St. Vincent – St. Mary FRR Presentation

NASA Student Launch Initiative

Final Launch Vehicle DimensionsLength: 127.6 inDiameter: 5.54 inSpan Diameter: 19.0400 inMass: 29.5 lbs. with ballastCenter of Gravity: 82.1 inCenter of Pressure: 90.4 inStatic Margin: 1.5

Rocket Rocksim Drawing

Key Design Features• Dual altimeters • Payload piston ejection system• Airship inflation system• Airship release system• Boat-tail

Final Motor ChoiceThe final motor we are using on our full

scale rocket is a Cessaroni K660. We chose the K660 because it has the ideal thrust for our full scale rocket design. The motor also has a fast burn time, allowing the rocket to reach maximum speed faster and

provide better launch stability

Rocket Flight Stability Margin

1.5Thrust-to-Weight Ratio

Rail Exit Velocity38.09 ft/s

5.46

Mass StatementOur mass margin is zero ( We are

overweight)

The rocket weighs about 29.5 pounds. The

rocket is at its limit on weight, any more and it will be hard to reach the expected height.

Parachutes and Recovery HarnessMain Chute – Skyangle Size 7 Recovery Harness – Area: 56.8 sq.ft Type: Tubular NylonMass: 40.9132 oz Size: 5/8 in w x 25 ft lDescent Rate: 13.84 ft Drogue Chute – Cert-3Area: 6.3 sq.ftMass: 6.00 ozDescent Rate: 75.5ft/s

Kinetic EnergyAfter drogue parachute is deployedRocket Section Kinetic Energy

(ft-lb)

Section 1(nose cone, forward payload tube, electronics bay, aft payload tube)

2048.58

Section 2(booster tube)

697.87

After main parachute is deployedRocket Section Kinetic Energy

(fl-lb)

Section 1(nose cone)

2.27

Section 2(forward payload tube, electronics bay, aft payload tube)

52.93

Section 3(booster tube)

18.81

Predicted Altitude of Launch Vehicle

Wind Speed (mph) Altitude (ft)

5 4468.5

10 4429.2

15 4359.4

20 4257.1

Predicted Drift from the Launch Pad

Wind Speed (mph)

Drift Drogue (ft)

Drift Main (ft)

Total Drift (ft)

0 0.00 0.00 0.005 327.27 538.86 866.1310 654.55 1077.71 1732.2615 981.82 1616.57 2487.6720 1309.10 2155.42

23464.52

Test Plans and Procedures• Tests–Airship inflation–Airship release from the rocket

Full Scale Flight TestFlight Information

• Motor Used: Cesaroni 1635k445

• Altitude: 2000 ft.

• The rocket was fired without the payload. Bags of sand were used as weights to simulate the payload in the rocket.

Final Payload Design Overview

Payload IntegrationThe main parachute will sit in the top

of the forward rocket body tube and will rest on the airship. Below the airship is a rocket body tube coupler and bulkhead that will serve as a piston to push out the main parachute, airship, and nose cone.

Recovery TestingRecovery System Testing Results

Electronics/EjectionTest1(drogue1) 1.41g(12psi)

Test2(main1) .191g(4psi)

Test3(main2) .286g(6psi)

Test4(drouge2) .469g(4psi)

Interfaces• RC-Airship• RC-Airship Inflation System• RC-Airship Disconnect • Altimeter On/Off Switches

Status of Requirements VerificationRequirements StatusAltitude Pending KE Completed Launch Readiness for 1 hour Completed8 foot long rail CompletedTotal Impulse <2560 n-s Completed10% Ballast Completed½ Scale Flights CompletedDrift Rate CompletedGPS CompletedFull Scale test launch Completed

Basic Funding Plan• Company Sponsorships• Travel est. $6,330• Ask for about $1000 if possible• Major Companies- Timken,

Birdgestone, Ohio Space Consortium, STVM

Project Funding• Timken: $1000• Magni-Power: $250• Ohio Aerospace Institute: $1500• Metallic Resources, Inc. $100• Bridgestone:$1025• STVM:$1000• Therapeutic Associates: $250• NASA: $3700• Expected Total to Date: $8825

Fundraising Methods• Letters sent with flyers and press

release- 30 letter• Phone calls/ emails- made after

letters sent• Presentation to companies• Sponsors listed on website and t-

shirts

Educational Outreach• October 6th- Cub Scout Pack 3206 of

Medina• October 14th- IX Center• November 26th- St. Francis de Sales

School• December 7th- Sacred Heart of Mary

School• December 13th- St. Vincent Elementary• Goal of 100 met• Total of 360 students met so far• More to come?

End