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UAA Rocketry. PDR Presentation NASA Student Launch 2014-2015. Launch Vehicle. 1. Vehicle Dimensions. Overall Length 77.7 inches Body tube diameter 4 inches and 0.0625 inch thickness. 2. Vehicle Materials. 4 inch 5:1 VonKarmen Filament wound nose cone

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Uaa rocketry

UAA Rocketry

PDR Presentation

NASA Student Launch 2014-2015


Launch vehicle

Launch Vehicle

1


Vehicle dimensions

Vehicle Dimensions

  • Overall Length 77.7 inches

  • Body tube diameter 4 inches and 0.0625 inch thickness

2


Vehicle materials

Vehicle Materials

  • 4 inch 5:1 VonKarmen Filament wound nose cone

  • Filament wound ProFusion body and coupler tubing

3


Vehicle materials1

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

4


Vehicle materials2

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 materials3

Vehicle Materials

  • Epoxies

    • West System 105 Epoxy Resin

    • Henkel Loctite

    • JB Weld

6


Vehicle justifications

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

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

Motor Selection

Preliminary Motor Selection:

Aero Tech J415W

54 mm Diameter

326 mm Length

9


Justification for selected motor

Justification for Selected Motor

10


Stability analysis

Stability Analysis

  • 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

11


Test plan overview

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

Launch Pad Drawing

13


Launch pad discussion

Launch Pad Discussion

  • 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

14


Motor compartment dimensions discussion

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

Drouge Parachute System Drawing

16


Drogue parachute discussion

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

Deployment System Drawing

18


Deployment system discussion

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

Payload Compartment Drawing

20


Payload compartment discussion

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

Main Parachute/Shock Cord Compartment Drawing

22


Main chute discussion

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

Recovery System Drawing

24


Recovery system discussion

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:

    • Aft nose cone/payload section descend separately

    • Central and booster sections descend under drogue chute and main chute

25


Nose cone drawing discussion

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

Tail Fin Drawing/Discussion

  • Fins cut from 0.1875 inch structural fiberglass

  • Delta-style shape

  • Dimensions:

    • 12 inch root cord

    • 8 inch tip cord

    • 5 inch height

    • 2 inch sweep length

27


Agse overview

AGSE Overview

  • Control

    • Spatial Constraints

    • Degrees of Freedom

    • Precision and accuracy

  • Components

    • Base Structure

    • Arm

    • End Effector

28


Base structure

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


Uaa rocketry

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

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

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

AGSE Integration and Testing

  • 3D component models

  • Assembly checks – QC

  • Iterative testing at subsystem and system levels

  • Sensor/program testing de-bugging

33


References

References

[1]https://www.performancehobbies.com/secure/store.aspx?groupid= 31820148555848

34


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