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

2. 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
Reusable Rocket Vehicle Proposed: “Gunrocket”
Team Faculty Advisor: Dr. Nesrin Sarigul-Klijn
Launch Assistance/Mentor:
Cliff Sojourner
done

3. 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

4. VEHICLE SUMMARY
done

5. 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

6. COMPONENT LAYOUT
Done

7. 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?

8. 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

9. Vehicle Structure
done

10. 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:

11. 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

12. MOTOR SELECTION AND PROPULSION SYSTEM
done

13. 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

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

15. Baseline Payload Design
done

16. 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

17. 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

18. 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

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

20. Verification Plan and Test Plan Overview
done

21. 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

22. Mission Performance and Predictions
done

23. Altitude and Velocity
done

24. 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

25. 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

26. 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

27. Thank You!
DONNEEEEEEE!!!