Preliminary Design review

Slides:

Advertisements

Similar presentations

UF Hybrid Rocket Teams Mile High Club Brought to you by Chris Leonard, Ty Morton, Alex Aueron, Sam Darr, and Josh Childs.

Advertisements

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

P RELIMINARY D ESIGN R EVIEW University of North Dakota Frozen Fury Rockety Team.

Critical Design Review NASA University Student Launch Initiative University of Nebraska–Lincoln

Student Launch Project Preliminary Design Review January 10, 2014.

Illinois Space Society Tech Team USLI CDR Presentation.

FLIGHT READINESS REVIEW TEAM HAWAII. LEO HANO FULL SCALE LOW POWER March 13, 2011 Motor = K780R.

U NIVERSITY OF F LORIDA PDR P RESENTATION. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work.

Project Λscension. Vehicle Dimensions Weight: 19.6 Ib Length: in (9 ft. 4.5 in) Diameter: 6 in Fin Semi-Span: 6 in.

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.

Windward Community College University of Hawaii

Windward Community College. Rocket: Leo Hano Payload: Hula-hoop.

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.

Hawaii - WCC.  5,280 ft  Carry a student payload  National CanSat program  No bigger than a 12 fl oz soda can  Mass no greater than 1 kg  USLI.

FLIGHT READINESS REVIEW TEAM HAWAII. LEO HANO FULL SCALE LOW POWER March 13, 2011 Motor = K780R.

LESSON ld05 Rocket Stability

Flight Readiness Review Atomic Aggies. Final Launch Vehicle Dimensions Diameter 5.5” Overall length: inches Approximate Loaded Weight: lb.

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

Illinois Space Society Tech Team USLI FRR Presentation.

Rocket Based Deployable Data Network University of New Hampshire Rocket Cats Collin Huston, Brian Gray, Joe Paulo, Shane Hedlund, Sheldon McKinley, Fred.

Preliminary Design Review “Analysis of Atmospheric Cosmic Radiation Distribution as a Function of Altitude” Steven Schroeder-Program Manager Damon Emerson-Rocket.

Launch Vehicle Summary Rocket Name: The Green Machine 124 inches in length 6” diameter L1500T 98-mm motor 42” drogue deployed at apogee 144” main to be.

Student Launch Project Flight Readiness Review April 21, 2014.

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

Windward Community College University of Hawaii

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.

3/19/09. Animal Motor Works (AMW) K475WW High Power Rocket Motor. 54 mm casing, 40.3 cm long, 2.9 seconds burn time, 1394 N-sec total impulse, and

The Rocket Men Project One Giant Leap. Final Launch Vehicle Dimensions Rocket Length in. Rocket Mass- 171 oz. Top Body Tube Length in. Bottom.

University of Arkansas Senior Project- When Pigs Soar.

The Comparative Analysis of Airflow Around a Rocket.

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

Flight Readiness Review Student Launch Initiative SCS Rocket Team Statesville Christian School April 2, 2008.

Windward Community College University of Hawaii

University of Florida Rocket Team Critical Design Review Presentation.

Critical Design Review Presentation Jan. 20, 2011.

Rockets Applied Science Fall 08 Mrs. Dickerson.

Critical Design Review- UCF Jeremy Young Anthony Liauppa Erica Terry, Emily Sachs Kristen Brightwell Gillian Smith 1.

WINDWARD COMMUNITY COLLEGE UNIVERSITY OF HAWAII

Atomic Aggies CDR. Final Launch Vehicle Dimensions Diameter 5.5” Overall length: inches Approximate Loaded Weight: lb.

Project Ares University of Central Florida NASA Student Launch 1/28/2015.

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

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

University Student Launch Initiative Team Members Todd Esposito Patrick Lancaster Joleen Iwaniec Premo Ames II Jazmine Maru Jazmine Maru.

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

University Student Launch Initiative Preliminary Design Review University of Illinois at Urbana-Champaign Team Rocket.

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

NUSTA RS NASA Student Launch MAV Challenge 2016 Critical Design Review 15 Janurary2015 Northwestern University | 2145 Sheridan Road | Evanston, IL

January 14,  Length: inches  Diameter: 6 inches  Mass: oz. / lbs.  Span: 22 inches  Center of Gravity: inches 

Critical Design Review Presentation Project Nova.

Flight Readiness Review UNIVERSITY OF SOUTH ALABAMA CONNER DENTON, JOHN FAULK, NGHIA HUYNH, KENT LINO, PHILLIP RUSCHMYER, & ANDREW TINDELL MENTOR : RICHARD.

UCF_USLI Preliminary Design Review David Cousin Freya Ford Md Arif Drew Dieckmann Stephen Hirst Mitra Mossaddad University of Central Florida.

Project Aegis Preliminary Design Review Team Members:

Preliminary Design Review Presentation

Rocket Stability.

College of Engineering

* 07/16/96 Propulsion Lab 6 Winter Quarter *.

Critical Design Review Presentation

NASA USLI Preliminary Design Review

Georgia Tech NASA Preliminary Design Review Teleconference

November 7, 2014.

LESSON ld05 Rocket Stability

November 7, 2014.

Final Readiness Review

Windward Community College ARLISS/USLI Presentation Fall 2009 KCC, Ohi’a Room 118 November 21, 2009 Premo Ames II Todd Esposito Joleen Iwaniec Patrick.

Characteristics,Construction, Recovery

LESSON ld05 Rocket Stability

University of Iowa USLI

Presentation transcript:

Preliminary Design review Windward Community College University of Hawaii 2010-2011

Project: Rocket; Leo Hano Payload; Hula Hoop

Design Criteria Build a Rocket to be launched to an altitude of 5280 ft. (1 mile) Rocket must carry a scientific payload Rocket must return safely

Flight Profile Boost Phase Coast Phase Apogee Rapid Decent Phase Drogue Deployed Rapid Decent Phase ~60 ft/sec Main Decent Phase ~20 ft/sec

Rocket Design Details Length: 121” Diameter: 6” Weight: 15 lbs., unloaded Weight: ~20 lbs., on the pad Materials: G10 Fiberglass Recovery: Dual Deployment, electronic Propulsion: 75mm AMW L777WW

Characteristics GPSFlight in nose cone Variable Drag Configuration (VDR) Four fin design Avionics Featherweight Raven-2 PerfectFlight MAWD Dual deployment

Rocket Stability Center of Pressure: 91.70” Center of Gravity: 75.27” Caliber: 2.74 Marginally Over-stable

Motor Selection Animal Motor Works L777WW Total Impulse: 3180 Ns Casing: 75mm X 497mm Average Thrust: 774.47 N Peak Thrust: 1000.16 N Thrust to weight: ~7.5

Motor Justification Drag force is linear to ~30 degrees Approximate altitude loss ~1.2%/degree 30 degree deployment yields ~36% loss Must yield max altitude below 7180 ft and above 5280 ft

Hula Hoop Three perpendicular coils around a non-magnetic sphere 24-bit ADC EEPROM BS2p Micro-Controller 3-axis accelerometer (comparison)

Timeline

Important Dates Recovery deployment testing: 1/22/11 Full-Scale Low-Power test: 3/13/11

1:3.7 Scale Drag Shoe

pau