UAA Rocketry PDR Presentation NASA Student Launch

Launch Vehicle 1

Vehicle Dimensions ● Overall Length 77.7 inches ● Body tube diameter 4 inches and inch thickness 2

Vehicle Materials ● 4 inch 5:1 VonKarmen Filament wound nose cone ● Filament wound ProFusion body and coupler tubing 3

Vehicle Materials ● Fins and centering rings cut from inch structural fiberglass ● Motor tube made from wound G12 fiberglass tubing ● Bulkheads and payload compartment CNC cut from inch structural fiberglass 4

Vehicle Materials ● ¼”-20 stainless steel full threaded rods ● Grade-8 ¼ ”-20 Nylon- insert flanged locknuts ● 0.25 inch foged steel Eyebolts 5

Vehicle Materials ● Epoxies o West System 105 Epoxy Resin o Henkel Loctite o JB Weld 6

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 7

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 8

Motor Selection Preliminary Motor Selection: Aero Tech J415W 54 mm Diameter 326 mm Length 9

Justification for Selected Motor 10

Stability Analysis ● Center of Pressure: inches from nose ● Center of Gravity: inches from nose ● Static Stability Margin: 1.95 ● Thrust-to-Weight Ratio: 5.5:1 ● Rail Exit Velocity: 33.4 feet/second 11

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 12

Launch Pad Drawing 13

Launch Pad Discussion ● Launch rail is 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 14

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 15

Drouge Parachute System Drawing 16

Drogue Parachute Discussion ● Located between booster and central sections ● Parachute is a 2 foot Rocketman Parachute ● Tethered to rocket with ¼” Aramid rope 17

Deployment System Drawing 18

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 19

Payload Compartment Drawing 20

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 21

Main Parachute/Shock Cord Compartment Drawing 22

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 23

Recovery System Drawing 24

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: o Aft nose cone/payload section descend separately o Central and booster sections descend under drogue chute and main chute 25

Nose Cone Drawing/Discussion Image credit to performancehobbies.com [1] ● 4 inch 5:1 Von Karmen Filament Wound Nose Cone ● Connected to payload compartment 26

Tail Fin Drawing/Discussion ● Fins cut from inch structural fiberglass ● Delta-style shape ● Dimensions: o 12 inch root cord o 8 inch tip cord o 5 inch height o 2 inch sweep length 27

AGSE Overview Control – Spatial Constraints – Degrees of Freedom – Precision and accuracy Components – Base Structure – Arm – End Effector 28

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 29

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 30

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 31

End Effector Control – Spatial Constraints Of sufficient width to capture a 6” area – Precision and accuracy Closing pressure detection Orientation of capture 32

AGSE Integration and Testing 3D component models Assembly checks – QC Iterative testing at subsystem and system levels Sensor/program testing de-bugging 33

References [1]