2 Team SummaryLeads: Matthew Gentile, Christina Middleton, Jayant Mukhopadhaya, Bader Nasser, Matthew SkeelsAdvisor: Dr. Ephrahim GarciaMentor: Mr. Daniel Sheerer, TRA No: 13281
3 Presentation Outline 1. Changes made since proposal 2. Launch Vehicle Subsystem3. Recovery Subsystem4. Mission Performance Predictions4. Payload Criteria5. Project Plan
4 1.1 Changes Made Since Proposal - Launch Vehicle The payload and the R&T sections have been separatedThe drogue has been moved from below the nose cone to below the R&T bayThe dimensions of the fins have changedThe Hazard Detection Camera has been moved from the bottom of the sustainer section, to the top of the payload sledOverall length has increased from 95.5 inches to 110 inches and the weight of the rocket has increased from 32.7 lbs to lbsShould we have changes
5 1.2 Changes Made Since Proposal - Recovery and Tracking Added reefing system to main parachuteDesigned cable cutterNose cone ejected at 6,100 ft for better payload ejection mechanism design
6 2. Launch Vehicle Criteria 2.1 Mission Statement2.2 Subsystem Overview2.3 Material selection2.4 Performance Characteristics-launch vehicle designed to meet all the requirements as outlined in section 1 of the NASA SL handbook, operating within the specified constraints
7 2.1 Mission StatementCornell Rocketry Team plans to develop a robust, streamlined, and cost effective inline two-stage rocket that will reach a desired apogee of 9,600 feet. Capabilities include a novel payload ejection system, the dispersion of ejectable methane units to collect scientific data, a custom recovery system made in house and a hazard detection camera to warn users on the ground of potential threats in real time. By demonstrating this technology, the team hopes that our efforts will contribute to the advancement of rocketry in both academic and commercial sectors.I know it’s not good to have big blocks of text but I feel this is an important one
9 2.3 Material Selection- Airframe Blue Tube selected for airframeIncreased durability to withstand Mach .71 forcesFiberglass reinforcementRocket lighter than rocket with same strength using phenolic tubingWhat is the strength of blue tube??
10 2.3 Material Selection- Bulkheads Constructed from birch plywood reinforced with carbon fiberPrimary bulkhead force is a bending forceUsed property M’ = σ0ρ plotted in CES Edupack for selectionStress analysis in SolidWorks verified material choice
11 2.3 Material Selection- Fins Balsa wood core with three layers of carbon fiber reinforcement inserted into fin slots, secured with Proline High Temperature EpoxyAdditional layer of carbon fiber secures fins to body
12 2.3 Material Selection- Nose Cone Constructed from filament wound fiberglassSuperior strength to weight ratio than biaxial fiberglassAluminum tipNOSE CONE DESIGN
13 2.6 Risk Analysis Extensive risk analysis completed on rocket Risk plot used to severity and probability of risk.Example of risks include:Catastrophic failure during test launchNot meeting major deadlinesSafety accidents during manufacturingMitigation of Risks include extensive testing, adhering to strict schedules and following all proper safety procedures.
14 2.7 Testing Tension, Compression, Crush, Three Point Bending Ground Testing of electronics and recovery systemsDrop TestingHalf-scale and low power testing
16 2.10 Electrical Schematics of Recovery System- 1st Stage Timer with 9V battery and key lock switch used to separate booster from sustainer stageKey lock accessible from outsideAll systems redundant
17 2.10 Electrical Schematics of Recovery System- 2nd Stage Two Raven 3 altimetersHas 4 eventsMinimum of three events needed to implement reefing systemsAll systems redundantKey lock accessible from outside
18 2.11 Mass Statement Yields a 6.37:1 thrust to weight ratio Can increase weight by 9.7 lb and still launch safelySubsystemMass (lbs)Airframe23Recovery and Tracking6.6Payload5.6Total35.2
19 3. Recovery Subsystem 3.1 Parachute Design 3.2 Main Parachute 3.3 R&T Bay3.4 Forces on Rocket
20 3.1 Parachute DesignParachute Type: semi-ellipsoidCoefficient of Drag: 1.25Shroud lines proportional to diameter of parachuteSpill hole located at center of each parachute for stabilization
21 3.2 Main Parachute 120 inch diameter main parachute Deployed at 900 ft Main Parachute uses reefing mechanismWill allow parachute to open more smoothlyLess force applied to components on rocketsCable cutter built in-house
23 3.3 R&T Bay Designed to be lightweight Carbon fiber electronic mounts Removable Carbon Fiber disks allows addition of more electronicsIndividual carbon fiber plates allows multiple people to work on different electronic components simultaneouslyR&T bay can be completely assembled outside of rocket for easier launch preparation
24 3.4 Forces on Rocket Forces exerted on rocket as seen in diagrams Top image: MainBottom image: DrogueR&T Bay Retainer ring transmits forces through coupler tubes to airframe
25 3.4 Forces on RocketCalculated snatch force on rocket from parachute deployment.
26 4. Mission Performance Predictions 4.1 Motor Characteristics4.2 Altitude Simulation4.3 Velocity Simulation4.4 CP and CG Estimates4.5 Kinetic Energy Estimates4.6 Drift for Each Section
27 4.1 Motor Characteristics First stage: Aerotech K1000T-P motorAverage thrust: 1012 NTotal impulse: 2497 N*sThrust to weight: 6.46
28 4.1 Motor Characteristics Second stage: Aerotech K560W motorIgnited 3 seconds after first stage burn outAverage thrust: 551 NTotal impulse: 2467 N*sThrust to weight: 4.84
29 4.2 Altitude Simulation Projected apogee: 9,600 ft Time to apogee: 29.6 s
32 4.5 Kinetic Energy Estimates All of these fall below the required 75 ft-lbf KE with a safety factor of 2.14Kinetic Energy at LandingBooster Sectionft-lbfSustainer Sectionft-lbfR&T Sectionft-lbfPayload Sectionft-lbfNoseconeft-lbf
33 4.6 Drift for Each SectionDrift of components calculated using custom MATLAB Script0 mph5 mph10 mph15 mph20 mph1st stage0 ftftftftft2nd stage1636 ft ftftftftNoseConeftftftftDO YOU THINK THIS IS A NECESSARY SLIDE?
35 4.1 Hazard Detection Camera Detect three categories of objects during descent:Objects > 5 ft2, objects < 5 ft2, circular objects
36 4.1 Hazard Detection Camera Will begin looking for hazards at 1600 ftCamera module mounted on payload ejection sledWill only turn on if nosecone separates from rocketWill test full capabilities in half-scale testdo we have any pictures to include here?
37 4.1 Hazard Detection Camera Raspberry pi processor used for edge detectionOpenCV vision software will be used
40 4.2 Payload Ejection Mechanism Houses three Ejectable Methane sensing Units (EMUs) to be ejected at 1500 ft, 1000 ft and 500 ftFeatures sled on rails which will begin motorized extension at 6100 ftWill fully protrude full 12” from rocket prior to ftWill fully retract by 100 ft to avoid damage
42 4.2 Payload Ejection Mechanism Parallax altimeter will determine when to eject EMUsWill fire using pyrotechnic charge, threaded into phenolic canistersAltimeter interfaces with Raspberry Pi to ignite E-match with transistor circuit.
43 4.3 Payload Ejection Mechanism Firing Circuit SchematicEither know how to explain this in presentation or add labels/text
44 4.3 Ejectable Methane Units Payload ejection mechanism will deploy the EMUs at three different heightsThe payloads’ descent will be slowed with tri-wing configurationWings made of nylon and spring wireTerminal velocity: 7 ft/s
45 4.3 Ejectable Methane Units Payload units 3D printed from ABS plasticPaired with offset stand to give wings clearance from baseWhen leg and wings contracted, largest dimension: 2.8”
46 4.3 Ejectable Methane Units Will collect atmospheric methane concentrations on groundWill send methane concentrations and GPS coordinates to ground station with XBeeAchieves actuation with the use of a double jointed arm and nitinol wire
47 4.4 Dual Inline Staging Two stage, inline motor design Eliminates hazards involved with simultaneous ignition errors associated with parallel motorsLower thrust to weight ratioDanger of misaligned rocket during ignition
48 4.4 Dual Inline Staging Ignition of second stage Stager series to avoid premature ignitionPerfectFlite MiniTimer4 series staging device andArms only if 0.3 second upward acceleration prior to decelerationRockeTiltometer for redundancyOnly fires within specified angle rangewhatever you do don’t have a freudian slip on “premature ignition”
49 4.4 Dual Inline Staging 1st stage burns for 2.5 s Timer blows black powder charge, separating boosterMain deploysSecond stage ignites 3s after burnout~100ft between stages
50 Funding Plan Majority of funding from Cornell University Finishing a new sponsorship packet and plan to send it out in mid JanuaryActively searching for more funds and ways to cut down on costs to save for travel for more teammates
51 Educational Engagement Previously taught concepts and physics behind rocketry with middle school studentsTeam up with URRG to hold an event at the Science CenterCreate more connections with school and Boy Scouts in the area