PRELIMINARY DESIGN REVIEW 2015 NASA STUDENT LAUNCH FLORIDA INTERNATIONAL UNIVERSITY (FIU-ASME) MAXI-MAV
TEAM ORGANIZATION T eam Leader: Giancarlo Lombardi NAR – Level 1 certified Safety Officer: Maryel Gonzalez NAR – Level 1 certified Lead Designer: Christopher Hayes Mentor: Joseph Coverston TRA – Level 2 certified
MISSION STATEMENT FIU ASME will design and build Autonomous Ground Support Equipment (AGSE) that will be capable of performing on-pad operations to prepare a high-powered rocket for launch that will be capable of reaching altitudes no greater than 3000 ft above ground level. In addition, the AGSE will recover a payload located outside the rocket’s mold line and insert the payload into the rocket’s payload bay.
CHANGES SINCE PROPOSAL
VEHICLE CHANGES Material: Carbon Fiber -----> Fiberglass issues with carbon fiber blocking radio transmissions from the internal GPS units. Recovery: T wo ----->Three parchutes Initial design: drogue doubled as our main after payload separation (high decent rates.) The payload bay and upper airframe will now have a dedicated main parachute. Fins: Four -----> Three trapezoidal fins. better center of pressure and overall rocket stability in our simulations. Motor: K2045 -----> J1520 projected altitude of 3155 feet (previously 4453 feet.)
AGSE CHANGES No changes
PROJECT PLAN CHANGES NEW Safety Officer: Maryel Gonzalez (NAR – Level 1 Certified) Carmela Vallalta (previous Safety Officer) received a Spring 2015 internship with NASA Dryden Flight Research Center
VEHICLE CRITERIA
MISSION SUCCESS CRITERIA The vehicle’s mission will be considered to be a success if the following criteria are met: The vehicle’s apogee does not exceed 5000 ft above ground level. The payload is ejected at 1000 ft. The vehicle’s descent is controlled and does not result in damage to itself, property, or people. No safety violations occur.
LAUNCH VEHICLE SUMMARY Length: 117 inches Inner Diameter: 3.9 inches Unloaded: 13 lbs; Loaded: 15.2 lbs Motor: J1520, Pro 54mm – 3G Dual-Deployment Drogue deploys at apogee, mains deploy at 1000 ft.
DESIGN AT SYSTEM LEVEL Airframe materials: 3.9” Phenolic tubing Fiberglass Three independent sections: Lower Airframe Payload Bay Nosecone & Upper Airframe
AIRFRAME Airframe Material PML Phenolic Fiberglassed PML Giant Leap Fiberglass Phenolic Tubes Property Weighing Unit of Value Score T otal Value Score T otal Value Score T otal Factor measure Strength 4 High Med low 3 12 High 10 40 High 10 40 Low Cost 4 $ $23.50 10 40 $35.0 9 36 $97.28 4 16 Manufacturability 2 Easy-Hard Easy 10 20 Hard 4 8 Easy 10 20 Weight 1 oz 20.4oz 10 10 40oz 5 5 30oz 7 7 T otal 82 T otal 89 T otal 83
NOSECONE Nose Cone Material PML Plastic Fiberglassed PML Shockwave Rocketry Intellicone Nosecone Plastic Nosecone Fiberglass Nosecone Property Weighing Unit of Value Score T otal Value Score T otal Value Score T otal Factor measure Strength 6 High Med Low 2 12 High 10 60 High 10 60 Low Cost 4 $ $25.0 10 40 $30.0 8 32 $56.0 5 20 Manufacturability 2 Easy-Hard Easy 10 40 Medium 5 10 Hard 0 0 Weight 1 oz 10oz 10 10 25oz 5 5 15.1oz 7 7 Contains interior 3 Y/N Yes 10 30 Yes 10 30 No 0 0 Payload bay T otal 132 T otal 137 T otal 87
NOSECONE – UPPER ELECTRONICS BAY Intellicone was chosen for nosecone Decided to incorporate electronics bay in order to decrease overall rocket length Altimeter: Perfectflite Stratologger GPS unit: TK102 Buzzers will be present to perform audible beeps for easy retrieval Middle bulkhead ensures altimeter is physically separated from all other components
PAYLOAD BAY Rail system Bay opens to accept payload insertion Payload reception tube made out of 3” cut-out airframe Stepper motor located on bottom bulkhead of sliding plate drives the translation Powered externally by AGSE Quick-release power cable will be used – it will be pulled off the face of the vehicle when the rail is lifted
LOWER ELECTRONICS BAY Contains: Altimeter: Perfectflite Stratologger (x2 units - redundancy) GPS: TK102 PVC cleanout plug will be used for its strength Subjected to high axial forces – ejection and deployment – through the eyebolt Bolts extend through PVC supporting electronics
LOWER AIRFRAME / BOOSTER SECTION Motor choice: Cesaroni Pro54 - J1520 3G Three trapezoidal fins Root chord length: 4 in Tip chord length: 1.75 in Thickness: 0.063 in Sweep angle: 14.3 degrees
RECOVERY SYSTEM Drogue deployed at apogee (3000 ft.) Dual main deployment at 1000 ft T op section is jettisoned containing the payload bay Lower airframe descends on 44” main parachute Upper airframe descends on 12” drogue and 54” parachute
RECOVERY ELECTRICAL SCHEMATICS
AGSE CRITERIA
AGSE SCHEMATIC
RAIL LIFT Rail: 8 ft. 1” 80/20 rail Linear Actuator: 180 lbs thrust Retracted length: 18inches Travel: 12 inches 1” foot is located below launch rail to counteract moment produced by the rail and the rocket sitting on the rail Also serves to mount the linear actuator and push up on the rail
ROBOT ARM Single beam arm with robotic claw will rotate to pick up the payload from the ground. The arm will follow its circular arc path to drop the payload into the rocket The robot arm will be mounted on a platform offset by one arm length from the rocket’s payload bay
IGNITER INSERT Igniter will be placed on a rod attached to a rack The igniter will initially start below the thrust plate to increase pad safety The rack will be pushed upwards (towards the rocket’s motor) through the rotational motion of a pinion Once the igniter has been inserted, a clamp will hold the igniter in place The rod will be retracted downwards to decrease damage from motor ignition
AGSE ELECTRICAL SCHEMATIC
PROJECT PLAN
RISK ANALYSIS Risk Likelihood Impact Mitigation Late completion of Medium High Simultaneously design Reports and rocket and write Presentations report to keep updated documentation at all times. Late completion of Medium High Order parts and test rocket and/or components early to identify potential AGSE construction problems and allow for time to rectify them. Team member High Medium Continuously recruit decides not to and educate students continue working who are interested in on project rocketry and the NASA Student Launch competition Required budget is Set fundraising goals Medium High not met higher than necessary to account for any possible setbacks we may encounter Full scale rocket Follow mission Low Medium test failure performance criteria checklist prior to launch AGSE system fails Low High Perform extensive to perform testing of AGSE required function before final launch
TIMELINE November 5 Preliminary Design Review (PDR) report due 6 Start ordering parts for subscale vehicle 10 Begin fundraising efforts by contacting company sponsors 14 Start constructing AGSE components 19 PDR video teleconference 21 Begin constructing subscale vehicle 29 Ground ejection test December 3 Begin constructing full scale rocket 13 Subscale flight test January 6 AGSE testing 16 Critical Design Review (CDR) report due 21-31 CDR video teleconferences February 1-4 CDR video teleconferences March 7 Full-scale flight test 16 Flight Readiness Review (FRR) report due 18 FRR video teleconferences April 7 Team travels to Huntsville, AL 7 Launch Readiness Reviews (LRR) 8 LRR’s and safety briefing 12 Backup launch day 29 Post-Launch Assessment Review (PLAR) posted
EDUCATIONAL ENGAGEMENT Partnered with FIU ‘Engineers On Wheels’ provides local K-12 students with fun and interactive presentations on varying fields of engineering Plan to reach out to 250 middle school-aged students Will produce basics of aerodynamics and principles of rocketry presentation Powerpoint with live demonstrations of actual high-powered rockets (owned by team members) Water
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