St. Vincent St. Mary CDR Presentation NASA Student Launch
Initiative
Slide 2
Final Launch Vehicle Dimensions Length: 123.3748 in Diameter:
5.5512 in Span Diameter: 19.0400 in Mass: 26.49 lbs Center of
Gravity: 77.5333 in Center of Pressure: 85.5750 in Static Margin:
1.58
Slide 3
Rocket Rocksim Drawing
Slide 4
Key Design Features Dual altimeters Payload piston ejection
system Airship inflation system Boat-tail Airship release
system
Slide 5
Final Motor Choice The 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
Mass Statement Our mass margin is zero ( We are overweight) The
rocket weighs about 26.49 pounds. The rocket is at its limit on
weight, any more and it will be hard to reach the expected
eight.
Slide 8
Parachutes and Recovery Harness Main Chute Skyangle Size 7
Recovery Harness Area: 56.8 sq.ftType: Tubular Nylon Mass: 40.9132
ozSize: 5/8 in w x 7 ft l Descent Rate: 13.72 ft/sLength: 70 in
Drogue Chute Cert-3 Area: 6.3 sq.ft Mass: 6.00 oz Descent Rate:
83.61 ft/s
Slide 9
Kinetic Energy Rocket Descent Weight (lbm) Descent Velocity
(ft/sec) KE (ft lbf) 23.413.6167.30
Slide 10
Predicted Drift from the Launch Pad Wind Speed (mph) Drift
Drogue (ft) Drift Main (ft) Total Drift (ft) 00.00
5327.27538.86866.13 10654.551077.711732.26 15981.821616.572598.39
201309.102155.4223464.52
Slide 11
Test Plans and Procedures Tests Airship inflation Video testing
Airship release from the rocket
Slide 12
Scale Model Flight Test The half scale was changed several
times over the past few months. The first version that was built
was flown with a G88 Cessaroni motor. This motor proved to be very
underpowered for the size and weight of the rocket. The rocket shot
up 502ft (stably) and hurtled to earth, just narrowly deploying its
parachute before going into the ground.
Slide 13
Scale Model Flight Test Cont. Logically, a higher-powered motor
was needed. The half-scales next attempt ended with a weathercocked
flight that landed in a tree. The next launch did exactly the same
thing, because of the higher wind speed, the strange trajectory was
repeated.
Slide 14
Final Payload Design Overview
Slide 15
Payload Integration The airship will sit in the top of the
forward rocket body tube and will rest on the main parachute. Below
the main parachute is a rocket body tube coupler and bulkhead that
will serve as a piston to push out the main parachute, airship, and
nose cone.
Slide 16
Piston Ejection Testing
Slide 17
Interfaces RC-Airship RC-Airship Inflation System RC-Airship
Disconnect Video-Ground Station Altimeter On/Off Switches
Slide 18
Status of Requirements Verification RequirementsStatus
AltitudePending KECompleted Launch Readiness for 1 hourCompleted 8
foot long railCompleted Total Impulse