Preliminary Design Review. Rocket & Payload Schematic.

Slides:



Advertisements
Similar presentations
University of Florida Hybrid Rocket Team’s Mile High Club
Advertisements

University of Florida PDR Presentation. Vehicle Design Diameter: 5.86 Length: 135 Static Stability Margin: 1.4 Total Weight: 23.6 lbs.
BYU Rocket Team Special thanks to:
Northwestern University Space Technology and Rocketry Society (NUSTARS) NASA Student Launch Flight Readiness Review March 16, 2015.
U NIVERSITY OF F LORIDA T HE M OST I NTERESTING R OCKET IN THE W ORLD.
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.
St. Vincent – St. Mary CDR Presentation NASA Student Launch Initiative.
Our Mission Statement  Launch a high-power rocket to an altitude of one mile carrying the Operation: Epic Beep payload package. At lift off, the rocket’s.
NASA CDR Presentation Spring Grove Area High School.
St. Vincent – St. Mary FRR Presentation NASA Student Launch Initiative.
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.
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.
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.
Launch Vehicle  Launch Vehicle Summary  The length of the rocked is inches, and the mass is ounces.  We have a dual Deployment Recovery.
Illinois Space Society Tech Team USLI FRR Presentation.
CDR Clear Lake's Team Rocket 2929 Bay Area Blvd. Houston, TX
Rocket Based Deployable Data Network University of New Hampshire Rocket Cats Collin Huston, Brian Gray, Joe Paulo, Shane Hedlund, Sheldon McKinley, Fred.
Intercollegiate Rocket Engineering Competition Spring 2015 EML Ethics and Design Project Organization.
Rocket Based Deployable Data Network University of New Hampshire Rocket Cats Collin Huston, Brian Gray, Joe Paulo, Shane Hedlund, Sheldon McKinley, Fred.
Types of Rockets Avionics Phases of Flight Materials Home Page High Powered Rocketry End Show.
Student Launch Project Flight Readiness Review April 21, 2014.
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.
Windward Community College University of Hawaii
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.
STUDENT LAUNCH PRELIMINARY DESIGN REVIEW PROJECT ADVANCE.
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.
University of Florida Rocket Team Critical Design Review Presentation.
Critical Design Review Presentation Jan. 20, 2011.
Harvard-Westlake Rocketry Club SLI FRR.
Critical Design Review- UCF Jeremy Young Anthony Liauppa Erica Terry, Emily Sachs Kristen Brightwell Gillian Smith 1.
Atomic Aggies CDR. Final Launch Vehicle Dimensions Diameter 5.5” Overall length: inches Approximate Loaded Weight: lb.
The Rocket Men Project One Giant Leap. Dimensions Rocket Length in. Rocket Mass- 171 oz. Top Body Tube Length in. Bottom Body Tube Length-
D EPARTMENT OF M ECHANICAL AND A EROSPACE E NGINEERING HIGH POWERED ROCKETRY CLUB PDR PRESENTATION 1.
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 
FAMU PDR Presentation. Table of Contents Vehicle dimensions, materials, and justifications Static stability margin Plan for vehicle safety verification.
Critical Design Review Presentation Project Nova.
D EPARTMENT OF M ECHANICAL AND A EROSPACE E NGINEERING HIGH POWERED ROCKETRY CLUB CDR PRESENTATION 1.
Critical Design Review Presentation Alabama Rocket Engineering Systems (ARES) Team The University of Alabama.
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:
Critical Design Review Presentation
2018 First Nation Launch - Flight Readiness Review
Sounding Rocket CDR Team Name
Final Readiness Review
Mars Rover CDR Team Name
2019 First Nation Launch – PDR Virtual Review
2019 First Nation Launch – Oral Presentation
Dual-Deploy Launch Checklist
2019 First Nation Launch – CDR Virtual Review
Plantation High SL team 1
Target Altitude Safety Document
2019 First Nation Launch – Oral Presentation
Presentation transcript:

Preliminary Design Review

Rocket & Payload Schematic

Lift Off Apogee and ejection of drogue parachute Payload and main chute deployment

Rocksim predicted trajectory of rocket

Deployment of main parachute and Airship Airship Main parachute Rocket body

 The vehicle body tubes will be made of cardboard because of its cost and strength to weight ratio.  The Nose Cone will be made of Polystyrene because of its weight versus strength against other materials.  Both the Main Parachute and the Drogue Parachute will be made of rip-stop nylon.

 The thrust-to-weight ratio is:28.65  The rail exit velocity will be: 73.6 ft/s  The static stability margin is: 2.56  The current motor selected is a: Cesaroni K660. This choice came from vigorous testing in Rocksim to achieve the desired height.

Rocket with Cesaroni K660

 These components: airship, Tygon tubing, gas canister, electronics bay; will have repeated static testing.  Parachute charges will be static tested at various points in the design process.  Half-Scale Rocket will be made and tested several times before launch day.  A test flight of the main vehicle will be done to confirm rocket stability as required.

 Before launch, the team will confirm they have telemetric contact with the rocket.  Altimeters will be checked prior to launch.  All power supplies (batteries) will be checked before launch to ensure they are at maximum capacity.  The parachutes will be checked several times for proper folding.  Black powder charges will be checked by advisors before loading the charges into the rocket.

 Team will confirm they have telemetric contact and radio contact with the airship prior to putting the rocket on the pad.  Team will confirm airship is connected correctly to the gas tubing.  Air canisters will be checked prior to launch for correct capacity and pressure.

 The total mass of the vehicle and payload is expected to be 23 pounds at liftoff. The mass was used to calculate the ideal parachute for the rocket.  Recovery systems are attached using half-inch shock chord fastened through an eyebolt. The eyebolts will be fastened to bulkheads fitted inside of the airframe and securely set using epoxy.  At the end of the shock chord there is a one thousand pound rated swivel to which the parachute will attach. In order to keep the sustainer section attached to the rest of the vehicle after drogue chute deployment the drogue chute is attached to both the sustainer section and the electronics bay (EBay).

 The vehicle has a dual deployment system. Carrying a drogue and a main parachute, the vehicle deploys them via the use of an altimeter activated deployment charges. The drogue chute is positioned in the sustainer section and is deployed at an altitude of one mile (agl). Once the altimeter reads 5,280 feet, an electrical charge will set off two deployment charges. Then, the pressure built up inside of the airframe will separate the two tubes releasing the drogue parachute.

 As the rocket begins its decent with the deployed drogue chute, the altimeter will be waiting until the vehicle reaches the height of 1,000 feet and at that point will again trigger two deployment charges. These two will be position in the payload section just above the air tank and separated by three bulkheads. The pressure created will push out the nose cone deploying the airship and the main parachute.

 The airship, to perform correctly must inflate in the air and release when instructed from the falling rocket body. To do this, the air canisters in the payload section of the rocket will be on a remote controlled valve system. This system will allow ground personnel to open them and allow the gas inflate the airship at 1000 ft., after the main parachute is deployed. 

 The airship will also have a motored system that is radio controlled. It allows ground personnel to direct the airship’s flight pattern. This system allows the airship to land safely and accurately  A radio controlled tether release will be used on the airship after it has fully inflated.  Finally, the airship will hold a steady-cam camera that takes video during its flight. The camera will continuously send data back to the ground station during the entire trip.

 The Rocket will have an electronics bay inside containing the ejection charged wired to altimeters. At specified altitudes the ejection charges will go off, ejecting the drogue and main parachutes as planned. The main parachute will eject at around 1000 feet, to give the airship time to inflate and deploy.

End