NASA USLI Preliminary Design Review University of California, Davis Eclipse Rocketry 2016-2017 Presented by: Matt Huang Andrew Chuen Janine Moses Daniel Torrecampo Andy Trang done

SCHOOL INFORMATION Name of school/organization: UC Davis – Eclipse Rocketry Team Mailing Address: Attn: Nesrin Sarigul-Klijn Professor and Director of SpaceED Mechanical and Aerospace Engineering Department 2132 Bainer Drive Davis, CA 95616-5294 Reusable Rocket Vehicle Proposed: “Gunrocket” Team Faculty Advisor: Dr. Nesrin Sarigul-Klijn Launch Assistance/Mentor: Cliff Sojourner - 82864 408.234.9281 done

OVERVIEW School Information Vehicle Summary and Mass Budget Vehicle Design - In Depth Motor Selection Payload Design - In Depth Verification Plan and Testing Mission Performance and Predictions Safety Plan and Verification Compliance Matrix done

VEHICLE SUMMARY done

VEHICLE SUMMARY Length: 109’’ Diameter: 6.15’’ Nose Cone: Ogive shape, 20’’ long, 6.1’’ base diameter Airframe 1: 22’’ Avionics Bay: 12’’ Airframe 2: 18’’ Payload Frame: 18’’ Airframe 30”: Motor: Aerotech L1390G-P Total Mass (with motor): 32.2 lbs done

COMPONENT LAYOUT Done

STATIC STABILITY MARGIN Static Stability Margin, Dry Mass: 3.81 Static Stability Margin, with Motor: 2.23 done Goal: recoverable launch vehicle to be retrievable Static stability margin between 1 and 3. follow advice for modern rocketry Rocketry handbooks longitudinal stability If the CG of the launch vehicle is forward of the center of pressure, the vehicle will respond to a disturbance by producing an aerodynamic moment that returns the angle of attack of the vehicle towards the angle that existed prior to the disturbance. If CG of the launch vehicle is behind the center of pressure, the vehicle will respond to a disturbance by producing an aerodynamic moment that continues to drive the angle of attack of the vehicle further away from the starting position. How did we get to it?

Mass Budget Weight (oz.) 50.25 44.66 47.53 140.4 13.4 91.39 5 81 Component Weight (oz.) Nose Cone 50.25 Airframe 1 44.66 Airframe 2 47.53 Airframe 3 140.4 Main Parachute 13.4 Avionics Bay 91.39 Drogue Chute 5 Payload Experiments 81 Component Weight (ox.) Motor Bay 29.9 Motor 137.6 Static Fins 59.5 Roll Fins 2.56 Total Dry Mass (no motor) 341.7 Total Mass with Motor 479.3 done

Vehicle Structure done

Vehicle Structures External Structures Internal Structures Fuselage: Nose cone, Fins, Airframe Internal Structures Bulkheads Couplers Material choice G10 - Fiberglass Phenolic Manufacturer Public Missiles Ltd. Done Goal:

Recovery System Dual Deployment Drogue: Fruity Chutes Classic Elliptical 18" Standard Parachute Main: Fruity Chutes Iris Ultra 84" Compact Parachute Ejection Method: Blackpowder w/ electronic igniter Altimeter: StratoLoggerCF Tracking Device: ArduPilot + GPS attachment done goal: fulfill requirement to have the launch vehicle recoverable and repeatable selecting dual deployment rather than the tumble recovery or streamer recovery impulse and amount of Gs that rocket experiences “report the official competition altitude via a series of beeps “ location heading altitude

MOTOR SELECTION AND PROPULSION SYSTEM done

Motor Selection Must propel rocket to at least 5280 ft AGL. Aerotech L1390G-P Motor-thrust curve from ThustCurve.org done REACH 5280ft AGL additional growth weight more margin for g brakes to operate more easily accessible motors to obtain in california motor choice limitation

Motor Specifics Diameter 2.95 inches Length 20.4 inches Propellant Mass 4.35 lbs Total Mass 8.55 lbs Average Thrust 1375.0 N Peak Thrust 1649.8 N Total Impulse 3946.5 N*s Rail Exit Velocity 67.5 ft/s Thrust-to-Weight Ratio 3.44 Thrust Duration 2.9 s done

Baseline Payload Design done

Payload: Roll Control Experiment Structures Fin actuation Linkage arm assembly Trapezoidal fins Base plate mount Boarding component storage Main payload bus structure understand how liquid slosh behaves in micro gravity change in CG surface velocity cavitiation resonance self excitation fixturing configuration/placement of subsystems slosh tank material manufacturing video equipment changes since proposal

Payload: Roll Control Experiment Controls Microcontroller: Arduino 101 Operations split to two separate boards Guidance navigation control Servo controller Servo: HITEC HSB-9380TH Servo DONEEEEE understand how liquid slosh behaves in micro gravity change in CG surface velocity cavitiation resonance self excitation fixturing configuration/placement of subsystems slosh tank material manufacturing video equipment changes since proposal

Payload: Roll Control Experiment Sensors Measure acceleration and rotational velocity BMI 160 IMU (embedded in Arduino 101 Intel Curie module) Correction with Kalman filters understand how liquid slosh behaves in micro gravity change in CG surface velocity cavitiation resonance self excitation fixturing configuration/placement of subsystems slosh tank material manufacturing video equipment changes since proposal

Payload: Roll Control Experiment Vehicle Integration Through-wall bolt system External structure consists of payload fairing Fairing attaches through coupler mates

Verification Plan and Test Plan Overview done

Recovery System Altimeter Ejection charges Tracking system Barometric testing Ejection charges Shear pins Black powder mass Tracking system Distance and location testing and verification done

Mission Performance and Predictions done

Altitude and Velocity done

Kinetic Energy (ft*lb) Drift & Kinetic Energy Tailwind (miles/hr) Lateral Drift (ft) Kinetic Energy (ft*lb) 3.69 64.86 5 547.81 65.82 10 577.5 60.14 20 1473.5 60.05 done Wind Drift Accuracy Issues -discrepancies with commonly expected results -test-launch verification of simulated flight data -past simulated flight data and actual flight data Kinetic Energies -meet requirements for all wind speeds

Compliance Matrix Requirement Completed Design Feature Requirement Rocket must reach apogee of 5280 ft. AGL, and cannot exceed 5600 ft. AGL Yes Rocket motor choice Rocket must be recoverable and reusable Recovery system/Vehicle Design Rocket can only use commercial, NAR/TRA certified solid motor propulsion system Motor choice Rocket motor cannot exceed total impulse of 5120Ns Includes Payload Payload design

Requirement Completed Design Feature Requirement Deployment of recovery devices must be staged. Dual deployment must be used. Yes Recovery system Each independent section must land with a maximum Kinetic Energy of 75ft*lbf Recovery system/Overall rocket design Only Electronic recovery system must be completely independent of payload circuits Recovery System Drogue and main parachutes must be deployed with removable shear pins Rocket and payload can only cost a maximum of $7500 as it sits on launch pad. Overall rocket design and component choice

Thank You! DONNEEEEEEE!!!