Atomic AggiesCDR

Final Launch Vehicle Dimensions

Diameter 5.5”Overall length: 117.14 inchesApproximate Loaded Weight: 34.36 lb.

Key design features

5.5” Blue Tube3-3/8 Fiberglass reinforced birch plywood fin set

Ogive polycarbonate nosecone

Final motor choice

Manufactory EngineClass/Model

Diameter (mm)

Length (in)

Burn Time (s)

Impulse (N-s)

Avg. thrust(N)

RockSim Altitude (ft.)

Cesaroni Technology

L800 75 19.1 4.68 3722 795.5 5743

Rocket flight stability in static margin diagram

Thrust-to-weight ratio and rail exit velocity

Kinetic energy at key phases of the mission, especially landing

Parachute Velocity at Deployment (ft./s)

Landing Velocity (ft./s)

Kinetic Energy During Descent (ft-lb)

Kinetic Energy Upon Landing (ft-lb)

Drogue 57.27 ft/s   Section 1 - 365.5 ft-lbSection 2 - 331.04 ft-lbSection 3 - 651.89 ft-lb 

 

Main 75.729 ft/s 18.66 ft/s   Section 1 - 37.85 ft-lbSection 2 - 35.14 ft-lbSection 3 - 69.2 ft-lb 

Test plans and proceduresFull scale test launch:

1st test launch is planned for Febuary 16Data Analysis

Planning for 2nd test launch

Parachute sizes, recovery harness type, size, and lengthDrogue Parachute:Elliptical Custom24” diameterDecent Rate: 75 ft/s

Main Parachute:Iris Ultra96” diameterDecent Rate: 16.53 ft/s

Recovery harness will be 27’ of ½” tubular nylon.

Avionics Bay

Predicted drift from the launch pad

Wind speed Drift

0-2 MPH 0 Ft’

3-7 MPH 133.02445’

8-14 MPH 367.30896’

15-25 MPH 686.55649’

Final payload design overviewThe payload will incorporate sensors that will be used to measure solar irradiance, ultraviolet radiation, atmospheric pressure, temperature, and humidity once apogee is reached by our rocket. The payload bay will contain one camera taking video throughout the duration of the flight, where still shots will be obtained of the horizon. The payload will include a GPS unit to provide spatial data and to provide a tracking unit to aid in vehicle recovery. A DE0- Nano FPGA Development and Education Board will be used to control data collection operations and provide data logging. Data will be sampled and stored at a frequency of 1Hz starting at apogee until ten minutes after landing. The data will be transmitted wirelessly from the vehicle to a ground receiving station where it will be stored and processed on a personal computer.

Payload Integration/Testing

Top is the DE-0 Nano board connected to the seven segment module for testing, and to the right is the PCB with temperature, pressure, and humidity sensors soldered on. The seven segment display above shows what channel (sensor) is being displayed along with the converted analog value. To display this data we also converted the digital measurements to HEX values for testing purposes making sure we are receiving the correct data information.

InterfacesThe scientific payload will be independent of

recovery electronics so that there is no interference between the two systems.

The DE-0 Nano microcontroller will be used to take analog readings given from five specific atmospheric

Strato-Logger Altimeter on board the payload to trigger the data collection at apogee.

Data stored on the FPGA board will be transmitted to the receiver at the ground station.

Status of requirements verification

DesignBuilding process of full scale rocket

has begun with about 30% completion.

PayloadSensors have been interfaced to the

FPGA and ongoing testing is still being done

Questions from Panel?