127 19.500000000000142 19.550000000000143 19.600000000000144 19.650000000000144 19.700000000000127 19.750000000000146 19.800000000000146 19.850000000000147 19.90000000000013 19.950000000000149 20.000000000000149 20.05000000000015 20.100000000000151 20.150000000000151 20.200000000000152 20.250000000000153 20.300000000000153 20.350000000000154 20.400000000000137 20.450000000000156 20.500000000000156 20.550000000000157 20.600000000000158 20.650000000000158 20.700000000000159 20.75000000000016 20.800000000000161 20.85000000000016 1 20.900000000000162 20.950000000000163 21.000000000000163 21.050000000000164 21.100000000000165 21.150000000000183 21.200000000000166 21.250000000000167 21.300000000000168 21.350000000000168 21.400000000000169 21.45000000000017 21.500000000000171 21.550000000000171 21.60000000000019 21.65000000000019 21.700000000000173 21.750000000000174 21.800000000000175 21.85000000000019 21.900000000000176 21.950000000000177 22.000000000000178 22.050000000000178 22.10000000000019 22.15000000000019 22.20000000000018 22.250000000000181 22.300000000000185 22.35000000000019 22.400000000000183 22.450000000000184 22.500000000000185 22.550000000000185 22.60000000000019 22.65000000000019 22.700000000000188 22.750000000000188 22.800000000000193 22.85000000000019 22.900000000000187 22.950000000000188 23.000000000000192 23.050000000000193 23.100000000000193 23.150000000000194 23.200000000000188 23.250000000000192 23.300000000000196 23.350000000000197 23.400000000000187 23.450000000000188 23.500000000000199 23.5500000000002 23.6000000000002 23.650000000000201 23.700000000000202 23.750000000000203 23.800000000000203 23.850000000000204 23.900000000000187 23.950000000000202 24.000000000000206 24.050000000000207 24.100000000000207 24.150000000000208 24.200000000000209 24.25000000000021 24.30000000000021 24.350000000000211 24.400000000000212 24.450000000000212 24.500000000000213 24.550000000000214 24.600000000000215 24.650000000000215 24.700000000000216 24.750000000000217 24.800000000000217 24.850000000000218 24.900000000000219 24.95000000000022 25.00000000000022 25.050000000000221 25.100000000000225 25.15000000000023 25.200000000000223 25.250000000000224 25.300000000000225 25.350000000000225 25.400000000000226 25.450000000000227 25.500000000000227 25.550000000000228 25.600000000000232 25.65000000000023 25.700000000000227 25.750000000000227 25.800000000000232 25.850000000000232 25.900000000000226 25.950000000000227 26.000000000000227 26.050000000000232 26.100000000000236 26.150000000000237 26.200000000000227 26.250000000000227 26.300000000000239 26.350000000000239 26.400000000000226 26.450000000000227 26.500000000000242 26.550000000000242 26.600000000000243 26.650000000000244 26.700000000000227 26.750000000000242 26.800000000000246 26.850000000000247 26.90000000000023 26.95000000000023 27.000000000000249 27.050000000000249 27.10000000000025 27.150000000000251 27.200000000000252 27.250000000000252 27.300000000000253 27.350000000000254 27.400000000000237 27.450000000000252 27.500000000000256 27.550000000000257 27.600000000000257 27.650000000000258 27.700000000000259 27.750000000000259 27.80000000000026 27.850000000000261 27.900000000000244 27.950000000000262 28.000000000000263 28.050000000000264 28.100000000000264 28.150000000000265 28.200000000000266 28.250000000000266 28.300000000000267 28.350000000000268 28.400000000000269 28.450000000000269 28.50000000000027 28.550000000000271 28.600000000000271 28.65000000000029 28.700000000000273 28.750000000000274 28.800000000000274 28.850000000000275 28.900000000000276 28.950000000000276 29.00000000000 0277 29.050000000000278 29.100000000000293 29.15000000000029 29.20000000000028 29.250000000000281 29.300000000000281 29.350000000000293 29.400000000000283 29.450000000000284 29.500000000000284 29.550000000000285 29.600000000000293 29.65000000000029 29.700000000000287 29.750000000000288 29.800000000000288 29.850000000000293 29.900000000000286 29.950000000000287 30.000000000000288 30.050000000000292 30.1000000000002 93 30.150000000000293 30.200000000000287 30.250000000000288 30.300000000000296 30.350000000000296 30.400000000000286 30.450000000000287 30.500000000000288 30.550000000000299 30.6000000000003 30.650000000000301 30.700000000000287 30.750000000000302 30.800000000000303 19 29 38 38 48 57 57 76 76 95 95 115 115 134 153 163 172 182 191 210 210 230 230 249 249 268 287 287 307 307 307 326 326 345 365 365 365 384 394 403 403 423 423 433 442 461 461 461 481 481 500 500 500 519 519 539 539 539 558 558 578 578 578 597 597 597 617 617 617 636 636 636 655 655 655 675 675 675 694 694 694 694 714 714 714 724 733 733 733 743 753 753 753 763 772 772 772 772 782 792 792 792 792 812 812 812 812 812 822 831 831 831 831 831 841 841 851 851 851 851 851 851 861 861 870 870 870 870 870 870 870 880 880 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 890 831 694 900 890 890 890 890 890 890 890 900 900 890 890 890 890 890 890 910 910 920 890 890 890 890 890 890 890 890 890 870 870 861 851 851 851 851 851 851 890 890 851 851 831 831 851 851 851 831 812 822 831 841 831 812 812 802 812 812 812 792 792 772 772 772 772 772 772 772 753 753 753 753 763 753 753 753 753 753 733 724 714 714 714 714 704 694 694 694 694 694 694 685 675 675 675 655 655 646 636 646 636 636 617 617 617 617 617 597 578 578 578 568 558 558 558 539 539 539 529 519 519 519 500 481 500 481 481 481 481 461 461 461 452 442 442 442 423 423 423 423 423 423 423 423 403 403 384 375 365 365 365 345 345 345 345 345 423 413 326 307 307 307 307 297 307 307 297 307 297 287 287 287 287 287 287 287 287 287 287 278 268 268 268 268 268 268 268 268 268 268 268 268 268 268 268 268 249 249 249 249 249 249 249 249 249 249 249 249 240 249 240 230 230 230 230 230 230 230 230 230 230 230 230 230 230 220 220 210 210 210 210 210 210 210 210 210 210 210 210 210 210 210 201 210 201 210 210 210 210 201 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 191 182 191 182 182 182 172 172 172 172 172 172 172 172 172 172 172 172 172 172 172 172 172 163 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 153 144 144 134 134 134 134 134 134 134 134 134 134 134 134 134 134 125 125 125 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 115 105 115 115 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 95 86 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 76 67 76 76 57 67 57 57 57 57 57 57 57 57 57 57 57 57 48 48 48 38 38 38 38 38 38 38 38 38 38 38 38 38 38 38 38 29 29 29 19 19 19 19 19 19 19 19 19 19 19 19 19 19 10 19 0 10 0 0
Time (seconds)
Future Work
Flight Simulations
MATLAB 2DOF
MATLAB has been updated to include downrange motion of the rocket
Downrange motion is only affected by launch angle; no angle of attack
Better reflection of physical system
Still lacks:
Drag Coefficient
Lack of knowledge of the true coefficient of drag prevents accurate simulation. True for RockSim and MATLAB
In order to achieve a better estimate of the drag coefficient, the max altitude of the MATLAB 2DOF was matched to the max alt. of the subscale launch altimeter data
Full Scale Max Altitude Optimization
Ran RockSim model at various wind conditions with the L1400
Found that, to minimize downrange drift, the launch angle into the wind should increase by one degree for every mph of wind
Found the additional mass needed to reach a mile depending on the launch angle
On launch day, once launch conditions are known, the additional mass needed will be added with modeling clay in between the top two centering rings (near the center of gravity), then the top centering ring will be screwed in place
Launch Angle (°)
Mass added to achieve mile (oz)
0
0
5668
26
0
5
5663
26
0
10
5647
25
5
0
5620
23.5
5
5
5589
21.5
5
10
5545
18.5
10
0
5479
14
10
5
5424
10
10
10
5356
5
15
0
5252
15
5
5178
15
10
5091
Outline
Future Work
Educational Engagement
Presented to 150 5th graders at Hidden Oak Elementary School for one hour
PowerPoint presentation taught students about the basics of rocketry, how to get involved, and how to remain safe
Three model rockets were launched to give the students an first-hand example of rocketry
Educational Engagement
Presented to sixty 4th-8th graders at Millhopper Montessori School (private school) for one hour
Similar presentation to the one at Hidden Oak, but the subscale rocket was also shown
Like at Hidden Oak, three model rockets were launched in a nearby field for the students to see
Educational Engagement
Educational Engagement
Engineering-Fair
This department wide event occurs on February 22nd and 23rd and brings in elementary, middle, and high school students from the local area to teach them about engineering
The USLI team plans on sharing a booth at this fair with AIAA and will teach students the basics of rocketry and what to do in school to better their chances at getting into UF
Aerospace Day
UF AIAA chapter brings together middle school students from around the local area to build gliders, bottle rockets, and small model rockets
The USLI team will provide support in model rocket building and launching and will also launch some higher power rockets to influence the students to pursue engineering studies. Date is uncertain
Industry
Presented to three SpaceX employees
Used PowerPoint to describe the work done over the past two years, and what the team is working towards
Showed the subscale rocket, our static test stand, and the data from the wind tunnel experiments
Also plan to present to Northrop Grumman representatives in late February
Outline
MATLAB model will be extended to 3DOF
More altimeter data collected from second subscale launch and full scale rocket launch to adjust coefficient of drag
Continued wind tunnel testing to compare experimental CD values with RockSim CD values
Compare with RockSim for various wind speeds
RockSim and MATLAB models compare to launch data. Best-fit determined
Payload Testing
Sensor conversion constant verification
Solar cell has range of 430 to 1100 nm. Test the voltage to W/m2 conversion constant
UV sensor voltage to W/m2 conversion constant (1.962)
Sensor-to-RDAS configuration
R-DAS Tiny altitude testing
Will be tested with second subscale flight and compared with PerfectFlite altimeter
Video camera vibration testing
Full scale ejection charge ground testing
Need parts to be ejected at least 15 feet apart from each other without significantly damaging components
Payload streamer descent rate verification
Need a descent rate between 50 and 100 ft/s
Payload bay separation testing
Sliding in and out of upper airframe, legs springing out
Payload landing testing
With horizontal motion, rotation, and tilt angles
R-DAS & GPS testing in Avionics Bay and Payload Bay
Static Motor Testing
The L1400 will be tested on a different test stand provided by our mentor, Jimmy, which is capable of such large motors
This will test our ignition method
This will help verify which motor characteristics that should be trusted- the official one provided by the NAR or the one provided by RockSim
The motor will also be tested with the retention device connected, just in case it effects the exhaust flow at all
UF Rocket Team Timeline
Start Date Avionics Testing Subscale rocket construction Presentation to Middle School Presentation to El ementary School Recovery Testing Subscale Launch 1 Flight Analysis 1 Full Scale construction Payload bay construction Sensor Testing CDR due Subscale Launch 2 Flight Analysis 2 Static Motor Testing Payload bay Ejection Testing Full Scale Launch 1 Full Scale Launch 2 Flight Analysis 3 FRR due Travel to Huntsville Launch Day PLAR Due 40501 40501 40512 40514 40547 40551 40551 40552 40552 40552 40567 40586 40586 40587 40587 40614 40621 40614 40623 40646 40649 40672 Duration
Nov 19-Dec 8
Nov 19-Jan 7
Mar 21
Apr 13
Apr 16
May 9
Avionics Testing Subscale rocket construction Presentation to Middle School Presentation to Elementary School Recovery Testing Subscale Launch 1 Flight Analysis 1 Full Scale construction Payload bay construction Sensor Testing CDR due Subscale Launch 2 Flight Analysis 2 Static Motor Testing Payload bay Ejection Testing Full Scale Launch 1 Full…