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

Slides:

Advertisements

Similar presentations

SRB Return to Flight Activities

Advertisements

CAP Model Rocketry Program.  1. MATERIALS. I will use only lightweight, non-metal parts for the nose, body and fins of my rocket.  2. MOTORS. I will.

Combustion Design Considerations

MAE 4261: AIR-BREATHING ENGINES

Preliminary Design Review. Rocket & Payload Schematic.

Northwestern University Space Technology and Rocketry Society (NUSTARS) NASA Student Launch Flight Readiness Review March 16, 2015.

Thrust E80 Static Motor Test Spring Forces on a Rocket

U NIVERSITY OF F LORIDA T HE M OST I NTERESTING R OCKET IN THE W ORLD.

What is a Pulse Detonation Engine?

UAA Rocketry Critical Design Review Presentation.

NASA SLI 2010 Mulberry Grove High School Flight Readiness Review Measurement of UVB Radiation Absorption by Cloth Material at Different Altitudes and Measurement.

Student Launch Project Critical Design Review February 28, 2014.

Flight Readiness Review. Intimidator 5: 5” diameter, 10’ length, 47 lbs  Motor: Aerotech L1300R 4556 N-Sec of impulse  Predicted altitude 5203’- RockSim.

Critical Design Review. Intimidator 5: 5” diameter, 10’ length, 45 lbs  Motor: Aerotech L1300R 4556 N-Sec of impulse  Predicted altitude RockSim.

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.

Launch Procedures No-Go Criteria 1.Winds exceeding 10 knots steady from any direction 2.Cloud ceiling below 10,000 ft AGL 3.Data acquisition systems not.

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

ME 501 Corey Roberts Leo Montgomery Motor Plate Analysis.

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

November 7,  Length: inches  Diameter: 6.00 inches  Mass: oz. / 17.34lbs.  Span: inches  Center of Gravity: inches.

The Thrust Generator P M V Subbarao Professor Mechanical Engineering Department Another Passive Device…… An Obvious Concept for Generation of Motive Power.

UNITY IV BYU USU U of U Flight Controller Diagram Tiny Tiger Multitasking Controller To Ball Valve To Fire Separation Ring To Cable cutter for Main.

Hybrid Rocket Combustion Process & Nozzle John Chambers.

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

Coast displace- ment, y 2 Thrust displace- ment, y 1 The Rocket Lab.

Critical Design Review of “Mach Shock Reduction” Phase II January 2008 Statesville, NC.

Intercollegiate Rocket Engineering Competition Spring 2015 EML Ethics and Design Project Organization.

Tropos-1 Hybrid rocket Project

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

Science Fiction. Rocket flight Centre of Mass or Centre of Gravity (CM or CG) Centre of mass is the mean or central location of all the mass of an object.

 Vehicle dimensions, materials, and justifications  Static stability margin  Plan for vehicle safety verification and testing  Baseline motor selection.

36th Annual Frontiers in Education Conference

Flight Readiness Review Team Hawaii. Vehicle Properties Diameter (in)6 inches Length (in)127 inches Gross Liftoff Weight (lb)50.25 lb Launch Lug/button.

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

FRR Presentation IF AT FIRST YOU DON’T SUCCEED, TRY AGAIN… AND AGAIN AND AGAIN AND AGAIN.

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

Harvard-Westlake Rocketry Club SLI FRR.

AEROSPACE 410 AEROSPACE PROPULSION Lecture (10/25/2002) RAMJET ANALYSIS IDEAL RAMJET AND ACTUAL RAMJET DESIGN Dr. Cengiz Camci.

Gas Dynamics of Variable Area Ducts P M V Subbarao Professor Mechanical Engineering Department I I T Delhi Development of Efficient and Compact Passive.

TESLA Rocket Project Lecture #3 10/28/15

UNITY IV Critical Design Review Hill Air Force Base 13 April 2000 Phase II First Launch.

Hemodynamics Star Splitters 4-H Club Two Rivers, WI Hemodynamics.

HARDING UNIVERSITY FLYING BISONS A Study of Atmospheric Properties as a Function of Altitude Flight Readiness Review.

High Powered Rocket Team Fall Project Manager Wesley M. Harpster Team Members James Lawrence Ryan Horton Karna Shah James “Trey” Simmons Irfan Shaukat.

Design and Performance Analysis of a Hybrid-Motor Powered Model Rocket Ted Kapustka 15 Mar 2011 Photographs from

NUSTA RS NASA Student Launch MAV Challenge 2016 Preliminary Design Review 6 November 2015 Northwestern University | 2145 Sheridan Road | Evanston, IL

Solid Rocket Motors A solid rocket motor is a system that uses solid propellants to produce thrust Advantages High thrust Simple Storability High density.

SPACE By Rosie. List poems Now were going to write a list poem about space for example: Rockets, Oxygen, Moon, NASA, Science, These are thing to do with.

D EPARTMENT OF M ECHANICAL AND A EROSPACE E NGINEERING HIGH POWERED ROCKETRY CLUB CDR PRESENTATION 1.

UPDATE #2.  The predicted altitude was ~9500 feet.  Actual altitude was ~11960 feet.  After investigation the error was found in the simulated weight.

UKRA is affiliated to the British Model Flying AssociationBritish Model Flying Association Rocketry.

Apex. TRL:# Risk:  Apex has designed a rocket engine to meet the following criteria: Hybrid engine utilizing liquid N 2 O oxidizer Produce between 75.

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.

2018 First Nation Launch - Flight Readiness Review

November 7, 2014.

MaCH – SR1: Increasing T/W Ratio of Engine

November 7, 2014.

Eagle Space Flight Team

ESFT : Propulsion Team Solid Propellant Propulsion

Rocket Engine Test Aerospace Engineering

2019 First Nation Launch – FRR Virtual Review

Dual-Deploy Launch Checklist

Rocket Physics The Rocket Nozzle

Project METEOR Hybrid Rocket Motor Team Members: Marc Balaban

Project METEOR Hybrid Rocket Motor Team Members: Marc Balaban

2019 First Nation Launch – Oral Presentation

Presentation transcript:

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

Motor System Fuel –HTPB: Fuel grain composed of R-45M resin –Cross- linked with diisocyanate Motor Housing –6061-T6 Aluminum –Static tested to 1200 psia Nozzle –Ceramic Composite –Rated to 5000 F

Ignition Model Rocket Motors –2, Estes C8-0 motors Accessible on Launch Rail Low power requirement –4 AA Batteries Reliable Performance

HTPB NO 2 inlet Estes C8-0 Motor Injector “O” Ring Seal Motor Cap Assembly

Flight Profile Maximum Altitude –10,641 feet AGL, at T = 28 seconds Burn Time –T = 5.4 seconds Flight Velocity –Launch Rail Exit = 89.1 ft/s –Overall Flight = 0.71 Mach FTS Failure Impact –763 ft/s at T=58 seconds

Maximum Energy Footprint 5.40 Miles at   =45 0 No Critical Areas with in Range

Motor Assembly

Motor Cap

Motor Housing

Motor Nozzle

Motor Nozzle Retainer

Motor Assembly