Preliminary Design Review Eclipse Rocketry at University of - - PowerPoint PPT Presentation
NASA USLI Preliminary Design Review Eclipse Rocketry at University of California, Davis 2017-2018 Presented By: Janine Moses Andy Trang Eden Tessema Alysia Iglesias Duarte Lucas OVERVIEW School Information Vehicle Summary and Mass
Presented By: Janine Moses Andy Trang Eden Tessema Alysia Iglesias Duarte Lucas
Attn: Nesrin Sarigul-Klijn Professor and Director of SpaceED Mechanical and Aerospace Engineering Department 2132 Bainer Drive Davis, CA 95616-5294
Cliff Sojourner - 82864 408.234.9281
Length: 98’’ Diameter (excluding camera fairings): 6.142’’ Motor: Aerotech L1150-P Total Mass (with motor): 29.38 lbs Material: G10 Fiberglass Airframe, plywood bulkheads, other electronic parts Payload: Target Acquisition, Recognition, and Processing System (TARPS)
C.G: 65.381” from nose C.P: 77.87” from nose Static Stability Margin, Dry Mass: 3.34 caliber Static Stability Margin, with Motor: 2.03 caliber
Thrust to Weight Ratio: 8.78 Rail Exit Velocity: 67.1 ft/s
Component Weight (lb.) Nose Cone
4.01
Airframe 1
1.59
Main Parachute
0.8375
Avionics Bay
1.175
Airframe 2
2.06
Drogue Chute
0.313
Component Weight (lb) Payload Experiment
2.5
Airframe 3
7.04
Motor
8.13
Static Fins
2.5
Total Dry Mass (no motor)
21.23
Total Mass with Motor
29.36
○ Fuselage: Nose cone, Fins, Airframe
○ Bulkheads ○ Couplers
○ G10 - Fiberglass ○ Phenolic
○ Public Missiles Ltd.
3 during flight.
and bolted to airframe 3 (purple) and attached to airframe 2 (green) with shear pins.
deployment from black powder charges as well as rocket launch vibrations/flight loads.
○
Drogue: Fruity Chutes Classic Elliptical 18" Standard Parachute
○
Main: Fruity Chutes Iris Ultra 84" Compact Parachute
www.fruitychutes.com
○ Barometric testing
○ Shear pins ○ Black powder mass
○ Distance and location testing and verification
5280 ft AGL.
○ L1150-P
ThustCurve.org
Diameter 2.95 inches Length 20.9 inches Propellant Mass 4.58 lbs Total Mass 8.125 lbs Average Thrust 258.1 lbf Peak Thrust 294.5 Ib Total Impulse 784.4 Ib*s Rail Exit Velocity 67.1 ft/s Thrust-to-Weight Ratio 8.78 Thrust Duration 3.04 s
Tailwind (miles/hr) Lateral Drift (ft) Kinetic Energy (ft*lbf) 163.83 43.39 5 594.72 42.45 10 860.03 38.82 15 1318.9 39.33 20 1748.6 39.07
Overview
○ USLI ○ Self-derived
○ Camera fairings
Processing System
○ Camera ○ Microprocessor and Sensors ○ Power source
○ Image processing ○ Automation ○ Data verification (tarp color differentiation)
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 Yes Recovery system/Vehicle Design Rocket can only use commercial, NAR/TRA certified solid motor propulsion system Yes Motor choice Rocket motor cannot exceed total impulse of 5120 Ns Yes Motor choice Includes Payload Yes 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 Yes Recovery system/Overall rocket design Only Electronic recovery system must be completely independent of payload circuits Yes Recovery System Drogue and main parachutes must be deployed with removable shear pins Yes Recovery System Rocket and payload can only cost a maximum of $7500 as it sits on launch pad. Yes Overall rocket design and component choice