Transcript Flight Readiness Review Atomic Aggies Final Launch Vehicle Dimensions  Diameter 5.5”  Overall length: 117.14 inches  Approximate Loaded Weight: 35.25 lb.

Flight Readiness Review
Atomic Aggies
Final Launch Vehicle Dimensions
 Diameter 5.5”
 Overall length: 117.14 inches
 Approximate Loaded Weight: 35.25 lb.
Key Design Features of launch
vehicle
 5.5 “ Blue Tube Fiber glass reinforced
 3 (3/8”) Birch Plywood fin set
 Ogive polycarbonate nosecone
 Electronic Bay contains 3 ports for external data
acquisition (solar irradiance, UV and video)
Motor Description
 Cesaroni Technology L800 Reload
 Propellant Weight: 63.3 oz.
 Average Thrust: 804 N
 Total Weight: 123.8 oz.
Rocket flight stability in static
margin diagram
 CP: 92.65 inches
 CG: 69.84 inches
 Stability Margin: 4.13
Overstable
Launch thrust-to-weight ratio and
rail exit velocity
 Exit Rail Velocity from RockSim: 57.1 feet/sec.
Mass statement
 Met mass predictions for design
 Maintained vehicle weight to 440 oz.
 Mass growth since CDR 6%
Parachute sizes, recovery
harness type, size, and length
Drogue Parachute:
 Classic Elliptical
 24” diameter
 Decent Rate: 53.91 ft/s
Main Parachute:
 Iris Ultra
 96” diameter
 Decent Rate: 5.34 ft/s
Recovery harness will be 27’ of ½” tubular nylon.
Kinetic energy at key phases of the
mission
Parachute
Velocity at
Deployment
(ft./s)
Landing
Velocity
(ft./s)
Drogue
49.5
Kinetic Energy
Upon Landing
(ft-lb)
Section 1 – 333.5
Section 2 – 300.1
Section 3 – 606.98
0
Main
Kinetic Energy During
Decent
(ft-lb)
5.34
Section 1 – 3.27
Section 2 – 2.94
Section 3 – 5.955
Predicted drift from the launch pad
with a 5-,10-,15-,20-mph wind
Wind
Predicted Drift
5 MPH
340.845 MPH
10 MPH
682.155 MPH
15 MPH
1023 MPH
20 MPH
1362.45 MPH
Test plans and procedures
 Full scale test launch:
 1st test launch took place February 16th
 2nd and 3rd test launch took place on March 17th
Full-scale flight test
Altitude vs. time
Feburary 16th
March 17th
Recovery system tests
 Altimeter check - Simulation of altitude by changing the
pressure in jar.
 Wiring test – check for continuity by shorting leads on
terminal
 Ground test – test ejection charges and shear pins
Summary of Requirements
Verification (Launch vehicle)
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1 dedicated altimeter for scoring
Maximum velocity is 52% of Subsonic (589.64 ft./sec.)
Peak Altitude is 5277.8 ft.
Rocket is recoverable and reusable containing 3 independent sections
Assembled and prepared vehicle in 1 hr. 20 mins during 2 test flights
Tested on board components and have remained flight ready for 2.3
hours
Launch Vehicle is designed to fit on 8’ x 1” rail and launched by a 12 V
ignition system w/o external support
Cesaroni L800 is a reloadable motor
Total impulse is 3757 Ns
3.4% of design is Ballast
Vehicle design construction costs has maintained under $5,000
Payload design and dimensions
 The scientific payload and components will be
mounted on a 5.36” x 18” piece of ½” ply board.
 Blue-Tube coupler material split lengthwise around
the payload making a 5.36” diameter
Payload integration
 The payload will be encased in a blue tube coupler that
will be cut to fit inside of the air frame allowing for
easy access to the internal components.
 The payload bay will be integrated into the rocket
body by sliding it in the air frame and held in place by
a piece of blue tube cut to the radius of 2.68” place
below the payload inside of the air frame.
 The payload will be aligned with a hole on the exterior
of the airframe for the HD video camera.
Interfaces with ground systems
 GPS – The GPS system is the BRB900 TX/RX Base GPS
Telemetry system operating at 900MHz. The data will
be received by a LCD hand held receiver and Smart
Data Controller connected to the ground station
computer.
 Transmitter/Receiver – The Xbee Pro 900 transceiver
will transmit and receive the stored data from the DE0
– Nano board to the ground station.
Summary of requirements
verification (payload)
 The payload measures solar irradiance, ultraviolet
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radiation, atmospheric pressure, temperature, and
humidity .
The payload contains one camera taking video throughout
the duration of the flight.
The payload includes a GPS unit to aid in vehicle recovery.
Data will be sampled and stored starting at apogee until
ten minutes after landing.
The data will be transmitted wirelessly to a ground
receiving station and stored on a personal computer.
Questions from Panel?