● Team Structure ● Mission Success Criteria ● Vehicle ● Recovery ● Drag Module ● Payload - Rover ● Payload - Housing ● Testing Plan ● Safety ● Project Plan
● Ashton Johnston - Team Lead ● Dallas Solomon - Safety Officer ● Taylor Forte - Project Manager ● Jose Giacopini - Vehicle Lead ● Brandon Crotty - Vehicle Construction ● Tijon Clark - Vehicle Construction ● David Jessick - Vehicle Recovery ● Jennifer Adams - Payload Lead ● Pedro Regalado - Payload Electronics ● Michael Stokes - Rover Housing Design ● Andrew Hillier - Rover Design ● Andrew Dahl - Rover Construction
● Team Structure ● Mission Success Criteria (Section 3.0.2 & 5.0.2) ● Vehicle ● Recovery ● Drag Module ● Payload - Rover ● Payload - Housing ● Safety ● Project Plan
● Mission Success Criteria MS1 - The launch vehicle reaches the 5280 ft. target altitude within 100 ft. MS2 - The vehicle carries rover safely through flight and landing MS3 - The rover successfully deploys and travels 5 ft. from the landing site to deploy its solar panels ● Vehicle Success Criteria VS2 - The airframe must withstand the forces of takeoff, ascent, and landing VS4 - The vehicle must not cause any significant safety risk to onlookers or property VS5 - The team must be able to assemble the vehicle within 4 hours of reaching the launch site ● Recovery Success Criteria RS3 - All recovery systems must successfully deploy at set altitudes RS4 - The landing energy of all sections must be below 75 lbf-ft
● Housing Success Criteria PS1 - The rover housing successfully protects the rover through launch, separation, and landing PS2 - The ground team successfully transmits a signal to initiate deployment PS3 - The rover housing orients the rover within ±5° of a normal orientation PS4 - The leadscrew properly deploys the rover from the rover housing ● Rover Success Criteria PS5 - The rover autonomously travels a minimum distance of 5 ft. from the vehicle PS6 - The rover deploys its foldable solar panel array
● Team Structure ● Mission Success Criteria ● Vehicle (Section 3) ● Recovery ● Drag Module ● Payload - Rover ● Payload - Housing ● Testing Plan ● Safety ● Project Plan
Section Mass (lb) Upper Lower Loaded Length Un-Loaded CG CP Diameter Diameter Mass Booster 25.3 (in) Mass (lb) (in) (in) (in) (in) (lb) Recovery 6 96.5 6.16 5.13 39.3 49.3 56.93 72.15 Payload 18
LOADED CG/CP: Loaded: Unloaded:
● Performance Criteria per NASA SL Handbook Statement of Work ○ Maximum Impulse: 5120 Ns (L class) ○ Velocity Off Rail: 52 fps ● Motor choice: Aerotech L1500T ○ Impulse: 5089.3 Ns ○ Burn Time: 3.5 s ○ Max Thrust: 1752 N ○ Avg Thrust: 1500 N Thrust to Rail Velocity Max Altitude Max Velocity Max Acceleration Weight Ratio (fps) (ft) (fps) (G) 30 65 5877 643 7
Part Material Length (in) Diameter (in) Mass (lbm) Airframe Carbon Fiber Fins Polycarbonate 40.97 5 25.3 Boattail ULTEM 9085
Part Material Body ABS Length (in) Diameter (in) Mass (lbm) Flaps ABS 15 5 5 E-Bay ABS
Avionics bay Main parachute Drogue parachute BP charges Part Material Length (in) Diameter (in) Mass (lbm) Airframe Carbon Fiber Bulkheads Carbon Fiber 18.38 5 to 6 6 Avionics Bay ABS
10 ft. Main Housing E- Bay Parachute Rover Housing Avionics Part Material Airframe Fiberglass Length (in) Diameter (in) Mass (lbm) Nosecone ABS 36 6 18 Av. Bay ABS
● Carbon Fiber - Booster Airframe, Recovery Airframe, Fincan Motor tube, and Centering Rings ○ Highest strength to weight ratio ○ Rigid and durable for reusability ● Fiberglass - Payload Airframe, Drag Modulation Electronics Bay ○ High strength to weight ratio ○ Non-conductive to allow EM signals to pass ● 3D Printed Polycarbonate - Fincan Fins ○ Tighter print tolerance for precision geometry ○ High rigidity and fatigue allows for reusability ● 3D Printed ABS - Drag Modulation System, Nosecone, Electronic Bays ○ Less expensive and lighter than polycarbonate ○ Sufficient strength to withstand flight ● 3D Printed ULTEM 9085 - Boattail ○ High heat resistance
NASA Outlined Requirements Verification Item Requirement Verification Method Verification Plan 2.1 The vehicle will deliver the scientific Analysis The launch vehicle will reach the target payload to an apogee altitude of 5,280 altitude through a combination of motor ft. above ground level. selection, vehicle aerodynamics, drag modulation, and the overall mass. 2.6 The launch vehicle will be designed to Inspection Robust design, repackable parachutes, be recoverable and reusable. Reusable and replaceable fins on hand at launch is defined as being able to launch again site will ensure relaunch on same day. on the same day without repairs or modifications. 2.17 The launch vehicle will accelerate at a Analysis Simulation software will be utilized to minimum of 52 fps at rail exit. verify velocity at rail exit.
Team Derived Requirements Verification Item Requirement Verification Method Verification Plan 2.1 Weight Max: 60 lbm Analysis Use lightweight materials, and do not have any empty space. All onboard components will serve a required purpose. All components and material not considered necessary for flight will be removed. 2.4 Allow for EM to pass through necessary Analysis Purchase, and properly handle, materials on Launch Vehicle fiberglass material. 2.5 Do not allow for EM to pass through Analysis Purchase, and properly handle, carbon certain materials on Launch Vehicle fiber and metal components.
Subsystem Pre- /Compone Failure Mode Cause Effect Mitigation RAC nt Name Ensure licensed vendor for purchasing Fracture of motor casing or Catastrophic loss of vehicle at Motor CATO 1A of motors. Inspection of motor improper grain packing. take-off. assembly prior to use. Proper design such that boat tail is Ultem structural Excessive heat near boat Loss of motor retention. minimally exposed to exhaust. Inspect 1D failure. tail. Catastrophic mission failure. boattail before and after flight for Motor structural damage. retention Boat tail attachment Improper securing of boat Loss of motor retention. Inspect boattail for security and proper 1D failure tail to the vehicle Catastrophic mission failure. installation. Fracture of fin Excessive shear forces Drastically altered flight profile Inspect fins before and after flight for 1C during flight acting on the fin and loss vehicle stability structural damage Fins Fracture of fin upon Excessive shear forces Drastically altered flight profile Inspect fin and boattail assembly for 3A recovery acting on the fin and loss vehicle stability proper installation
● Team Structure ● Mission Success Criteria ● Vehicle ● Recovery (Section 3.2) ● Drag Module ● Payload - Rover ● Payload - Housing ● Testing Plan ● Safety ● Project Plan
1. Separation at apogee 2. Booster Drogue 3. Payload Main (reefed) after 2 second delay 4. Booster Main - 600 ft. 5. Payload Main - 300 ft. 6. Landing 7. Rover Deployment
Booster Section Drogue Parachute ● Manufacturer: Fruity Chutes ● Model: Iris Ultra Standard ● Diameter: 3 ft. ● Deployment: Apogee Booster Section Main Parachute ● Manufacturer: Fruity Chutes ● Model: Iris Ultra Standard ● Diameter: 10 ft. ● Deployment: 600 ft. Payload Main Parachute ● Manufacturer: Fruity Chutes ● Model: Iris Ultra Standard ● Diameter: 10 feet ● Deployment: Reefed at apogee, full at 300 ft.
1 2 3 ● Constricts the opening of the main parachute ● Uses closed main parachute as drogue ● Reefing ring slows opening to dampen opening forces ● Will open at 300 ft.
Booster: Payload: Wind Speed (mph) Payload Drift Distance (ft) Booster Drift Distance (ft) 0 0 0 5 1334 2028 10 2667 4056 15 4000 6083 20 5331 8111
Section Payload Main Booster Drogue Booster Main Estimated B.P. 3.5 6.7 7.1 Charge (g)
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