PRELIMINARY DESIGN REVIEW
|
|
|
- Lillian West
- 5 years ago
- Views:
Transcription
1 PRELIMINARY DESIGN REVIEW
2 1 1 Team Structure - Team Leader: Michael Blackwood NAR #101098L2 Certified - Safety Officer: Jay Nagy - Team Mentor: Art Upton NAR #26255L3 Certified - NAR Section: Jackson Model Rocketry Club Section #620 Team Leadership: - Michael Team Lead, Payload System Lead - Connor Payload Hardware Lead - Andrew Vehicle Body Lead, Treasurer - Peter Propulsion Lead - Jay Safety Officer - Patrick Recovery Lead - Marwan Payload Electronics Lead - William Education/Outreach Lead
3 Slide 2 1 This is a very simple section someone can take if they dont know a whole bunch Andrew Loch, 11/7/ dibs lol William Frey, 11/7/2016
4 Vehicle Dimensions Length (in) Outer Diameter (in) Inner Diameter (in) Nose cone (1) Main Parachute Bay (2) Recovery Bay (3) Drag Chute Bay (4) Payload Bay (5) Motor Mount (6) Nose cone Shape: Ogive
5 Fin Dimensions (Nard Fins) Number of Fins: 4 (1) Root Chord: 3.50 in (2) Tip Chord: 1.25 in (3) Height: 2.00 in (4) Sweep Length: 2.30 in Thickness: 0.25 in ϴ 1 (ϴ) Sweep Angle: 49
6 Slide 4 2 I can take this section too but I think it'd be better if someone else did this, not too challenging Andrew Loch, 11/7/ I can do this slide Nathan Riethman, 11/7/2016
7 Fin Dimensions (Main) in in in
8 Materials 3 1 Part Nose Cone Body Tubing & Motor Mount Fins (Nards & Main) Motor Retention Fin Fillets Glue Material Plastic Fiberglass Fiberglass Metal (Steel) JB Weld 2 Ton Epoxy Fiberglass was chosen due to its high strength to weight ratio. It will provide the best stability for the rocket without becoming too heavy. Plastic was chosen for the Nose Cone as it would allow a commercially made nose cone to be purchased and to reduce weight. Steel was chosen for the motor retention for a reliable, heat resistant retention that can be used multiple times. JB Weld will be used for the fin fillets because of its rigidity when fully cured and its superior bonding strength. 2-Ton Epoxy will be used as it will provide adequate strength bonding without excess weight.
9 Slide 6 3 Also a pretty easy section, basically just reading the slide adn adding a few extra words in. Andrew Loch, 11/7/ I can do this section. Kevin Bruns, 11/7/2016
10 Stability Margins (With Motor) 4 CG CP Stability Margin: Center of Gravity: Center of Pressure: 1.86 Cal in in Motor Used: Aerotech K480W
11 Slide 7 4 Here we need to explain how we want to improve our stability margin and move our CG higher up while keeping the CP low. Andrew Loch, 11/7/2016
12 Stability Margins (Without Motor) 5 CG CP Stability Margin: Center of Gravity: 3.22 Cal in Center of Pressure: in No Change
13 Slide 8 5 Maybe make references to the previous slide and say again how we want to improve the stability margin. Andrew Loch, 11/7/2016
14 Preliminary Motor Selections Primary Motor Selection: Aerotech K480W Will Reach and exceed the target height (~400 ft over) Built in weight adjustment Easier to add weight than to take away Provides Wiggle room for adjustment and weather Built in buffer against motor underperformance 54mm motor mount required Secondary Motor Selection: Aerotech K700W Will Reach and exceed the target height (~300 ft over) Built in weight adjustment Easier to add weight than to take away ***To be used if less weight is added than planned*** Provides Wiggle room for adjustment and weather Built in buffer against motor underperformance 54mm motor mount required
15 Thrust vs. Weight Ratio & Rail Exit Velocity 6 K480W Thrust vs. Weight Ratio: Max. Thrust: 916 N Max. Weight: 16.6 lb = 7.53kg Gravity: 9.81m/s T vs W Ratio = K700W Thrust vs. Weight Ratio: Max. Thrust: 1029 N Max. Weight: 16.5 lb = 7.48kg Gravity: 9.81m/s T vs W Ratio = K480W Rail Exit Velocity: 65.6 ft/sec Rail Length: 72in K700W Rail Exit Velocity: 70.8 ft/sec Rail Length: 72in
16 Slide 10 6 Here you want to compare the two motors we are thinking about using and just compare contrast the exit velocities and mention how regardless of the motor, we need a 72 inch rail. Andrew Loch, 11/7/2016
17 Motor Mount Overview 7 2 Length: in OD: in ID: in Mounted to bulkhead at the bottom of the electronics bay
18 Slide 11 7 Say how our mount will be made of fiberglass, is for 54mm motors, and can hold both of our motors we are debating on using. Andrew Loch, 11/7/ I can do this slide Nathan Riethman, 11/7/2016
19 Recovery Overview Drogue Chute Recovery Bay (Altimeter & Ejection Charge Housing) Main Chute Drogue Chute: 12 Deploys at apogee Main Chute: 72 Deploys at 700ft Altimeter StratologerCF Programmed to trigger blast caps at apogee for drogue and 700 ft for main. Two units Each unit given independent battery Each unit connects to a blast cap for the drogue and main chutes. 2 grams of black powder are used for each blast cap.
20 8 Recovery Overview (Cont.) TeleGPS unit MHz Ham Band Interfaces with ground station to output altitude, velocity, and GPS location Kinetic Energy at Impact Velocity: 22.4 ft/s Maximum permissible Energy is 75 ft-lbf Nylon Rip Stop Shock Cords Nomex Fire Resistant Blankets Kinetic Energy of Each Section (Ftlbs) Nose Section Forward Section Aft Section
21 Slide 13 8 Mention how we are using the same GPS as last year so we are familiar with it, and our kinetic energy values are a-okay. Andrew Loch, 11/7/2016
22 Payload Overview The payload will consist of an active surface controlling the roll of the rocket during flight. Single Servo controlling a differential (Figure 1) All four (4) control surfaces will move in sync Control surfaces will be connected via a rod system which will secure using flush screws (Figure 2) Breakdown of Payload System Colors (Figure 3) Green Spacer to guide threader rods and provide support between servo and differential bulkheads. Blue Top support of PCB Yellow Bottom support of PCB Red Holds battery components Electronics Reads and stores sensor data Directs control loop 3 1 2
23 Slide 14 1 I can take this I am currently planning on doing the sections I am officially lead on but could add this as well. Depends on how it distributes, would rather not have 4 slides in a row. Marwan Mohamed, 11/7/ Just someone who knows exactly what they are talking about need to take this, go very in depth here. Andrew Loch, 11/7/ If you want, I can take this. If you can just tell me what parts to emphasize. Nathan McFarland, 11/7/2016
24 10 Payload Hardware 4 Way Pinion Differential Connects servo to control surfaces 2:1 Gear Ratio Bevelled gears Single HV 40 Kg-cm Servo Motor Found using Calculations in Matlab Equations obtained from OpenRocket Technical Documentation Shows Torque over a range of deflection angles Exceeds factor of safety of 2 Metal gears 2X Threaded Rod Runs Through Payload Keeps payload bay in compressions Compresses 3D printed components PCB, Battery, Servo Contained in 3D Printed Parts Control Fins 3D Printed Support Fins use Standard Rocket Fin Construction Carbon fiber internal fillets Fumed silica external fillets
25 Slide Similar as last slide, just go very in depth. Andrew Loch, 11/7/2016
26 11 2 Payload Electronics ATmega32u4 Running Sparkfun Bootloader Compatibility with Arduino IDE Can create and test program on standard Arduino devices MPU-9250 IMU, Accelerometer, Gyroscope, Magnetometer 9 degrees of freedom Will be used to monitor roll state of rocket Micro SD Data Logging in SPI Mode External storage to record roll of rocket Quick and simple to pass to computer HV ( V Direct) 40kg-cm Servo Motor 7.4V 2S 1500mAh Lipo Battery (Servo) ~1.5 Hour Logic Battery (9V) Life Will last through the entire launch including pad time Exclusively for Microcontroller and sensor suite
27 Slide Someone else knows knows wayyyy more about this than I do. Andrew Loch, 11/7/ See Comments section Marwan Mohamed, 11/7/2016
28 Payload Control Microcontroller Reads data from MPU9250 Uses PID loop to determine Servo position to output Saves data to SD card. Servo Control Servo will only run when sufficient power is applied Before burnout servo holds 0 position Servo will move a maximum of 10 during control Disabled after apogee
29 Requirement Compliance Plan 3 Follow the NAR official guidelines for proper flight preparation, launch, and recovery. Follow the guidelines set forth by the team Safety officer. Verify that all required operations fall within safe operating limits (as determined by safety officer and build conventions)
30 Slide 18 3 I can do this slide as well (this would be my 3rd) Nathan Riethman, 11/7/2016
31 Questions?
CRITICAL DESIGN PRESENTATION
CRITICAL DESIGN PRESENTATION UNIVERSITY OF SOUTH ALABAMA LAUNCH SOCIETY BILL BROWN, BEECHER FAUST, ROCKWELL GARRIDO, CARSON SCHAFF, MICHAEL WIESNETH, MATTHEW WOJCIECHOWSKI ADVISOR: CARLOS MONTALVO MENTOR:
Critical Design Review
Critical Design Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1 Overview Illinois Space Society 2 Launch Vehicle Summary Javier Brown Illinois Space
Illinois Space Society Flight Readiness Review. University of Illinois Urbana-Champaign NASA Student Launch March 30, 2016
Illinois Space Society Flight Readiness Review University of Illinois Urbana-Champaign NASA Student Launch 2015-2016 March 30, 2016 Team Managers Project Manager: Ian Charter Structures and Recovery Manager:
Jordan High School Rocketry Team. A Roll Stabilized Video Platform and Inflatable Location Device
Jordan High School Rocketry Team A Roll Stabilized Video Platform and Inflatable Location Device Mission Success Criteria No damage done to any person or property. The recovery system deploys as expected.
FLIGHT READINESS REVIEW TEAM OPTICS
FLIGHT READINESS REVIEW TEAM OPTICS LAUNCH VEHICLE AND PAYLOAD DESIGN AND DIMENSIONS Vehicle Diameter 4 Upper Airframe Length 40 Lower Airframe Length 46 Coupler Band Length 1.5 Coupler Length 12 Nose
Auburn University. Project Wall-Eagle FRR
Auburn University Project Wall-Eagle FRR Rocket Design Rocket Model Mass Estimates Booster Section Mass(lb.) Estimated Upper Section Mass(lb.) Actual Component Mass(lb.) Estimated Mass(lb.) Actual Component
Team Air Mail Preliminary Design Review
Team Air Mail Preliminary Design Review 2014-2015 Space Grant Midwest High-Power Rocket Competition UAH Space Hardware Club Huntsville, AL Top: Will Hill, Davis Hunter, Beth Dutour, Bradley Henderson,
NUMAV. AIAA at Northeastern University
NUMAV AIAA at Northeastern University Team Officials Andrew Buggee, President, Northeastern AIAA chapter Dr. Andrew Goldstone, Faculty Advisor John Hume, Safety Officer Rob DeHate, Team Mentor Team Roster
NASA SL - NU FRONTIERS. PDR presentation to the NASA Student Launch Review Panel
NASA SL - NU FRONTIERS PDR presentation to the NASA Student Launch Review Panel 1 Agenda Launch Vehicle Overview Nose Cone Section Payload Section Lower Avionic Bay Section Booster Section Motor Selection
The University of Toledo
The University of Toledo Project Kronos Preliminary Design Review 11/03/2017 University of Toledo UT Rocketry Club 2801 W Bancroft St. MS 105 Toledo, OH 43606 Contents 1 Summary of Proposal... 6 1.1 Team
Preliminary Design Review. California State University, Long Beach USLI November 13th, 2017
Preliminary Design Review California State University, Long Beach USLI November 13th, 2017 System Overview Launch Vehicle Dimensions Total Length 108in Airframe OD 6.17in. ID 6.00in. Couplers OD 5.998in.
Preliminary Design Review. Cyclone Student Launch Initiative
Preliminary Design Review Cyclone Student Launch Initiative Overview Team Overview Mission Statement Vehicle Overview Avionics Overview Safety Overview Payload Overview Requirements Compliance Plan Team
Flight Readiness Review
Flight Readiness Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1 Overview Illinois Space Society 2 Launch Vehicle Summary Javier Brown Illinois
CRITICAL DESIGN REVIEW. University of South Florida Society of Aeronautics and Rocketry
CRITICAL DESIGN REVIEW University of South Florida Society of Aeronautics and Rocketry 2017-2018 AGENDA 1. Launch Vehicle 2. Recovery 3. Testing 4. Subscale Vehicle 5. Payload 6. Educational Outreach 7.
Auburn University Student Launch. PDR Presentation November 16, 2015
Auburn University Student Launch PDR Presentation November 16, 2015 Project Aquila Vehicle Dimensions Total Length of 69.125 inches Inner Diameter of 5 inches Outer Diameter of 5.25 inches Estimated mass
The University of Toledo
The University of Toledo Project Cairo Preliminary Design Review 10/08/2016 University of Toledo UT Rocketry Club 2801 W Bancroft St. MS 105 Toledo, OH 43606 Contents 1 Summary of Preliminary Design Review...
Presentation Outline. # Title # Title
CDR Presentation 1 Presentation Outline # Title # Title 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 Team Introduction Vehicle Overview Vehicle Dimensions Upper Body Section Payload
NASA SL Critical Design Review
NASA SL Critical Design Review University of Alabama in Huntsville 1 LAUNCH VEHICLE 2 Vehicle Summary Launch Vehicle Dimensions Fairing Diameter: 6 in. Body Tube Diameter: 4 in. Mass at lift off: 43.8
Presentation Outline. # Title
FRR Presentation 1 Presentation Outline # Title 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 Team Introduction Mission Summary Vehicle Overview Vehicle Dimensions Upper Body Section Elliptical
Project NOVA
Project NOVA 2017-2018 Our Mission Design a Rocket Capable of: Apogee of 5280 ft Deploying an autonomous Rover Vehicle REILLY B. Vehicle Dimensions Total Length of 108 inches Inner Diameter of 6 inches
Wichita State Launch Project K.I.S.S.
Wichita State Launch Project K.I.S.S. Benjamin Russell Jublain Wohler Mohamed Moustafa Tarun Bandemagala Outline 1. 2. 3. 4. 5. 6. 7. Introduction Vehicle Overview Mission Predictions Payload Design Requirement
NASA USLI PRELIMINARY DESIGN REVIEW. University of California, Davis SpaceED Rockets Team
NASA USLI 2012-13 PRELIMINARY DESIGN REVIEW University of California, Davis SpaceED Rockets Team OUTLINE School Information Launch Vehicle Summary Motor Selection Mission Performance and Predictions Structures
Georgia Tech NASA Critical Design Review Teleconference Presented By: Georgia Tech Team ARES
Georgia Tech NASA Critical Design Review Teleconference Presented By: Georgia Tech Team ARES 1 Agenda 1. Team Overview (1 Min) 2. 3. 4. 5. 6. 7. Changes Since Proposal (1 Min) Educational Outreach (1 Min)
Tacho Lycos 2017 NASA Student Launch Flight Readiness Review
Tacho Lycos 2017 NASA Student Launch Flight Readiness Review High-Powered Rocketry Team 911 Oval Drive Raleigh NC, 27695 March 6, 2017 Table of Contents Table of Figures... 9 Table of Appendices... 11
GIT LIT NASA STUDENT LAUNCH PRELIMINARY DESIGN REVIEW NOVEMBER 13TH, 2017
GIT LIT 07-08 NASA STUDENT LAUNCH PRELIMINARY DESIGN REVIEW NOVEMBER TH, 07 AGENDA. Team Overview (5 Min). Educational Outreach ( Min). Safety ( Min) 4. Project Budget ( Min) 5. Launch Vehicle (0 min)
Notre Dame Rocketry Team. Flight Readiness Review March 8, :00 PM CST
Notre Dame Rocketry Team Flight Readiness Review March 8, 2018 2:00 PM CST Contents Overview Vehicle Design Recovery Subsystem Experimental Payloads Deployable Rover Payload Air Braking System Safety and
UC Berkeley Space Technologies and Rocketry Preliminary Design Review Presentation. Access Control: CalSTAR Public Access
UC Berkeley Space Technologies and Rocketry Preliminary Design Review Presentation Access Control: CalSTAR Public Access Agenda Airframe Propulsion Payload Recovery Safety Outreach Project Plan Airframe
Pre-Flight Checklist for SLIPSTICK III
Advanced Planning 1 Schedule a Check that waivers are available at the intended launch site and date. b Check weather forecast for wind and temperature conditions at the site. c Have TAP members approved
Tripoli Rocketry Association Level 3 Certification Attempt
Tripoli Rocketry Association Level 3 Certification Attempt Kevin O Classen 1101 Dutton Brook Road Goshen, VT 05733 (802) 247-4205 kevin@back2bed.com Doctor Fill Doctor Fill General Specifications Airframe:
NASA USLI Flight Readiness Review (FRR) Rensselaer Rocket Society (RRS)
2016-2017 NASA USLI Flight Readiness Review (FRR) Rensselaer Rocket Society (RRS) Rensselaer Polytechnic Institute 110 8th St Troy, NY 12180 Project Name: Andromeda Task 3.3: Roll Induction and Counter
Pegasus II. Tripoli Level 3 Project Documentation. Brian Wheeler
Pegasus II Tripoli Level 3 Project Documentation Brian Wheeler Contents: A. Design Overview B. Booster Construction C. Electronics Bay (Mechanical) Construction D. Nose Cone Construction E. Recovery System
University Student Launch Initiative
University Student Launch Initiative HARDING UNIVERSITY Flight Readiness Review March 31, 2008 Launch Vehicle Summary Size: 97.7 (2.5 meters long), 3.1 diameter Motor: Contrail Rockets 54mm J-234 Recovery
NASA SL Flight Readiness Review
NASA SL Flight Readiness Review University of Alabama in Huntsville 1 LAUNCH VEHICLE 2 Vehicle Overview Vehicle Dimensions Diameter: 6 fairing/4 aft Length: 106 inches Wet Mass: 41.1 lbs. Center of Pressure:
PROJECT AQUILA 211 ENGINEERING DRIVE AUBURN, AL POST LAUNCH ASSESSMENT REVIEW
PROJECT AQUILA 211 ENGINEERING DRIVE AUBURN, AL 36849 POST LAUNCH ASSESSMENT REVIEW APRIL 29, 2016 Motor Specifications The team originally planned to use an Aerotech L-1520T motor and attempted four full
LEVEL 3 BUILD YELLOW BIRD. Dan Schwartz
LEVEL 3 BUILD YELLOW BIRD Dan Schwartz This entire rocket is built using the same techniques I use for my nose cones, a central airframe tube for compression strength and rings of high compression styrofoam
NASA s Student Launch Initiative :
NASA s Student Launch Initiative : Critical Design Review Payload: Fragile Material Protection 1 Agenda 1. Design Overview 2. Payload 3. Recovery 4. 5. I. Sub-Scale Predictions II. Sub-Scale Test III.
University of Notre Dame
University of Notre Dame 2016-2017 Notre Dame Rocketry Team Critical Design Review NASA Student Launch Competition Roll Control and Fragile Object Protection Payloads Submitted January 13, 2017 365 Fitzpatrick
Bumble Bee. Please read and understand all instructions before building!
Bumble Bee The Bumble Bee kit contains all the parts necessary* to build a flying high power rocket: (1) Pre-slotted main airframe (1) Recovery tube (1) Nose cone (3) Fins (1) Piston ejection kit: (1)
NASA Student Launch College and University. Preliminary Design Review
2017-2018 NASA Student Launch College and University Preliminary Design Review Institution: United States Naval Academy Mailing Address: Aerospace Engineering Department United States Naval Academy ATTN:
Tacho Lycos 2017 NASA Student Launch Critical Design Review
Tacho Lycos 2017 NASA Student Launch Critical Design Review High-Powered Rocketry Team 911 Oval Drive Raleigh NC, 27695 January 13, 2017 Table of Contents Table of Figures:... 8 Table of Appendices:...
University of Illinois at Urbana-Champaign Illinois Space Society Student Launch Preliminary Design Review November 3, 2017
University of Illinois at Urbana-Champaign Illinois Space Society Student Launch 2017-2018 Preliminary Design Review November 3, 2017 Illinois Space Society 104 S. Wright Street Room 18C Urbana, Illinois
Critical Design Review Report
Critical Design Review Report I) Summary of PDR report Team Name: The Rocket Men Mailing Address: Spring Grove Area High School 1490 Roth s Church Road Spring Grove, PA 17362 Mentor: Tom Aument NAR Number
Presentation 3 Vehicle Systems - Phoenix
Presentation 3 Vehicle Systems - Phoenix 1 Outline Structures Nosecone Body tubes Bulkheads Fins Tailcone Recovery System Layout Testing Propulsion Ox Tank Plumbing Injector Chamber Nozzle Testing Hydrostatic
University Student Launch Initiative
University Student Launch Initiative HARDING UNIVERSITY Critical Design Review February 4, 2008 The Team Dr. Edmond Wilson Brett Keller Team Official Project Leader, Safety Officer Professor of Chemistry
Critical Design Review
Critical Design Review 1/27/2017 NASA Student Launch Competition 2016-2017 California State Polytechnic University, Pomona 3801 W Temple Ave, Pomona, CA 91768 1/27/2017 California State Polytechnic University,
NASA - USLI Presentation 1/23/2013. University of Minnesota: USLI CDR 1
NASA - USLI Presentation 1/23/2013 2013 USLI CDR 1 Final design Key features Final motor choice Flight profile Stability Mass Drift Parachute Kinetic Energy Staged recovery Payload Integration Interface
Overview. Mission Overview Payload and Subsystems Rocket and Subsystems Management
MIT ROCKET TEAM Overview Mission Overview Payload and Subsystems Rocket and Subsystems Management Purpose and Mission Statement Our Mission: Use a rocket to rapidly deploy a UAV capable of completing search
Rocket Design. Tripoli Minnesota Gary Stroick. February 2010
Rocket Design Tripoli Minnesota Gary Stroick February 2010 Purpose Focus is on designing aerodynamically stable rockets not drag optimization nor construction techniques! Copyright 2010 by Gary Stroick
Flight Readiness Review March 16, Agenda. California State Polytechnic University, Pomona W. Temple Ave, Pomona, CA 91768
Flight Readiness Review March 16, 2018 Agenda California State Polytechnic University, Pomona 3801 W. Temple Ave, Pomona, CA 91768 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission
Student Launch. Enclosed: Preliminary Design Review. Submitted by: Rocket Team Project Lead: David Eilken
University of Evansville Student Launch Enclosed: Preliminary Design Review Submitted by: 2016 2017 Rocket Team Project Lead: David Eilken Submission Date: November 04, 2016 Payload: Fragile Material Protection
AUBURN UNIVERSITY STUDENT LAUNCH PROJECT NOVA II. 211 Davis Hall AUBURN, AL CDR
AUBURN UNIVERSITY STUDENT LAUNCH PROJECT NOVA II 211 Davis Hall AUBURN, AL 36849 CDR January 10, 2019 Contents List of Tables...7 List of Figures...9 1 CDR Report Summary...12 1.1 Payload Deployable Rover...12
AUBURN UNIVERSITY STUDENT LAUNCH. Project Nova. 211 Davis Hall AUBURN, AL Post Launch Assessment Review
AUBURN UNIVERSITY STUDENT LAUNCH Project Nova 211 Davis Hall AUBURN, AL 36849 Post Launch Assessment Review April 19, 2018 Table of Contents Table of Contents...2 List of Tables...3 Section 1: Launch Vehicle
NASA Student Launch W. Foothill Blvd. Glendora, CA Artemis. Deployable Rover. November 3rd, Preliminary Design Review
2017 2018 NASA Student Launch Preliminary Design Review 1000 W. Foothill Blvd. Glendora, CA 91741 Artemis Deployable Rover November 3rd, 2017 Table of Contents General Information... 9 1. School Information...
MR-1. Please read and understand all instructions before building!
MR-1 This kit contains all the parts necessary* to build a flying high power rocket: (1) Pre-slotted main airframe (1) Nose cone with strap (3) Fins (1) Transition (1) Airframe section 1 long (1) Piston
CNY Rocket Team Challenge. Basics of Using RockSim 9 to Predict Altitude for the Central New York Rocket Team Challenge
CNY Rocket Team Challenge Basics of Using RockSim 9 to Predict Altitude for the Central New York Rocket Team Challenge RockSim 9 Basics 2 Table of Contents A. Introduction.p. 3 B. Designing Your Rocket.p.
Skill Level 3 Average Skills Needed. Made In USA. Kit #04997 Skill Level 4. Zephyr Parts List
Kit #04997 Skill Level 4 Made In USA Zephyr Parts List Item # Item Name Qty 10137 Engine Mount Tube (AT-38/11) 1 10218 Airframe Body Tube (AT-98/18) 4" Thick Wall 1 10219 Airframe Body Tube (AT-98/18)
Flight Readiness Review Addendum: Full-Scale Re-Flight. Roll Induction and Counter Roll NASA University Student Launch.
Flight Readiness Review Addendum: Full-Scale Re-Flight Roll Induction and Counter Roll 2016-2017 NASA University Student Launch 27 March 2017 Propulsion Research Center, 301 Sparkman Dr. NW, Huntsville
NASA SL Preliminary Design Review
NASA SL Preliminary Design Review University of Alabama in Huntsville 1 Mission Summary Design, fabricate, test and fly a rocket and payload to 1 mile in altitude Deploy a rover upon landing to autonomously
Preliminary Design Review
Preliminary Design Review November 16, 2016 11/2016 California State Polytechnic University, Pomona 3801 W Temple Ave, Pomona, CA 91768 Student Launch Competition 2016-2017 1 Agenda 1.0 General Information
This Week. Next Week 4/7/15
E80 Spring 2015 This Week! Transfer breadboard circuit to PC board.! Verify everything still works.! Get data logger working.! Pass off consists of: " Power PC board with data logger & start logging. "
COMPLETED SUMO LEVEL 1 MODEL ROCKET ADVANCED HIGH POWER MODEL ROCKET ASSEMBLY AND OPERATION INSTRUCTIONS BEFORE YOU BEGIN:
COMPLETED SUMO LEVEL 1 MODEL ROCKET ADVANCED HIGH POWER MODEL ROCKET ASSEMBLY AND OPERATION INSTRUCTIONS BEFORE YOU BEGIN: Study the illustrations and sequence of assembly. The sequence of assembly is
Critical Design Review
AIAA Orange County Section Student Launch Initiative 2011-2012 Critical Design Review Rocket Deployment of a Bendable Wing Micro-UAV for Data Collection Submitted by: AIAA Orange County Section NASA Student
Illinois Space Society University of Illinois Urbana Champaign Student Launch Maxi-MAV Preliminary Design Review November 5, 2014
Illinois Space Society University of Illinois Urbana Champaign Student Launch 2014-2015 Maxi-MAV Preliminary Design Review November 5, 2014 Illinois Space Society 104 S. Wright Street Room 321D Urbana,
ADVANCED MODEL ROCKET
Division of RCS Rocket Components, Inc. Assembly and Operation Instructions BEFORE YOU BEGIN: ADVANCED MODEL ROCKET COMPLETED INITIATOR ADVANCED MODEL ROCKET 19911-8091 Rev. 8/12/04 Study the illustrations
Student Launch. Enclosed: Proposal. Submitted by: Rocket Team Project Lead: David Eilken. Submission Date: September 30, 2016
University of Evansville Student Launch Enclosed: Proposal Submitted by: 2016 2017 Rocket Team Project Lead: David Eilken Submission Date: September 30, 2016 Payload: Fragile Material Protection Submitted
MASSACHUSETTS INSTITUTE OF TECHNOLOGY Department of Aeronautics and Astronautics
MASSACHUSETTS INSTITUTE OF TECHNOLOGY Department of Aeronautics and Astronautics 16.00 Introduction to Aerospace and Design Problem Set #4 Issued: February 28, 2002 Due: March 19, 2002 ROCKET PERFORMANCE
ADVANCED MODEL ROCKET. Read And Follow All Instructions
Division of RCS Rocket Components, Inc. Assembly and Operation Instructions BEFORE YOU BEGIN: ADVANCED MODEL ROCKET COMPLETED CHEETAH ADVANCED MODEL ROCKET 19916-3092 Rev. 8/12/04 Study the illustrations
CYCLONE STUDENT LAUNCH INITIATIVE
NSL PROPOSAL September 19, 2018 CYCLONE STUDENT LAUNCH INITIATIVE 2018-19 Iowa State University 537 Bissell Rd. 1200 Howe Hall Ames, IA 50011 Table of Contents Table of Contents... 2 Table of Figures...
Critical Design Review Report NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME)
Critical Design Review Report 2014-2015 NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME) Florida International University Engineering Center College
Florida A & M University. Flight Readiness Review. 11/19/2010 Preliminary Design Review
Florida A & M University Flight Readiness Review 11/19/2010 Preliminary Design Review 1 Overview Team Summary ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Vehicle Criteria ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~
Strap-on Booster Pods
Strap-on Booster Pods Strap-On Booster Parts List Kit #17052 P/N Description Qty 10105 AT-24/12 Slotted (Laser Cut) Tube 2 10068 Engine Mount (AT-18/2.75) Tube 2 13029 CR 13/18 2 13031 CR 18/24 4 14352
ADVANCED MODEL ROCKET
ADVANCED MODEL ROCKET Assembly and Operation Instructions Division of RCS Rocket Components, Inc. BEFORE YOU BEGIN: COMPLETED BARRACUDA ADVANCED MODEL ROCKET 19920-3092 Rev. 8/12/04 Study the illustrations
Northwest Indian College Space Center USLI Critical Design Review
2012-2013 Northwest Indian College Space Center USLI Critical Design Review Table of Contents, Tables, and Figures I.0 CDR Report Summary... 1 I.1 Team Summary... 1 I.2 Launch Vehicle Summary... 1 I.2a
Rocketry Projects Conducted at the University of Cincinnati
Rocketry Projects Conducted at the University of Cincinnati 2009-2010 Grant Schaffner, Ph.D. (Advisor) Rob Charvat (Student) 17 September 2010 1 Spacecraft Design Course Objectives Students gain experience
Proposal NASA Student Launch Competition
2017-2018 Proposal NASA Student Launch Competition Table of Contents 1 Summary............................................ 5 1.1 Team Summary....................................... 5 1.2 Student Team Leaders...................................
Cal Poly Pomona Rocketry NASA Student Launch Competition POST LAUNCH ASSESMENT REVIEW April 24, 2017
Cal Poly Pomona Rocketry NASA Student Launch Competition 2016-2017 POST LAUNCH ASSESMENT REVIEW April 24, 2017 California State Polytechnic University, Pomona 3801 W Temple Ave, Pomona, CA 91768 Department
THE UNIVERSITY OF AKRON
THE UNIVERSITY OF AKRON College of Engineering 302 E Buchtel Ave Akron, OH 44325 September 20, 2017 NASA Student Launch Initiative Table of Contents 1. Adult Educators and Advisors... 4 2. Team Officials...
LaserHawk Flying Model Rocket Instructions Designed by Matt Steele
VEHICLE DATA SHEET Physical Data North Coast Rocketry LaserHawk Flying Model Rocket Instructions Designed by Matt Steele Parameter Dimension Length Diameter 57 (145 cm) 2.64 (6.7 cm) Weight (w/o chute)
COMPLETED MIRAGE ADVANCED MODEL ROCKET
Division of RCS Rocket Components, Inc. BEFORE YOU BEGIN: Study the illustrations and sequence of assembly. The sequence of assembly is important. Review the parts list and become familiar with all parts
ISS Space Grant Team Exocoetidae
ISS Space Grant Team Exocoetidae Illinois Space Society University of Illinois at Champaign-Urbana March 9, 2018 Faculty Advisor: Diane Jeffers (dejeffer@illinois.edu, 217-898-5888) Team Lead: Shivani
Project WALL-Eagle Maxi-Mav Flight Readiness Review
S A M U E L G I N N C O L L E G E O F E N G I N E E R I N G Auburn University Project WALL-Eagle Maxi-Mav Flight Readiness Review 2 Engineering Dr. Auburn, AL 36849 March 6th, 205 Table of Contents Section
University of North Dakota Department of Physics Frozen Fury Rocketry Team
University of North Dakota Department of Physics Frozen Fury Rocketry Team NASA Student Launch Initiative Flight Readiness Review - Report Submitted by: The University of North Dakota Frozen Fury Rocketry
Preliminary Design Review November 15, Agenda. California State Polytechnic University, Pomona W. Temple Ave, Pomona, CA 91768
Preliminary Design Review November 15, 2017 Agenda California State Polytechnic University, Pomona 3801 W. Temple Ave, Pomona, CA 91768 Agenda 1.0 General Information 2.0 Launch Vehicle System Overview
How Does a Rocket Engine Work?
Propulsion How Does a Rocket Engine Work? Solid Rocket Engines Propellant is a mixture of fuel and oxidizer in a solid grain form. Pros: Stable Simple, fewer failure points. Reliable output. Cons: Burns
Post Launch Assessment Review
AIAA Orange County Section Student Launch Initiative 2011-2012 Post Launch Assessment Review Rocket Deployment of a Bendable Wing Micro-UAV for Data Collection Submitted by: AIAA Orange County Section
Electronic Deployment
Electronic Deployment and a little bit of recovery too! By: Gerald Meux, Jr. NAR and TRA Level 3 1-3-11 8/28/2014 Electronic Deployment - Gerald Meux, Jr. 1 Table of Contents 8/28/2014 Electronic Deployment
NWIC Space Center s 2017 First Nations Launch Achievements
NWIC Space Center s 2017 First Nations Launch Achievements On April 18, 2017, we were on two airplanes to Milwaukee, Wisconsin by 6:30 am for a long flight. There were 12 students, 3 mentors, 2 toddlers
NASA University Student Launch Initiative (Sensor Payload) Final Design Review. Payload Name: G.A.M.B.L.S.
NASA University Student Launch Initiative (Sensor Payload) Final Design Review Payload Name: G.A.M.B.L.S. CPE496-01 Computer Engineering Design II Electrical and Computer Engineering The University of
Table of Content 1) General Information ) Summary of PDR Report ) Changes Made Since Proposal ) Safety... 8
Table of Content 1) General Information... 3 1.1 Student Leader... 3 1.2 Safety Officer... 3 1.3 Team Structure... 3 1.4 NAR/TRA Sections... 4 2) Summary of PDR Report... 5 2.1 Team Summary... 5 2.2 Launch
NORTHEASTERN UNIVERSITY
NORTHEASTERN UNIVERSITY POST-LAUNCH ASSESSMENT REVIEW NORTHEASTERN UNIVERSITY USLI TEAM APRIL 27TH 2018 Table of Contents 1. Summary 2 1.1 Team Summary 2 1.2 Launch Summary 2 2. Launch Vehicle Assessment
Information Pack for Mid Power Rockets
Information Pack for Mid Power Rockets www.qldrocketry.com Table of Contents 1. Introduction... 2 2. Terminology... 3 3. Rocket Flight Phases... 4 4. Igniters... 5 5. Motors... 6 5.1 Key Components...
FLYING MODEL ROCKET KIT INSTRUCTIONS KEEP FOR FUTURE REFERENCE. TEST-FIT ALL PARTS TOGETHER BEFORE APPLYING ANY GLUE!
www.estesrockets.com ESTES INDUSTRIES 1295 H Street Penrose, CO 81240 PRINTED IN CHINA EST 1247/2053 FLYING MODEL ROCKET KIT INSTRUCTIONS KEEP FOR FUTURE REFERENCE. ASSEMBLY TIP: Read all instructions
UNIVERSITY OF NORTH DAKOTA FROZEN FURY CRITICAL DESIGN REVIEW REPORT NASA STUDENT LAUNCH 2015
1 UNIVERSITY OF NORTH DAKOTA FROZEN FURY CRITICAL DESIGN REVIEW REPORT NASA STUDENT LAUNCH 2015 2 Table of Contents Summary Team Summary Launch Vehicle Summary AGSE/Payload Summary Changes Made Since PDR
Flight Readiness Review Report NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME)
Flight Readiness Review Report 2014-2015 NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME) Florida International University Engineering Center College
Post Launch Assessment Review
Post Launch Assessment Review University of South Alabama Launch Society Conner Denton, John Faulk, Nghia Huynh, Kent Lino, Phillip Ruschmyer, Andrew Tindell Department of Mechanical Engineering 150 Jaguar
1:6 BLACK BRANT II. c o s m o d r o m e r o c k e t r y
c o s m o d r o m e r o c k e t r y 1:6 BLACK BRANT II This kit is capable of use with high thrust motors. It is therefore strongly recommended that epoxy be used throughout the construction of this kit.
University of South Florida
University of South Florida NASA Student Launch Centennial Challenge MAV Project Flight Readiness Report 14 March 2016 Society of Aeronautics and Rocketry 15219 Plantation Oaks Drive, Apt 4. Tampa, FL,
University Student Launch Initiative Preliminary Design Review
UNIVERSITY OF MINNESOTA TWIN CITIES 2012 2013 University Student Launch Initiative Preliminary Design Review Department of Aerospace Engineering and Mechanics 3/18/2013 2012-2013 University of Minnesota
Modified shock-cord mount and cables (cables are shown pushed into motor mount here)
Building the Ariel Builder: Ray Wilkinson This is Ray Wilkinson's own rocket, but will mostly reside at UH, and will be used for display purposes as well as being flown. It's built from a kit made by PML
COMPLETED ASTROBEE D ADVANCED MODEL ROCKET
Division of RCS Rocket Components, Inc. BEFORE YOU BEGIN: ADVANCED MODEL ROCKET Assembly and Operation Instructions Study the illustrations and sequence of assembly. The sequence of assembly is important.