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no edit summary
Charybdis is launching an passive ascent spin stabilization rocket with the use of canted fins. Prior to apogee, the rocket will implement a yo-yo de-spin unit to halt the rocket's angular velocity for uninhibited parachute deployment.
{{rocket-project
{{rocket-project
| header = Charybdis (ARES-3)
| header = Charybdis (ARES-3)
= Team Summary =
= Team Summary =
Stanford SSI Rockets Team - Charybdis,<br />
Stanford SSI Rockets Team - Charybdis,<br />
Leland Stanford Junior University<br />
Leland Stanford Junior University<br />
Stanford, CA<br />
Stanford, CA<br />
Ian Gomez<br />
'''Ian Gomez<br />
Project Manager<br />
Project Manager<br />
iangomez@stanford.edu<br />
iangomez@stanford.edu<br />
Calvin Lin<br />
'''Calvin Lin<br />
Team Lead<br />
Team Lead<br />
calvinlin@stanford.edu<br />
calvinlin@stanford.edu<br />
William Alvero Koski<br />
'''William Alvero Koski<br />
Structural Integration Analyst<br />
Structural Integration Analyst<br />
walverok@stanford.edu<br />
walverok@stanford.edu<br />
Navjot Singh<br />
'''Navjot Singh<br />
De-spin Specialist and Senior Advisor<br />
De-spin Specialist and Senior Advisor<br />
navjot@stanford.edu<br />
navjot@stanford.edu<br />
Derek Phillips<br />
'''Derek Phillips<br />
Avionics Specialist<br />
Avionics Specialist<br />
djp42@stanford.edu<br />
djp42@stanford.edu<br />
= Launch Vehicle Summary =
= Launch Vehicle Summary =
The objective of Charybdis is to demonstrate spin stabilization and de-spin of a rocket using canted fins and a de-spin unit.
The objective of Charybdis is to demonstrate spin stabilization and de-spin of a rocket using canted fins and a de-spin unit.
==Flight Events Overview==
# Canted fins induce spin during launch
# Before apogee, de-spin unit stops rocket’s spin
# At apogee, drogue chute deploys
# Rocket descends and main chute deploys
[[File:Events_Diagram-2.jpg|thumb|alt=A summary of the rocket's intended flight actions|Charybdis Rocket Events|upright=0.9|right|Flight Events Sequence]]
== Success Criteria ==
== Success Criteria ==
The reason the yo-yo de-spin was favored is because the unit does not require any calculations of initial angular velocity in order for the de-spin to halt the angular velocity. Rather, the only calculations required are the lengths of the two strings that wind around the airframe and the mass of the weights.
The reason the yo-yo de-spin was favored is because the unit does not require any calculations of initial angular velocity in order for the de-spin to halt the angular velocity. Rather, the only calculations required are the lengths of the two strings that wind around the airframe and the mass of the weights.
{{multiple image|caption_align=center
| width = 100
| footer = Final design of de-spin unit
| image1 = De_spin1.png
| alt1 = Aerial view
| caption1 = Aerial view
| image2 = De_spin2.png
| alt2 = Back view
| caption2 = Back view
| image3 = De_spin3.png
| alt3 = Close up view
| caption3 = Close up view
}}
= Avionics and Telemetry =
= Avionics and Telemetry =
In the forward airframe, the rocket will be split into the forward airframe avionics bay, herein referred to as the main avionics bay, and the aft airframe avionics bay, herin referred to as the secondary avionics bay. The main avionics bay will collect sensor information and communicate mission critical parts with the ground station. The unpressurized section is for the altimeter which will deploy the main parachute. The secondary avionics bay will contain an altimeter that controls the de-spin unit and drogue chute.
In the forward airframe, the rocket will be split into the forward airframe avionics bay, herein referred to as the main avionics bay, and the aft airframe avionics bay, herin referred to as the secondary avionics bay. The main avionics bay will collect sensor information and communicate mission critical parts with the ground station. The unpressurized section is for the altimeter which will deploy the main parachute. The secondary avionics bay will contain an altimeter that controls the de-spin unit and drogue chute.
[[File:Block_Diagram.png|image]]
[[File:Block_Diagram.png|thumb|center|upright=2.0|alt=Avionics Block Diagram|Avionics Payload Diagram]]
== Avionics Teensy Pinout and XBee Transmitter ==
== Avionics Teensy Pinout and XBee Transmitter ==
In the main avionics bay, a Teensy 3.2 microcontroller will communicate with an XBee 9B 900 Mhz 250MW radio transmitter. The XBee will have a rubberduck RPSMA antenna and communicate information to the ground station in real time. There will be an Adafruit 9DoF sensor providing acceleration, velocity, and orientation information to the Teensy, which will store the data. Parts of the data, such as orientation, that are deemed mission critical will be transmitted through the XBee to the ground station. Everything described above will be connected to a single battery, an Anker Astro E1 5200mAh Portable usb battery pack and have an estimated maximum power consumption of 2 Watts.
In the main avionics bay, a Teensy 3.2 microcontroller will communicate with an XBee 9B 900 Mhz 250MW radio transmitter. The XBee will have a rubberduck RPSMA antenna and communicate information to the ground station in real time. There will be an Adafruit 9DoF sensor providing acceleration, velocity, and orientation information to the Teensy, which will store the data. Parts of the data, such as orientation, that are deemed mission critical will be transmitted through the XBee to the ground station. Everything described above will be connected to a single battery, an Anker Astro E1 5200mAh Portable usb battery pack and have an estimated maximum power consumption of 2 Watts.
[[File:Teensy.jpg|220px]]
[[File:adafruit9DOF.jpg|220px]]
[[File:XBEEPro.jpg|150px]]
== APRS Transmission ==
== APRS Transmission ==
|}
|}
== Budget ==
'''Structural Components
'''Avionics
'''Recovery
'''Motor
'''Misc. Hardware
[[Category: Daedalus]]
[[Category: Daedalus]]
[[Category: Rockets]]
[[Category: Rockets]]
[[Category: Documentation]]