Transcript UAA Rocketry

UAA Rocketry
PDR Presentation
NASA Student Launch 2014-2015
Launch Vehicle
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Vehicle Dimensions
● Overall Length 77.7 inches
● Body tube diameter 4 inches
and 0.0625 inch thickness
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Vehicle Materials
● 4 inch 5:1 VonKarmen
Filament wound nose cone
● Filament wound ProFusion
body and coupler tubing
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Vehicle Materials
● Fins and centering rings cut
from 0.1875 inch structural
fiberglass
● Motor tube made from wound
G12 fiberglass tubing
● Bulkheads and payload
compartment CNC cut from
0.125 inch structural fiberglass
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Vehicle Materials
● ¼”-20 stainless steel full
threaded rods
● Grade-8 ¼ ”-20 Nyloninsert flanged locknuts
● 0.25 inch foged steel
Eyebolts
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Vehicle Materials
● Epoxies
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West System 105 Epoxy Resin
Henkel Loctite
JB Weld
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Vehicle Justifications
● Conventional configuration: Nose cone/Payload Compartment,
Central Section, and Booster Section
● Aft Nose Cone/Payload section serves as payload ejection mechanism
● Dual deployment; drogue and payload ejections simultaneous to
simplify design
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Safety Testing Plans
● AGSE components will be constructed with ample time left to
thoroughly test system safety, effectiveness, and consistency
● Extensive ground testing performed to ensure ejection
charges perform deployment operations safely and
consistently
● Subscale and full-scale launch vehicles will be test launched
early and often at Alaska Northstar (NAR) launch events
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Motor Selection
Preliminary Motor Selection:
Aero Tech J415W
54 mm Diameter
326 mm Length
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Justification for Selected Motor
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Stability Analysis
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Center of Pressure: 59.28 inches from nose
Center of Gravity: 51.42 inches from nose
Static Stability Margin: 1.95
Thrust-to-Weight Ratio: 5.5:1
Rail Exit Velocity: 33.4 feet/second
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Test Plan Overview
● AGSE components to be constructed and tested at UAA Design Studio
● Ejection Charges to be tested outdoors adjacent to Design Studio
● Subscale and full scale launch events at Lake Louise and Big Lake
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Launch Pad Drawing
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Launch Pad Discussion
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Launch rail is 8020-1530 Aluminum extrusion 180 inches in length
Feet are adjustable to level the apparatus
Declination of launch rail is calibrated to 5 degrees from vertical
Blast pad safely deflects exhaust gases away from grass
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Motor Compartment Dimensions/Discussion
● 54 millimeters in diameter and 13 inches in length to accommodate J
sized motor
● Motor compartment is G12 wound fiberglass made by ProLine
Rocketry Inc.
● Compartment is bonded to centering rings using JB Weld
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Drouge Parachute System Drawing
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Drogue Parachute Discussion
● Located between booster and central sections
● Parachute is a 2 foot Rocketman Parachute
● Tethered to rocket with ¼” Aramid rope
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Deployment System Drawing
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Deployment System Discussion
● Entire aft section will deploy simultaneously with main chute at 1000
feet AGL
● Aft section will descend under a 3 foot Rocketman Parachute
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Payload Compartment Drawing
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Payload Compartment Discussion
● Payload compartment is CNC cut from 0.125” structural fiberglass,
bonded with West Systems Epoxy
● Hatch is actuated by two servos at opposite ends of the compartment
● Over-center geometry of hatch respective to servo motor prevents
hatch from opening
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Main Parachute/Shock Cord Compartment
Drawing
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Main Chute Discussion
● The main chute will deploy at 1000 feet AGL
● Chute is a 60 inch Iris Ultra Parachute made by Fruit
Chutes
● Parachute is sized to allow central and booster
sections to descend with kinetic energy ≤ 75 ft-lbf
● Chutes and rocket sections tethered with ¼ inch
Aramid Rope
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Recovery System Drawing
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Recovery System Discussion
● First ejection charge at apogee; booster section and central section
separate to deploy drogue chute
● Second and third ejection charges at 1000 feet AGL:
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Aft nose cone/payload section descend separately
Central and booster sections descend under drogue chute and main chute
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Nose Cone Drawing/Discussion
● 4 inch 5:1 Von Karmen
Filament Wound Nose Cone
● Connected to payload
compartment
Image credit to performancehobbies.com [1]
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Tail Fin Drawing/Discussion
● Fins cut from 0.1875
inch structural fiberglass
● Delta-style shape
● Dimensions:
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12 inch root cord
8 inch tip cord
5 inch height
2 inch sweep length
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AGSE Overview
• Control
– Spatial Constraints
– Degrees of Freedom
– Precision and accuracy
• Components
– Base Structure
– Arm
– End Effector
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Base Structure
• Control Overview
– Spatial Constraints
• Retain rocket during
payload insertion
– fixed dimensional
relationship
– Precision and accuracy
• Primary mounting point
for the arm structure
• Contains all electronics
and power systems
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Arm
• Control Overview
– Spatial Constraints
•
Of sufficient height to
remain clear of Launch
Vehicle
– 1 degrees of freedom
• Boom: Rotation – Yaw
– Precision and accuracy
• Position
switches/sensors
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Linear Motion System
• Control
– Spatial Constraints
• Of sufficient length to
clear the base station
• Of sufficient length to
reach the ground
– 1 Degree of Freedom
• LMS: Translation - Heave
– Precision and accuracy
• Ground sensing
capability
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End Effector
• Control
– Spatial Constraints
• Of sufficient width to
capture a 6” area
– Precision and accuracy
• Closing pressure
detection
• Orientation of capture
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AGSE Integration and Testing
• 3D component models
• Assembly checks – QC
• Iterative testing at subsystem and system
levels
• Sensor/program testing de-bugging
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References
[1]https://www.performancehobbies.com/secure/store.aspx?groupid=
31820148555848
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