CDR

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FRR
FRR
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The Krueger SLI team will launch a rocket a
mile high and sample the ozone concentration at
various altitudes during descent. Once the data
is recovered it will be compared with ground
level concentration.
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Changes Since CDR

• Changes made to Vehicle Criteria
• The total rocket length is now 100 inches instead
  of 78.8 inches to make it more compatible with
  the payload.
• We are also changing the motor back to a K550W.
  Since we added fiberglass to the airframe and the
  extra length of the rocket the computer
  simulations call for the larger K550 to reach the
  desired height of one mile
• Changes made to Payload Criteria
• In order to accommodate the electronic package
  needed for the ozone experiment we had to extend
  the payload section of the rocket.
• To save space we put the ozone sensor package and
  the CanSat system on one side of the payload
  platform and the two altimeters on the other.
  The actual ejection charges are placed outside of
  either bulkhead so they will not interfere with
  the operation of the altimeters or the other
  electronic systems.
• Changes made to Activity Plan
• The teachers and students gave a TARC/SLI
  presentation to the parents and students of
  Wilderness Oaks Elementary during their School
  Math and Science Night.
• Due to a death in the family Astronaut John Blaha
  had to reschedule his visit later this spring.
• Peter Bella, an Environmental Engineer, from the
  Alamo Area Council of Governments (AACOG) gave a
  presentation about causes in ozone concentration
  levels to several of the 8th grade students on
  March 14. During the presentation Mr. Bella
  provided relevance to the project by suggesting
  our rocket be used to confirm AACOGs ozone
  concentration computer models and predictions.

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Mark Twain Atmospheric Sounding Rocket Design
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Rocket Flight Stability
Rocket Stability Margin CG Location is 28.3994
in CP Location is 81.5712 in The Mark Twain Is
over stable by a margin of 4.93
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Motor Selection Comparisons
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Altitude RockSim Data
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Acceleration RockSim Data
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Velocity RockSim Data
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Parachute Sizes and Descent Rates

• Dual Deployment System
• 28 in. drogue parachute
• 72 in. main parachute
• Velocity at Landing 19.7642 ft/s

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Launch Guide Data

• Launch guide length 72.0000 in.
• Velocity at launch guide departure 54.4888 ft/s
• The launch guide was cleared at 0.116 Seconds
• User specified minimum velocity for stable
  flight 43.9993 ft/s
• Minimum velocity for stable flight reached at
  25.0143 in.

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Test Plans and Procedures

• Altimeter Testing
• Reduce the air in the chamber until the altimeter
  reaches around 6000 ft.
• Altimeter will fire the first charge.
• Put back the air until the altimeter reaches 750
  ft.
• The second charge will fire.
• This was accomplished March 20, 2008.
• Recovery System Testing
• Put the rocket together and strap down the
  payload section to a table or a
• sawhorse.
• The altimeter will still be in the vacuum chamber
  so we can test the
• parachute recovery system.
• The safe distance will be 10 ft. from the rocket.
  
• The bottom of the rocket will separate from the
  payload section to its full
• length of the shock cord.
• Ozone data logger will turn on.
• Main parachute will come out of the nose section
  to its full length.
• This was accomplished March 20, 2008.
• All of this will be supervised by a certified
  level 3 NAR mentor.

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Dual Deployment Avionics Test and Ejection Charge
Amount Test
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Payload Assembly
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Ozone Sensor Testing
AACOG Sensor
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Payload Design
Datalogger
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Payload Integration

• Payloads (control, scientific, and recovery) will
  be mounted on an assembly designed to slide in
  and out of the rocket airframe.
• Assembly will be constructed of wood, fiberglass
  cloth, and Epoxy and consist of two cylindrical
  disks at the ends, with a 2-sided, flat mounting
  surface spanning the length between the ends.
• Two cylindrical disks will be constructed such
  that they are snug with the inner diameter of the
  airframe to prevent movement during flight, but
  will still be able to be removed as a single unit
  when disassembling the rocket.
• Payloads will be mounted to the flat surface
  using shock mounts to minimize the stresses
  transmitted to the payloads during lift-off and
  landing.
• All electrical interconnects will be secured in a
  way to provide adequate stress relief while
  preventing inadvertent disconnects.
• Air flow to the ozone sensor will be achieved by
  a drilling a small hole in the airframe.
• The hole will also serve as the air pressure
  source for the altimeter.

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Mark Twain Scale Model
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Scale Model Time vs. Altitude
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Scale Model Time vs. Acceleration
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Scale Model Time vs. Thrust
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Scale Model Time vs. Velocity
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Safety

• The Krueger SLI team follows all safety
  precautions and directions provided in the MSDS
  sheets for potentially hazardous material used
  during rocket construction.

The Safety Officer for the SLI team is Kirsten
(KC) Casteel.