L2 Post-Flight Analyses - Revision history

Thwhite at 14:43, 15 September 2017

2017-09-15T14:43:12Z

← Older revision		Revision as of 14:43, 15 September 2017
Line 188:		Line 188:
	The flight was fairly nominal. Due to a loose friction fit of the nose cone, there was an inertial deployment of the main chute with the drogue at apogee. However, due to low win the drift of the rocket was minimal. In the future, shear pin(s) should be used for a more controlled attachment method.		The flight was fairly nominal. Due to a loose friction fit of the nose cone, there was an inertial deployment of the main chute with the drogue at apogee. However, due to low win the drift of the rocket was minimal. In the future, shear pin(s) should be used for a more controlled attachment method.
	[[Category:Rockets]]		[[Category:Rockets]]
			[[Category:Documentation]]

Johnldean at 21:16, 17 April 2016

2016-04-17T21:16:43Z

← Older revision		Revision as of 21:16, 17 April 2016
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	FLAMOS's avionics coupler was installed upside down causing the main chute to be deployed at apogee. The rocket successfully executed two events which would have qualified the user for Level 2 certification had he been able to recover the rocket after it drifted upwards of 1 mile from the launch site. Cameron did not have a pair of binoculars handy and took his eyes off the rocket approximately 100ft before touchdown to take a bite of his pizza and thus the rocket's landing location could only be approximated to within a quarter mile square area. After approximately 45 minutes of searching for the rocket, the search party decided to give up on the recovery. In the future, all level 2 attempts should be tracked by binoculars and the recovery team should be inside a vehicle ready to begin driving towards the rocket should it start to drift. All rockets should have an audible alarm installed that activated upon liftoff.		FLAMOS's avionics coupler was installed upside down causing the main chute to be deployed at apogee. The rocket successfully executed two events which would have qualified the user for Level 2 certification had he been able to recover the rocket after it drifted upwards of 1 mile from the launch site. Cameron did not have a pair of binoculars handy and took his eyes off the rocket approximately 100ft before touchdown to take a bite of his pizza and thus the rocket's landing location could only be approximated to within a quarter mile square area. After approximately 45 minutes of searching for the rocket, the search party decided to give up on the recovery. In the future, all level 2 attempts should be tracked by binoculars and the recovery team should be inside a vehicle ready to begin driving towards the rocket should it start to drift. All rockets should have an audible alarm installed that activated upon liftoff.


			= MERRILL LYNCH I =
			== Flight Summary ==
			{\|class="wikitable"
			\|'''Date of Flight'''
			\|Apr. 16, 2016
			\|-
			\|'''Launch Location'''
			\|TCC
			\|-
			\|'''L2 Certification Attempt?'''
			\|Yes
			\|-
			\|'''Launcher'''
			\|John Dean
			\|-
			\|'''Recovery Status'''
			\|Successful, No Damage
			\|}

			== Rocket Specs ==
			{\|class = "wikitable"
			\|'''Manufacturer'''
			\|Giant Leap Rocketry Firestorm 54
			\|-
			\|'''Length'''
			\|69"
			\|-
			\|'''Weight'''
			\|5.2 lbs
			\|-
			\|'''Motor'''
			\|Aerotech J270
			\|-
			\|'''On-Board Avionics'''
			\|Featherweight Raven 3, Buzzer
			\|-
			\|'''Recovery'''
			\|Duel deploy 18" drogue, 36" main parachutes
			\|-
			\|'''Payload'''
			\|Airframe-Mounted Camera
			\|}

			The rocket was configured with the drogue chute located in the aft airframe and the forward chute located in the forward airframe with the aft airframe friction fitted onto the avionics bay. The Raven was programmed to fire a charge for the drogue chute at apogee (barometric), a redundant charge at apogee + 2.5 seconds (the time determined by OpenRocket that the rocket would have fallen 100 feet), the main charge at 600 ft, and a redundant charge at 500 ft. Each charge well contained 1.5 g of Pyrodex.

			== Analysis ==
			The flight was fairly nominal. Due to a loose friction fit of the nose cone, there was an inertial deployment of the main chute with the drogue at apogee. However, due to low win the drift of the rocket was minimal. In the future, shear pin(s) should be used for a more controlled attachment method.
	[[Category:Rockets]]		[[Category:Rockets]]

Iangomez at 07:48, 23 March 2016

2016-03-23T07:48:13Z

← Older revision		Revision as of 07:48, 23 March 2016
Line 1:		Line 1:
	~~{{rocket-stub}}~~

	= Cardinal II =		= Cardinal II =
	== Flight Summary ==		== Flight Summary ==

Cameron at 07:16, 23 March 2016

2016-03-23T07:16:39Z

← Older revision		Revision as of 07:16, 23 March 2016
Line 94:		Line 94:

	The data from the Raven can be found on the Google Drive [https://drive.google.com/open?id=0B_7MoD64h5LobGxBaVJxcU8zTUk here]		The data from the Raven can be found on the Google Drive [https://drive.google.com/open?id=0B_7MoD64h5LobGxBaVJxcU8zTUk here]

			= FLAMOS I =
			== Flight Summary ==
			{\|class="wikitable"
			\|'''Date of Flight'''
			\|Feb. 20, 2016
			\|-
			\|'''Launch Location'''
			\|TCC
			\|-
			\|'''L2 Certification Attempt?'''
			\|Yes
			\|-
			\|'''Launcher'''
			\|Cameron Ramos
			\|-
			\|'''Recovery Status'''
			\|MIA
			\|}

			== Rocket Specs ==
			{\|class = "wikitable"
			\|'''Manufacturer'''
			\|Giant Leap Rocketry Firestorm 54
			\|-
			\|'''Length'''
			\|69"
			\|-
			\|'''Weight'''
			\|5.1 lbs
			\|-
			\|'''Motor'''
			\|Aerotech J425
			\|-
			\|'''On-Board Avionics'''
			\|Featherweight Raven 3
			\|-
			\|'''Payload'''
			\|18" drogue, 36" main parachutes
			\|-
			\|}

			The rocket was configured with the drogue chute located in the aft airframe and the forward chute located in the forward airframe with the aft airframe friction fitted onto the avionics bay. The Raven was programmed to fire a charge for the drogue chute at apogee (barometric), a redundant charge at apogee + 2.5 seconds (the time determined by OpenRocket that the rocket would have fallen 100 feet), the main charge at 600 ft, and a redundant charge at 500 ft. Each charge well contained 1.5 g of Pyrodex.

			== Analysis ==
			FLAMOS's avionics coupler was installed upside down causing the main chute to be deployed at apogee. The rocket successfully executed two events which would have qualified the user for Level 2 certification had he been able to recover the rocket after it drifted upwards of 1 mile from the launch site. Cameron did not have a pair of binoculars handy and took his eyes off the rocket approximately 100ft before touchdown to take a bite of his pizza and thus the rocket's landing location could only be approximated to within a quarter mile square area. After approximately 45 minutes of searching for the rocket, the search party decided to give up on the recovery. In the future, all level 2 attempts should be tracked by binoculars and the recovery team should be inside a vehicle ready to begin driving towards the rocket should it start to drift. All rockets should have an audible alarm installed that activated upon liftoff.

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

Rwong: /* Rocket Specs */

2016-03-23T03:16:46Z

Rocket Specs

← Older revision		Revision as of 03:16, 23 March 2016
Line 88:		Line 88:
	\|}		\|}

	The rocket was configured with the drogue chute located in the aft airframe and the forward chute located in the forward airframe with the aft airframe friction fitted onto the avionics bay. The Raven was programmed to fire a charge for the drogue chute at apogee (barometric), a redundant charge at apogee + 2.5 seconds -- the time determined by OpenRocket that the rocket would have fallen 100 feet -- the main charge at 600 ft, and a redundant charge at 500 ft. Each charge well contained 1.5 g of Pyrodex.		The rocket was configured with the drogue chute located in the aft airframe and the forward chute located in the forward airframe with the aft airframe friction fitted onto the avionics bay. The Raven was programmed to fire a charge for the drogue chute at apogee (barometric), a redundant charge at apogee + 2.5 seconds (the time determined by OpenRocket that the rocket would have fallen 100 feet), the main charge at 600 ft, and a redundant charge at 500 ft. Each charge well contained 1.5 g of Pyrodex.

	== Analysis ==		== Analysis ==

Rwong: /* Rocket Specs */ added description of rocket set up

2016-03-23T03:15:54Z

Rocket Specs: added description of rocket set up

← Older revision		Revision as of 03:15, 23 March 2016
Line 87:		Line 87:
	\|-		\|-
	\|}		\|}

			The rocket was configured with the drogue chute located in the aft airframe and the forward chute located in the forward airframe with the aft airframe friction fitted onto the avionics bay. The Raven was programmed to fire a charge for the drogue chute at apogee (barometric), a redundant charge at apogee + 2.5 seconds -- the time determined by OpenRocket that the rocket would have fallen 100 feet -- the main charge at 600 ft, and a redundant charge at 500 ft. Each charge well contained 1.5 g of Pyrodex.

	== Analysis ==		== Analysis ==

Rwong: /* Analysis */ added link to Raven data on google drive

2016-03-23T03:09:43Z

Analysis: added link to Raven data on google drive

← Older revision		Revision as of 03:09, 23 March 2016
Line 45:		Line 45:
	== Analysis ==		== Analysis ==

			The data from the Raven can be found on the Google Drive [https://drive.google.com/open?id=0B_7MoD64h5LoWFVfQW4wYWhaYVE here]

	= JARVIS I =		= JARVIS I =

Rwong: /* Analysis */ added link to raven data

2016-03-23T03:08:44Z

Analysis: added link to raven data

← Older revision		Revision as of 03:08, 23 March 2016
Line 89:		Line 89:
	== Analysis ==		== Analysis ==
	JARVIS I marked the 2nd attempted rocket flight with on-board electronics for the 2015-2016 year. Flight takeoff was nominal, however, at apogee, the drogue parachute did not deploy, nor did the main chute deploy at any lower altitude. Upon recovery, it was determined that the nose cone was ejected, which helped to increase drag substantially so the rocket did not lawn dart but fell laterally instead. The Raven was operational even after recovery, and the data retrieved from the altimeter concurred with the physical evidence that all ejection chargers successfully fired. The most reasonable hypothesis for the parachute ejection failure was that the size of the ejection charges was simply undersized.		JARVIS I marked the 2nd attempted rocket flight with on-board electronics for the 2015-2016 year. Flight takeoff was nominal, however, at apogee, the drogue parachute did not deploy, nor did the main chute deploy at any lower altitude. Upon recovery, it was determined that the nose cone was ejected, which helped to increase drag substantially so the rocket did not lawn dart but fell laterally instead. The Raven was operational even after recovery, and the data retrieved from the altimeter concurred with the physical evidence that all ejection chargers successfully fired. The most reasonable hypothesis for the parachute ejection failure was that the size of the ejection charges was simply undersized.

			The data from the Raven can be found on the Google Drive [https://drive.google.com/open?id=0B_7MoD64h5LobGxBaVJxcU8zTUk here]

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

Rwong at 00:11, 23 March 2016

2016-03-23T00:11:48Z

← Older revision		Revision as of 00:11, 23 March 2016
Line 2:		Line 2:

	= Cardinal II =		= Cardinal II =
			== Flight Summary ==
	{\|class="wikitable"		{\|class="wikitable"
	\|'''Date of Flight'''		\|'''Date of Flight'''
Line 43:		Line 44:

	== Analysis ==		== Analysis ==


	= JARVIS I =		= JARVIS I =

	== Flight Summary ==		== Flight Summary ==
	{\|class="wikitable"		{\|class="wikitable"

Rwong: /* Cardinal II */

2016-03-23T00:11:19Z

Cardinal II

← Older revision		Revision as of 00:11, 23 March 2016
Line 8:		Line 8:
	\|'''Launch Location'''		\|'''Launch Location'''
	\|LUNAR		\|LUNAR
			\|-
	\|'''L2 Certification Attempt?'''		\|'''L2 Certification Attempt?'''
	\|Yes		\|Yes
Line 42:		Line 43:

	== Analysis ==		== Analysis ==


	= JARVIS I =		= JARVIS I =