Charybdis - Revision history

Thwhite at 14:48, 15 September 2017

2017-09-15T14:48:38Z

← Older revision		Revision as of 14:48, 15 September 2017
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	[[Category: Daedalus]]		[[Category: Daedalus]]
	[[Category: Rockets]]		[[Category: Rockets]]
			[[Category: Documentation]]

Ddjp42: /* Avionics Teensy Pinout and XBee Transmitter */

2016-04-02T19:39:01Z

Avionics Teensy Pinout and XBee Transmitter

← Older revision		Revision as of 19:39, 2 April 2016
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	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 ==

Calvinlin: /* Avionics and Telemetry */

2016-03-28T08:27:38Z

Avionics and Telemetry

← Older revision		Revision as of 08:27, 28 March 2016
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	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\|~~frame~~\|center\|alt=Avionics Block Diagram~~\|upright=0.6~~\|Avionics ~~block diagram~~]]		[[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 ==

Calvinlin: /* Avionics and Telemetry */

2016-03-28T08:25:42Z

Avionics and Telemetry

← Older revision		Revision as of 08:25, 28 March 2016
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	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\|frame\|center\|alt=Avionics Block Diagram\|upright=0.6\|Avionics block diagram]]

	== Avionics Teensy Pinout and XBee Transmitter ==		== Avionics Teensy Pinout and XBee Transmitter ==

Calvinlin: /* Team Summary */

2016-03-28T08:22:21Z

Team Summary

← Older revision		Revision as of 08:22, 28 March 2016
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	= Team Summary =		= Team Summary =


	Stanford SSI Rockets Team - Charybdis,<br />		Stanford SSI Rockets Team - Charybdis,<br />
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	Avionics Specialist<br />		Avionics Specialist<br />
	djp42@stanford.edu<br />		djp42@stanford.edu<br />


	= Launch Vehicle Summary =		= Launch Vehicle Summary =

Calvinlin at 08:22, 28 March 2016

2016-03-28T08:22:05Z

← Older revision		Revision as of 08:22, 28 March 2016
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	Charybdis is launching an 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 angular velocity ~~to allow~~ uninhibited parachute deployment.		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)

Calvinlin at 08:20, 28 March 2016

2016-03-28T08:20:50Z

← Older revision		Revision as of 08:20, 28 March 2016
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			Charybdis is launching an 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 angular velocity to allow uninhibited parachute deployment.

	{{rocket-project		{{rocket-project
	\| header = Charybdis (ARES-3)		\| header = Charybdis (ARES-3)

Calvinlin at 08:17, 28 March 2016

2016-03-28T08:17:47Z

← Older revision		Revision as of 08:17, 28 March 2016
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	'''Structural Components		'''Structural Components

	'''Avionics		'''Avionics

	'''Recovery		'''Recovery

	'''Motor		'''Motor

	'''Misc. Hardware		'''Misc. Hardware

	[[Category: Daedalus]]		[[Category: Daedalus]]
	[[Category: Rockets]]		[[Category: Rockets]]

Calvinlin at 08:17, 28 March 2016

2016-03-28T08:17:19Z

← Older revision		Revision as of 08:17, 28 March 2016
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	\|}		\|}

			== Budget ==

			'''Structural Components
			'''Avionics
			'''Recovery
			'''Motor
			'''Misc. Hardware

	[[Category: Daedalus]]		[[Category: Daedalus]]
	[[Category: Rockets]]		[[Category: Rockets]]

Calvinlin: /* Vehicle Criteria */

2016-03-28T08:11:57Z

Vehicle Criteria

← Older revision		Revision as of 08:11, 28 March 2016
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	# At apogee, drogue chute deploys		# At apogee, drogue chute deploys
	# Rocket descends and main 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]]		[[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]]
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	The mission will be considered successful if the rocket unit reaches spin stabilization, demonstrates successful de-spin prior to reaching apogee. The rocket must be recovered intact and reusable and pass the L3 certification inspection authorized by Tripoli.		The mission will be considered successful if the rocket unit reaches spin stabilization, demonstrates successful de-spin prior to reaching apogee. The rocket must be recovered intact and reusable and pass the L3 certification inspection authorized by Tripoli.


	== Constraints ==		== Constraints ==