Flight Readiness Review

1
Flight Readiness Review

• MCC Nerd Herd
• Mitchell Community College
• Statesville, NC
• March 18, 2009

2
Outline of Talk

• Specifics of Full Scale Rocket
• Test Plans for Rocket and Payload
• Recovery Tests
• Payload Integration
• Outreach/Financial

3
RockSim Diagram of Rocket

• Note 6.5 static margin (stable)

4
Thrust to Weight Motor Selection

• The thrust to weight for this rocket (L2200 motor
  compared to a 41 lb rocket) is 12.5 to 1
• This is above the minimum threshold for the safe
  flight of our rocket.

5
Rail Exit Velocity

• The rail exit velocity is 56 mph using an 8 ft
  rail. (According to RockSim)
• This is above the minimum of 30 mph for stable
  flight. (rule of thumb)

6
Parachute Sizes and Descent Rates

• Will use a 48 drogue parachute at apogee
• This is due to the weight of the payload
• Need to keep fincan and payload section in
  approximately the same descent plane
• Will prevent fincan entanglement with main
  parachute (seen in full scale test flight)
• Main parachute will be 12 ft in diameter
• Descent rate under main 20 ft/sec

7
Test Plans and Procedures for Rocket

• Full scale test flight completed
• Stable and altimeters performed as expected
• Recovery demonstrated need for drogue parachute
  at apogee
• Ground testing of ejection charges
• Amount was sufficient to separate rocket
• 40 and 50 scale model testing completed
• Rocket design was demonstrated stable
• Skirted payload design made rocket inherently
  unstable

8
Test Plans and Procedures for Payload (Completed)

• Have tested pressure sensor and analog to digital
  board performed as expected
• Have tested diffuser motor for rotation rate and
  torque as a function of voltage performed
  admirably
• Have completed 3D printing of converging/diverging
  duct system
• Have tested Pico-ITX form factor single board
  computer for functionality with sensor
  electronics passed all tests

9
Test Plans and Procedures for Payload (To Do)

• Complete testing of optical encoder for
  determining diffuser rotation rate
• Complete testing of controller electronics for
  changing the rotation rate of the diffuser
• Complete integration of all electronic devices in
  the payload section
• Range testing of the 2.4 GHz Yagi Antennae

10
Full Scale Test Flight and Results

• Flew full scale rocket at Orangeburg, SC, March
  7, 2009
• Rocket was 9.75 ft long, 6 in diameter and 47
  lbs in weight
• Motor for test flight Loki L1482
• Flight was stable and rocket landed under main
• Altitude was 2272 ft agl from Perfectflite MAWD
  and 2456 ft agl (Accelerometer) and 2210 ft agl
  (Barometric) From Loki Arts II.

11
Full Scale Test Flight and Results (cont)

• Rocket was slightly heavier (about 7 lbs) than
  one that will fly at MSFC in April
• After main parachute ejection, fincan was
  momentarily entangled with inflated main
  parachute then disentangled
• Most probably due to payload section too heavy.
  Main parachute bay was pointing straight down
  when the parachute was ejected from the bay.
  Fincan was directly vertical of main parachute
  bay

12
Full Scale Test Flight and Results (cont)

• Altitude much lower than target of 1 mile.
• Expected lower altitude on Loki L1482 vs.
  Aerotech L2200. But not this much.
• Reasons rocket weight, drag of the nozzle
  payload, base drag, rocket length and boundary
  layer drag
• To increase altitude
• Reduce weight
• Shorten rocket
• Small boattail to reduce base drag
• Smoother finish to rocket body

13
Apogee

• Test flight data from Loki ARTS II
• Blue line is from Accelerometer data and yellow
  line is smoothed barometric data

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• The Team (most of them)

Liftoff of OCD!
16

• OCD in Flight

Descent under main
17
Dual Deployment Avionics Test

• MAWD and Loki ARTS II altimeters were not
  independently ground tested with a pressure
  vessel
• Both had worked on previous flights for other
  rockets (dual deployment occurred) and altitude
  results were reasonable
• Altimeters were turned on before integration
  into altimeter bay to determine if working as
  expected. Each passed.
• Both altimeters performed flawlessly.

18
Ejection Charge Amount Test

• Performed ground test for drogue and payload bay
  separation
• Use 3.7 grams of 4F BP with 2 shear pins (2-56
  plastic screws)
• Result separated sections but seemed a little
  weak. Upped BP to 4.5 grams in Test Flight
  ejection charges.
• Results separated rocket as expected but charges
  may have been a little strong from video analysis
  of flight.

19
Payload Integration Feasibility

• Integrating Rocket to Payload
• Payload is effectively the rockets nosecone
• The payload will be attached to the main
  parachute bay using a friction fitted coupler and
  two 2-56 plastic shear pins

20
Payload Integration Feasibility (cont)

• The payload will be completely readied before
  attachment to the rocket.
• After attaching the payload to the rocket,
  turning the electronics and diffuser motor on are
  the only payload tasks left to complete.
• This will occur at the launchpad.

21
Outreach Completed

• Rocket Day
• American Renaissance School
• East Alexander Middle School
• Media Coverage
• Fox 18 News
• Statesville Record Landmark
• MCC Board of Trustees
• Rotary Club Presentation (3)

22
Outreach To Do

• Rocket Days
• Statesville Christian School
• East Iredell Middle School
• Boys and Girls Club
• Cub Scout Camp
• MCC Endowment Board
• MCC Alumni Retreat
• MCC Student Body Presentation

23
Financial and Sponsorships
Outreach 300 Payload 1250 Build/Recovery
2550 TOTAL 4100
24
Financial and Sponsorships

• The team, with much effort, has successfully
  raised enough money to cover our travel expenses
  through
• Food Fundraisers 210.50
• Sponsorships 3600.00
• Personal Donations 700.00
• TOTAL FUNDS RAISED 4510.50

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Conclusion

• Presented rocket specifics
• Discussed test flight of full scale rocket
• Demonstrated payload integration to rocket
• Discussed Outreach and Financial situation of team