The mission includes development of standardized payload subsystems and manuals that facilitate increasingly complex future payloads and the maximum transfer of corporate knowledge to future student participants. Additionally, the mission will provide opportunities for students to design, implement, and test innovative systems through hands-on experience and collaboration between disciplines, universities and practicing aerospace engineers and scientists.

Nosecone

The nosecone is made of fiber glass which if RF transparent

Payload Frame

The payload frame consists of 4 longerons and 5 decplates. The deckplates provide mounting area for the SRP4 electronics, and the longerons hold these deckplates in place.

Deckplates

Each aluminum deckplate provides a mounting structure for payload electronics

Longerons

The longerons form the mechanical frmae that hodls the deckplates together

Umbilical Block

The umbilical block allow access to electrical connections inside the payload tube.

Dragplate

Radex Joint

Parachute Deckplate

The parachute deckplate attaches the parachute to the payload tube

Parachute Recovery

The parachute recovery system ewill lower the payload without damaging it. The recovery system consists of a drag plate, a 6 ft guided surfacr drogue chite and a 33 foot cross main chute.

Separation System

Flight Computer

The flight computer samples the analog output voltage from the data producing instruments on the palyoad. Then it makes data packets form this info and sends these packets to the transmitter.

S-band TX

The S-band transmitter sends all data collected by the rocket to a data archive station on the ground via four externally mounted patch antennas.

Patch Antennas

The patch antennas convert the output signal form the S-band transmitter into electromagnetic waves that propagate from the rocket to the receiving station on the ground.

Power Splitter

The power splitter evenly distributes power from the transmitter into four patch antennas.

EED Board

The EED board electronically activates the pyrotechnic devices required to separate the motor from the payload adn to deploy the parachute recovery system.

GPS

The GPS determines the rocket's position and sends this data to the flight computer

Accelerometer

The accelerometer board measures x,y, longitudinal, radial, and tangential accelerations and sends them to the flight computer.

Flight Instrumentation Board

The flight instrumentation board contains a pressure sensor, an ambient temeperature sensor, and a thermocouple for measuring payload skin temperature.

Sun Attitude Sensor

The sun sensor, designed and fabricated by students at Tokai University, provides payload and attitude data.

Power Board

The power board converts the voltage level from the battery pack into the voltage levels required by the cicuit board used on the payload.

Battery Pack

The battery pack provides power for all the electrical components of the rocket.

Magnetometer

The 3-axis magnetometer, fabricated by students at Tokai University, is used for attitude determination and detecing perturbations in the magnetic field caused by current systems in the plasma.

Radio Receivers

The radio receivers in conjunction with the loop antenna will be used to determine the plasma cutoff frequenncy. This provides a calibation point to reference the relative measurements from the probes.

Ion and Electron Probe

The probes will be used to map the relative ion and electron densities in the D-Region of the ionosphere

Power Cables

Shielded data cables transfer analog data from the flight computer for sampling.

Anti-aliasing Filters

The anti-aliasing filters prevent the sampled data from being corrupted by alaising