P07109: Project M.E.T.E.O.R. Flying Rocket Team Andrew ScarlataProject Leader/ Mechanical Engineer Geoff CassellLead Engineer/ Mechanical Engineer David.

Slides:

Advertisements

Similar presentations

P07105: Project METEOR - Steel Rocket January 19, Project METEOR Design and Optimization of a Small Scale Rocket for Pico- Satellite Launching Team.

Advertisements

High Altitude Payload Design – A Mechanical Aspect Kaysha Young and Emily Bishop – Montana State University - Bozeman Advisor: Dr. Brock J. LaMeres Mechanical.

36th Annual Frontiers in Education Conference

Rocket Engines Liquid Propellant –Mono propellant Catalysts –Bi-propellant Solid Propellant –Grain Patterns Hybrid Nuclear Electric Performance Energy.

Hybrid Propulsion System Basics

EDGE™ Concept Level Project Plan P09102 – METEOR Stage Separation System JJ Guerrette (ME)

Filament Winding Machine. Project Name – Filament Winding Machine Project Number – P09226 Project Family – Competitive FSAE Autosports Systems Project.

Design Goals Saturn V Ariane 4 Pegasus Vanguard Bellerophon ? ? ?

 Zachary Huffaker, Brian Plank, Audrey Dearien Faculty Sponsor: Dr. Will Holmes.

Monopropellant Micro Propulsion system for CubeSats By Chris Biddy 174 Suburban Rd Suite 120 San Luis Obispo CA (805)

EDGE™ Copyright © 2007 Rochester Institute of Technology All rights reserved.. Design, Fabrication, and Testing of a Novel, Automated, Remotely Operated.

Introduction to Hypersonic Propulsion Systems

1. P09203 – 1kg Robotic Motor Module Gen 2 Platform This project is Sponsored by the Kate Gleason Foundation.  Team Members:  Lauren Farnsworth → Team.

MaCH – SR1: Increasing T/W Ratio of Engine 5 APR 2005.

Project M.E.T.E.O.R. P07109: Flying Rocket Team Andrew Scarlata, Geoff Cassell, Zack Mott, Garett Pickett, Brian Whitbeck, Luke Cadin, David Hall.

Classic Concept. HTPB Fuel Grain Nitrous Oxide Tank Pre-Combustion Chamber Post-Combustion Chamber Graphite Nozzle Helium Reservoir Vessel Electronics.

University of Utah Unity IV Responsibilities Motor System –Fuel –Nozzle –Ignition Flight Profile Maximum Energy Footprint.

The Team Lincoln Cummings (IE) – Project Manager Joe Calkins (ME) – Chief Engineer Mark Fazzio (ME) – Technical Writer Allison Studley (ME) – Minutes.

HTPB Fuel Grain Flow Rate, Sizing, and Thrust. Regression Rate Governs Size The faster the solid propellant is burned, the “fatter” the rocket must be.

P07109: Project M.E.T.E.O.R. Flying Rocket Team Andrew ScarlataProject Leader/ Mechanical Engineer Geoff CassellLead Engineer/ Mechanical Engineer David.

P07109: Project M.E.T.E.O.R. Flying Rocket Team Andrew ScarlataProject Leader/ Mechanical Engineer Geoff CassellLead Engineer/ Mechanical Engineer David.

R0X-56 Design. HTPB Fuel Grain Nitrous Oxide Tank Pre-Combustion Chamber Post-Combustion Chamber Graphite Nozzle Helium Reservoir Vessel Electronics Payload.

METEOR BACKGROUND This is a foundation project in an ambitious endeavor to provide the RIT research community with a means to conduct near space.

Identified Company (CompositeX) to manufacture Custom Composite Pressure Vessel ● Working pressure 1000psi ● Holds 8 kg Nitrous Oxide ● 700 cubic inch.

Concept Design Review Micro Air Vehicle Project: P Sponsored by Impact Technologies The Boeing Company Mark Baybutt Electrical Engineering.

Design Review Three Micro Air Vehicle Project: P Sponsored by Impact Technologies The Boeing Company Mark Baybutt Electrical Engineering.

Project Review Micro Air Vehicle Project: P Sponsored by Impact Technologies The Boeing Company Mark Baybutt Electrical Engineering David.

Propulsion Engineering Research Center NASA Technology Roadmap: Launch Propulsion Systems Robert J. Santoro The Propulsion Engineering Research Center.

University of Utah Unity IV Responsibilities Motor System –Fuel –Nozzle –Ignition Flight Profile Maximum Energy Footprint.

Project METEOR Microsystems Engineering and Technology for the Exploration of Outer Regions.

Project M.E.T.E.O.R. P07109: Flying Rocket Team Andrew Scarlata, Geoff Cassell, Zack Mott, Garett Pickett, Brian Whitbeck, Luke Cadin, David Hall.

Aerospace fuel and it’s composition

Tropos-1 Hybrid rocket Project

Daedalus Astronautics Gaines Gibson. Mission To further students’ education and expertise in propulsion related activities.

36th Annual Frontiers in Education Conference

Satellites and Launch Vehicles. “Gee Whiz” Facts Number of satellites currently in orbit is over 900 Satellites orbit at altitudes from 100 miles (Low.

EXTROVERTSpace Propulsion 02 1 Thrust, Rocket Equation, Specific Impulse, Mass Ratio.

Comprehend the different types of rockets Comprehend the propulsion and flight of rockets Comprehend the types of launch vehicles Comprehend the factors.

 Expand upon knowledge base developed from Panther 1 solid rocket launch (6/28/06)  Enhance relationship and training opportunities between Florida.

Electrical and Computer Engineering Senior Design John Peeples, Ph. D., P.E. Professor and Department Head.

Aug 9, 2008S. Kahn -- HCC Magnet Plans1 HCC Magnet Future Plans Steve Kahn Aug 9, 2008 NFMCC Friday Meeting.

Fluid Dynamics of Combustion System for Diesel Engines P M V Subbarao Professor Mechanical Engineering Department Use of Fluid Dynamics to Design Matured.

Project M.E.T.E.O.R. P07109: Flying Rocket Team

Effects of Swirl Injector Design on Hybrid Rocket Fuel Regression Rate

VEL TECH Dr. RR & Dr. SR TECHNICAL UNIVERSITY

P16680: AATech Universal Oil and Bag System Bryce Mowers Jessica Reed Maria King Nicole Anklam Philip Couturier Samantha Orlando.

TESLA Rocket Project Lecture #3 10/28/15

Introduction to Rocketry 1 June Rocket Concepts Newton’s Laws of Motion Thrust Drag Stability Moments of Inertia Parachutes Rocket Construction.

P07108: METEOR Instrumentation Recovery System. Team Bash Nanayakkara – Project Manager (ISE) Scott Defisher – Fuselage Design (ME) Mike Kochanski – Software.

RIT MAV System Review (P08121) Dr. Jeffrey Kozak – Faculty Guide Michael Reeder – Team Leader Kevin Hand – Lead Engineer Todd Fernandez – ME.

P07122: Autonomous Quadcopter Jason Enslin – EE: Team Leader, Circuit Design/Testing Glenn Kitchell – CE: Programming, Software Design Richard Nichols.

6/13/20161 P ROJECT METEOR H YBRID R OCKET M OTOR Ken Court Chad Eberhart Patrick Haus Chris Natoli Nohl Schluntz S ENIOR D ESIGN P ROJECT R EVIEW Friday.

P07122: Autonomous Quadcopter Jason Enslin – EE: Team Leader, Circuit Design/Testing Glenn Kitchell – CE: Programming, Software Design Richard Nichols.

EDGE™ Preliminary Project Plan P09102 – METEOR Stage Separation System JJ Guerrette (ME)

2005 Joint Propulsion Conference Tucson, AZ July 10-13, 2005 Candidate Near-Term Fuel Options for Conventional and Bimodal NTR Engines J. A. Halfinger.

EDGE™ Concept Level Project Plan P09103 Rocket Self-Destruction Device Chris Natoli (ME)

ROCKET TESTING TYPES OF TESTS

P07203 Dynamometry Laboratory Infrastructure

Rocket Engines Liquid Propellant Solid Propellant Hybrid Nuclear

Concept Level Project Plan P09102 – METEOR Stage Separation System

Analysis of Rocket Propulsion

MaCH – SR1: Increasing T/W Ratio of Engine

Project M.E.T.E.O.R. Flying Rocket Team P07109 Combustion Assembly

John Beasley 3/20/2008 Propulsion Group Contact: Black Boxes and Code Flowchart AAE 450 Spring 2008.

P07122: Autonomous Quadcopter

Vice President, Business Development

DESIGN OF THE ARIES IV TRIBRID LIQUID PROPELLANT ROCKET ENGINE

Project METEOR Hybrid Rocket Motor Team Members: Marc Balaban

Project METEOR Hybrid Rocket Motor Team Members: Marc Balaban

Team Members: Sagar Sheth Team Leader Leonardo Silva Industrial Eng.

Presentation transcript:

P07109: Project M.E.T.E.O.R. Flying Rocket Team Andrew ScarlataProject Leader/ Mechanical Engineer Geoff CassellLead Engineer/ Mechanical Engineer David HallLead Engineer/ Mechanical Engineer Luke CadinMechanical Engineer Zack MottMechanical Engineer Garett PickettElectrical Engineer Brian WhitbeckMechanical Engineer Sponsor: Dr. Dorin Patru Electrical Engineering department Advisor: Dr. Jeffrey Kozak Generous donation from Harris RF Corporation

Project Description Part of the M.E.T.E.O.R. family Launching small payloads into low-Earth orbit Continuation of P06006: Hybrid Rocket Engine Design and Testing Working in conjunction with P07105 & P07106 Research, develop, and manufacture a flight ready hybrid rocket stage Primary Customer Need: Achieve a structure to propellant ratio of 1:10 – 2:10. Other design specifications to consider Maintain structural integrity Accommodation of other systems Manufacturing feasibility Improvements on ignition system

Current Design HTPB Fuel Grain Nitrous Oxide Tank (inside) Pre Combustion Chamber Post-Combustion Chamber Graphite Nozzle Electronics Payload Polymer Matrix Composite Outer Shell Micro Inertial Measurement Unit Servo Actuated Cold Jet Array Honeycomb Structure/ Composite Sandwich End Cap

Special Concerns Given the cooperative nature of the project, physical data is still needed to make any final design decisions Testing is scheduled for the first week of Senior Design II Analysis of more complicated systems is out of the range of expertise for team members Combustion gas behavior

Current State of Design Accurate theoretical models have been made and await technical data from testing results Finite Element Analysis Thermal Modeling Material selection is underway Outer body materials Composite tank selection Pre and post combustion chamber alternatives Ignition system has been optimized and preliminary construction has begun

Mass Budget Imported Items: Electronics/Guidance System: 1kg Pre & Post Combustion Chambers: 0.15kg each Injector Plate: 0.31kg Exit Nozzle: 0.71kg Subtotal: 2.32kg Structural Items: Pressure Vessel: 0.64kg Titanium Shell: 0.56kg Composite Body: 0.85kg Subtotal: 2.05kg Total:4.37kg Limit: 2kg

Flying Rocket Ignition System Darlington Configuration of Transistors R3 Igniter load (Nichrome Wire) V2 = PWM from MSP430 F1-69

MSD II Schedule Week 1: Testing and data acquisition Week 2:Design detail and finalization Weeks 3-5: Material selection and ordering Weeks 6-8: Manufacture Week 9: Testing Week 10:Finalized documentation and Project Review

Questions? Thank You