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 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99 100 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161 162 163 164 165 166 167 168 169 170 171 172 173 174 175 176 177 178 179 180 181 182 183 184 185 186 187 188 189 190 191 192 193 194 195 196 197 198 199 200 201 202 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221 222 223 224 225 226 227 228 229 230 231 232 233 234 235 236  # Launch of LV2c in Brothers on June 27, 2010 [[!img takeoff.png size="300x300" class="picture"]] This was our second "return to flight" launch for the LV2 series. The airframe and recovery systems remained unchanged from [[last flight|news/2009-05-31]]. We added a [[roll control module|rollcontrol]] to as a runner up to full active guidance. We ran an ARTS-2 and a Telemetrum for the flight computers. The motor was an AeroTech N2000W. This page is a container for all the relevant data from the launch of the vehicle including pictures and video. [[!toc levels="3"]] ## Design ### Overview [[!img airframe/openRocket_labeled.png size="500x500"]] We started using Solid Works on academic licenses to model the entire rocket. This was a big success, tracking all of our parts and giving reasonably accurate CG and mass estimations as well as a bill of materials and assisting in the integration of new parts that fit and worked the first time. We also created a model in OpenRocket off the Solid Works data which resulted in accurate simulations of the flight. - [The airframe CAD model is in our git repository](http://git.psas.pdx.edu/?p=airframe-cad.git;a=summary) - [[OpenRocket model|airframe/LV2c.ork]] ## Simulation We ran a simulation of the flight using [OpenRocket](http://openrocket.sourceforge.net/). This gave us lots of data for our expected performance. ### **Simulated** Launch Data This is the data run in advance, not taking into account the measured mass or cg, instead values taken from the Solid Works model. [[!table class="data" data=""" | MKS | Imperial **GLOW** | 29.5 [kg] | 65.0 [lbs] **CP** (from tip of nosecone)| 2.72 [m] | 107.0 [in] **CG** (from tip of nosecone)| 2.56 [m] | 100.7 [in] **Burn Time** | 7.7 [s] | 6.45e-6 [fortnights] **Apogee** | 4616 [m] | 15,146 [ft] **Max Speed** | 358.9 [m/s] (Mach 1.05)| 802.8 [mph] **Max Accel** | 95.7 [m/s2] (9.75 [g]) | 314 [ft/s2] """]] [[!img height.png size="500x500"]] ### Notes ## Pictures ### Launch Prep
### Launch
### From onboard
## Video - View of the launch from the flight line. - [[!img launch_flightLine_still.png size="100x100"]] - Download: [[launch_flightLine_short.mp4]] - Watch on YouTube: [http://www.youtube.com/watch?v=2PoPGujVU5I](http://www.youtube.com/watch?v=2PoPGujVU5I) - View of the lunch from the top of a nearby hill. (Note the speed of sound delay!!) - [[!img launch_hill_still.png size="100x100"]] - Download: [[launch_hill_short.mp4]] - Watch on YouTube: [http://www.youtube.com/watch?v=6P6lFe1y9Hg](http://www.youtube.com/watch?v=6P6lFe1y9Hg) - We have a number of stills from Casey's camera taken at 20 fps. Here they are rendered together into a video: - [[!img takeoff.png size="100x100"]] - Watch on YouTube: [http://www.youtube.com/watch?v=1fD8NFaxiMs](http://www.youtube.com/watch?v=1fD8NFaxiMs) - Onboard camera video from the flight, starting just before ignition and lasting until just after touchdown. - [[!img photos/Horizon.png size="100x100"]] - Download: [[psas-lv2c-2010-06-27-short.avi]] - Watch on YouTube: [http://www.youtube.com/watch?v=vKw75YMiLA0](http://www.youtube.com/watch?v=vKw75YMiLA0) ## Launch Data ### Flight at a glance Actual Recoded data from the flight: - **Motor**: AeroTech N2000-W - **Liftoff Time**: 2:44 pm PDT June 27th, 2010 [[!table class="data" data=""" Metric | MKS | Imperial **GLOW** | 30.8 [kg] | 67.9 [lbs] **CG** (from NSR seam) | 1.357 [m] | 53.44 [in] **Apogee** (from TeleMetrum) | 4784.94 [m] | 15,699 [ft] **Max Speed** (from TeleMetrum) | 374.83 [m/s] (Mach 1.10 - sea level)| 838.5 [mph] **Max Accel** (from TeleMetrum) | 102.93 [m/s2] (10.5 [g]) | 337.7 [ft/s2] """]] ### Raw data All of the raw data is in the [raw data folder](http://psas.pdx.edu/lv2c_launchdata-2010-06-27/data/) for this launch #### TeleMetrum [TeleMetrum](http://www.altusmetrum.org/TeleMetrum/) flight data: - "Raw" ASCII data from the EEPROM: [[data/telemetrum.eeprom]] - Processed log: [[data/telemetrum.telem]] - Simple tab delimited file: [[data/telemetrum.detail]] - KML (Google Earth) file: [[data/telemetrum.kml]] #### ARTS2 Raw data from the [ARTS2 flight computer](http://www.ozarkaerospace.com/) - Raw data in ARTS (proprietary) format: [[data/ARTS2.odf]] - Plain CSV of the data (imperial units): [[data/ARTS2.csv]] - Plain CSV of the data (MKS units): [[data/ARTS2_MKS.csv]] #### Roll (CAN logger) - A CSV dump of the raw data [[data/CAN_converted.csv]] #### Opal In addition to the rocket flight computers we had a piggyback payload of an experimental motion recording device from the medical world. It contains a 6DOF IMU and 3-axis magnetometer. It was never designed for such a harsh environment, but nevertheless has recorded very interesting data. - Plain CSV data in MKS units: [[data/opal.csv]] ## Data Analysis/Conclusions ### Fin Flutter Careful viewing of the on board camera footage shows the fins fluttering for about one second around frame 31535. Liftoff was on frame 31423. At 30 frames per second this suggests the flutter happening about 3.7 seconds into the flight. This would correspond to the transonic region of flight right as the rocket enters Mach 1 according to both simulations and the flight computers. [[!img fins.png size="600x600"]] The above image shows two nearby frames from the on board camera with the right fin highlighted. In frame 31535 the fin is painted red and in 31537, blue. On the right the two images have been stacked and the fin highlights compared. The fin appears to undergo a flutter with an amplitude of about 4°s. #### Conclusion In general fin flutter is not a good thing. Oscillations can exceed material shear strength and break off fins resulting in catastrophically unstable flight. We are probably fine, but stiffening the fins won't hurt. ### Roll Control The [[roll control|rollcontrol]] was only a partial success. The mechanical and software systems appeared to work as designed. However we appeared to experience a "control reversal" where fins placed in the counter clockwise arrangement caused the rocket to rotate in the clockwise direction and visa versa. The cause of this problem is aerodynamic in nature and is under investigation. - [[Roll Control Failure Discussion Page|controlreversal]] ### Acceleration Data Here is a graph with a comparison of the raw data from the 3 on board computers that had accelerometers. They were all single axis accelerometers aligned vertically. They only capture vertical acceleration and so are only useful from launch to apogee. [[!img accel_raw.png size="650x325"]] Here is the acceleration just during the motor burn. There seems to be an interesting shoulder around the transonic region. [[!img accel_burn.png size="650x325"]] Taking all this data we created an averaged result by putting all the data into 50ms bins: [[!img accel_bin.png size="650x325"]] Download the binned data: [[accel binned.csv]] #### Comparison with OpenRocket This was our first launch using [OpenRocket](http://openrocket.sourceforge.net/) as our primary pre-launch simulation engine. Here we compare our recorded acceleration to the simulation. On the whole it did quite well. We suspect that the thrust curve that it had on file for our engine was not very accurate (or at least our motor deviated from it). [[!img accel_or.png size="650x325"]] Here is a close up of just during the burn. [[!img accel_or_burn.png size="650x325"]] ### Velocity Taking our binned/averaged data we can integrate to find the velocity at each point: [[!img velocity.png size="650x325"]] ### Drag After the motor burns out we should be able to find all the forces on the rocket; drag and gravity. Gravity is easy to predict and knowing the mass and acceleration we can solve for drag force: [[!teximg code="F_d = ma - mg" ]] [[!img drag.png size="650x325"]] Knowing the Drag force, height of the rocket, and velocity of the rocket we can estimate the Cd empirically. We simply solve for Cd. [[!teximg code="F_d = \frac{1}{2} \rho v^2 C_d A" ]] [[!teximg code="C_d = \frac{2 F_d}{\rho v^2 A}"]] [[!img drag_cd.png size="650x325"]] This technique does not appear to work very well, unless OpenRocket is just very wrong about drag. Which is possible. The technique is very sensitive to having the correct velocity.