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Project DiffusionThe effect of gravitational stress on the diffusion of liquids.

New team

Part 1: VehicleMajor Milestone ScheduleFebruary 17Full scale vehicle completedFebruary 18Full scale test flight #1 (1/2 impulse)March 17Full scale test flight #2 (full impulse)April 19/20Flight hardware and safety checksApril 21Launch day, full scale fight #3April 28/29Full scale flight #4 (rain date flight)GANTT Chart

Mission Profile Chart

Event 1:Ignition at 0s, 0ft Event 2:Burnout at2.24s, 1000ftCoastEvent 3:Apogee at16s, 4502ftDrogue descentEvent 4:Main parachute deployment at 84s, 700ftEvent 5:Landing at110s, 0ftApogee prediction updated based on data from full scale full-impulse flight (Cd=0.65): 4502ftVehicle Success CriteriaMotor ignitionStable flightAltitude of 5,280 feet AGL reached but not exceeded (most current prediction: 4502ft)Both drogue and main parachute deployedVehicle returns to the ground safely with minimal damageSafe recovery of the booster Vehicle Drawings

CP 83.1 from nosecone CG 65.6 from noseconeStatic margin 5.5 calibers

Length 108Diameter 5.5(body tube), 4(booster)Liftoff Weight 21 lbs with AT-K1050WMotor Aerotech K1050W Vehicle Parts

LetterPartANoseconeBMain ParachuteCDrogue ParachuteDPayload BayETransitionFMotor MountGFinsConstruction MaterialsBody: 5.5/4.0 LOC Precision fiber tubing Fins: 1/32 G-10 fiberglass + 1/8 balsa sandwich, TTW mountedCouplers: LOC Precision with stiffenersBulkheads, centering rings: 1/2 plywoodMotor mounts: 54mm Kraft phenolic tubingNosecone: Plastic nose coneRail buttons: standard nylon rail buttonsMotor retention system: Aeropack screw-on motor retainerAnchors: 1/4" stainless steel U-BoltsEpoxy: Locktite epoxyMotor SelectionLength[in]Mass[lbs]Diameter [in]Motor SelectionStability Margin [calibers]Thrust to weight ratioBurn time10816.05.5, 4.0AT-K1050W5.512.22.5sWe selected the AT-K1050W 54mm motor to propel our rocket to reach, but not exceed an altitude of 5280ft AGLThe AT-K1050W motor provides an appropriate thrust to weight ratio for our vehicle (12.2).Mach delay of 4 seconds will be set on both deployment altimeters(the setting was successfully tested during full impulse test flight)Thrust Curve AT K1050W

Altitude ProfileApogee 4502ft, 16s

Cd = 0.65(from flight data)

Acceleration ProfileMax acceleration:16g

Velocity ProfileMaximum velocity

507 mph (Mach number: 0.66)

Apogee vs. Wind SpeedWind Speed[mph]Altitude[ft]Percent Change in Altitude046200.00%546120.10%1045900.60%1545541.40%2045022.30%Flight Safety ParametersParameterValueFlight Stability Static Margin5.5Thrust to Weight Ratio12.2Velocity at Launch Guide Departure (12ft x 1 rail)70mphEjection Charge CalculationsWp=dP*V/(R*T)Wp - ejection charge weight [g]dP - ejection pressure (15 [psi])V - free volume [in3]R - universal gas constant (22.16 [ft-lb oR-1 lb-mol-1])T - combustion gas temperature (3,307 [oR])Ejection ChargesParachuteCharge [g]Drogueprimary2.4apogeebackup3.0apogee + 1sMainprimary5.5700ft AGL500ft AGLbackup7.0Charges have been finalized via static ejection tests. Per NASA recommendation we have upgraded our backup charges by 25% and delayed their activation. If primary charge fails, backup charge will try harder, otherwise it fires harmlessly in open air.Electrical Schematic

ParachutesParachuteDescent Weight (lbs)Parachute Diameter (in.)Descent Rate (ft/s)Kinetic Energy at Impact(ft-lbf)Drogue18.752454N/AMain18.759023Nosecone23.1Body58.6Booster69.4Drift PredictionsWind Speed(mph)Drift(ft)Drift(mi)0 0 0 5 8140.1510 16300.3115 24440.4620 32590.62Verification PlanTested Components

C1: Body (including construction techniques) C2: Altimeter C3: Accelerometer C4: Parachutes C5: Fins C6: Payload C7: Ejection Charges C8: Launch System C9: Motor Mount C10: Beacons C11: Shock Cords and Anchors C12: Rocket Stability22Verification PlanVerification Tests V1 Integrity Test: force applied; verifies durability. V2 Parachute Drop Test: tests parachute functionality. V3 Tension Test: force applied to shock cords; tests durability. V4 Prototype Flight: tests feasibility of vehicle with scale model. V5 Functionality Test: tests basic functionality of device on ground. V6 Altimeter Ground Test: simulate altitude changes; verifies preset altitude events fire. V7 Electronic Deployment Test: tests that electronics ignite deployment charges. V8 Ejection Test: tests that deployment charges can deploy parachutes/separate components. V9 Computer Simulation: RockSim predicts behavior of launch vehicle. V10 Integration Test: payload fits smoothly and snuggly into vehicle, and withstands flight stresses.23Verification MatrixV1V2V3V4V5V6V7V8V9V10C1C2C3C4C5C6C7C8C9C10C11C1224Full Scale Half Impulse Launch

Half Impulse LaunchLiftoff weight17 lbMotorAerotech K1100TLength9ftDiameter5.5 payload section4 boosterStability Margin5.3Half Impulse Launch ObjectivesTest drogue and main parachute deploymentTest flight electronics (altimeters and ejection charges)Test separation of body tubes at ejectionTest validity of simulation resultsTest rocket stabilityTest durability of rocketHalf Impulse Launch ResultsApogee- 3325ftRocksim prediction 3396ftTime to apogee- 13.4sApogee eventsDrogue deploymentMain eventMain parachute deploys at 700ft Calculated Cd : 0.61

Apogee for full scale impulse vehicle (Cd=0.61): 4718 ftRecorded Altitude Profile

Apogee : 3325ft at 13.4s(drogue deployment)Drogue Descent: measured rate 43fps (average)Main parachute: deploys at 500ft Final Descent: measured rate 21fps (average)Observed Problems

Because of a construction error, our fin assembly separated from the rest of the rocket at apogee (due to deployment shock). The problem has been fixed by adding 12 screws.Our drogue parachute was by mistake tied far from its upper anchor point (this increases the chance of drogue not leaving the body). The problem has been solved by moving the drogue closer to its upper anchor point.Full Scale Full Impulse Launch

Full Scale LaunchLiftoff weight21 lbMotorAerotech K1050WLength9ftDiameter5.5 body, 4 motor tubeStability Margin5.5Full Impulse Launch ObjectivesTest drogue and main parachute deploymentTest flight electronics (altimeters and ejection charges)Test separation of body tubes at ejectionVerify the flight apogee will not exceed 1 mileVerify fixes from half-impulse flightVerify final predictionsFull Impulse Launch ResultsApogee- 4502ftRocksim prediction 4718ft

Time to apogee- 16sApogee eventsDrogue deploymentMain eventMain parachute deploys at 700ft Calculated Cd : 0.65

Apogee for full scale vehicle (Cd=0.65): 4502 ft

Recorded Altitude ProfileApogee : 4502ft at 16.00s(drogue deployment)Drogue Descent: measured rate 54fps (average)Main parachute: deploys at 700ft Final Descent: measured rate 23fps (average)Problems Observed

Our rocket landed in the tree and we have lost some of its parts. This results in following issues:IssueSolutionTestsNosecone not recovered, need new noseconeNew noseconeRepeat static ejection testShockcord partially lostReplace shockcordRepeat static ejection testParachute lostReplace parachuteRepeat static ejection testAltimeters possibly damagedReplace altimeters*Pressure chamber testE-bay damagedRepair e-bayRepeat static ejection test* MAWD altimeters are no longer available and we will be replacing them with StratoLogger altimeters. While we will have no opportunity to test the StratoLogger units ourselves before the launch in Huntsville, our sister team has used StratoLoggers with success during their full impulse test flight. Delivery System Summary

Apparent coefficient of drag Cd=0.65

Apogee prediction 4,500ft

Primary motor choiceAT-K1050WWork to be done

Improve surface finish (decrease Cd)Remove surface protrusions (decrease Cd)Search and pursue minor weight savingsRepair E-bay

Recovery System Summary

ParachuteDescent Weight [lb]Descent Rate[fps]Ejection Charge [g]Impact Energy [ft-lbf]24 Drogue18.75542.4-90 Main18.75235.5Top23.1Body58.6Booster69.4To further reduce the drift, wed rather use a smaller drogue than to decrease the size of the main parachute (the booster impact energy is near the allowed maximum of 75ft-lbf)Work to be done

Replace lost parachuteReplace lost shockcordReplaced possibly damaged altimetersRepeat static ejection tests

Part II: Payload

Payload SummaryWe will investigate the effects of acceleration and vibrations during flight on the diffusion of dye into liquids using digital imaging.Payload ObjectivesDetermine the effect of acceleration on the diffusion of dye into liquids

Determine the effect of vibrations on the diffusion of dye into liquidsPayload Success CriteriaCollected data from the camera and accelerometers is accurateVessels containing liquid do not leakDye is injected into the liquid correctlyImages from camera are receivedAcceleration is recordedPayload is recoveredPayload Assembly

BatteryCameraLEDSyringeServoPayload Prototype

BatteryCameraLEDSyringeServo

Payload Electronics

Payload Computer Drives injector servosCollects and stores acceleration dataMonitors accelerometer for liftoff detectionMonitors G-Switch for liftoff detectionDistributed regulated voltages 3.3V for sensors 5.0V for servosPowered from a single pack of 6AA batteries80MHz, 32KB RAM, 8 core processor, 27 I/O pins128KB of EEPROM, 96KB available for data storageAccelerometer / G-Switch moduleLIS331 3D accelerometer+/- 24g, 16 bit resolutionDigital interface1000Hz maximum sampling rateGS21 G-switch (2.1g)Powered by payload computer (3.3V)Connected by a single ribbon cableData Acquisition Rates and Memory NeedsFlight PhaseSampling Rate[Hz]Memory Usage[KB]Ascent40016Descent10020Total-36Dimensioned Drawing of Payload

Nikon AW100 Camera

Selection RationaleFits inside the payload chamberWaterproof (in case of payload damage)Minimum focus is 1cm (0.4)Full HD video 1920 x 1080 @ 30fpsSufficient memory/battery capacity Within the budget of our project ($300)Robust design (designed for extreme sports)Integration of Payload Modules

Vertical moduleHorizontal moduleHorizontal moduleExperiment SequenceLaunch and BoostDye is injected into the solutionCamcorder records the diffusion processThe experiment chamber is brightly lit using LEDs to prevent any exposure problems during recording

The camcorder continues to record the diffusion process until the vehicle reaches apogee.Coast and Apogee Experiment SequenceAccelerometer records acceleration data.Experiment SequenceData Analysis

The pictures taken during the flight are analyzedControls Preflight ground testsCamcorder takes overhead pictures of Petri dishCamcorder takes side view pictures of water tank

Experimental GroupControl Group (stationary)Variables Independent variables a Acceleration t Time after dye is released (flight time)

Dependent Variables R Rate of diffusion (diffusion front speed) P Pattern of diffusion (qualitative classification)CorrelationsR = f(a) Rate of diffusion in relation to accelerationR = f(t) Rate of diffusion in relation to time after dye is releasedP = f(a) Pattern of diffusion in relation to accelerationP = f(t)Pattern of diffusion in relation to time after dye is releasedTest and MeasurementTestMeasurementRate of DiffusionDyed area boundary rectangle expansionPattern of DiffusionWidth to height ratio of dyeColor saturation per pixelVoids in dye55Image Analysis

Voids

Boundary rectangle: X pixels by Y pixelsMeasure color saturation in each pixelImage Analysis

CharacteristicMeasurementAverage void sizeMeasured in pixelsVoid scatteringNumber of void areasColor dye spreadClear vs. colored area (in pixels)Directional dye spreadWidth vs. height of color areaTo quantify the results of our experiment, we have selected the following characteristics to measure. Computerized digital image analysis will be used and we expect to process over 7 billion pixels using a multicore Linux machine.Instrumentation and MeasurementWe will use commercially available accelerometers and altimetersThe sensors will be calibratedWe will do extensive testing on the ground prior to the rocket launchVerification PlanTested Components

C1: Camera C2: Injection C3: Diffusion VesselVerification PlanVerification Tests

V1 Basic Function Test: testing the main functions of the payloadV2 Leak Test: verifying that the vessels containing the liquid do not leakV3 Battery Life Test: verifying that the battery life of the camera is long enough to take pictures during the entire diffusion processVerification MatrixV1V2V3C1C2C3

Questions?