Presenters - Lion Tech Rocket Labs

Report
Critical Design Review
02/02/ 2012
Project Phoenix 2011-2012
The Pennsylvania State University
1
Presenters
•
•
•
•
•
•
•
•
•
•
•
Russell Moore – Project Manager
Brian Taylor – Systems Engineer
Matt Hanna – Structures & Aerodynamics Lead
Tony Maurer – Structures & Aerodynamics Lead
Heather Dawe – Propulsion Lead
Rob Algazi – Propulsion Lead
Adam Covino – Payload Lead
Brian Lani – Payload Lead
Eric Gilligan – Avionics & Recovery Lead
Lawrence Digirolamo – Avionics & Recovery Lead
Tom Letarte – Safety Officer
2
Discussion Topics
•
•
•
•
•
•
•
•
Overview
Structures & Aerodynamics
Avionics & Recovery
Propulsion
Payload
Safety and Quality Assurance
Outreach
Conclusion
3
Overview (Project/Vehicle)
• Rocket is 92.2” in length, 4.5” in diameter (OD)- 4.375” (ID)and weighs 29 lbs.
• Uses machined fin brackets, motor retainer and tail cone.
• Recovery System is Single Ejection (CO2)/Dual Deployment
4
Fin Bracket
• Allows for easy replacement
of damaged fins
• Allows experimentation of fin
design (to alter the CP and
therefore Static Stability)
• CNC machined aluminum
– No epoxy or other permanent
bond
• Screws into fin and through
body tube
5
Motor Retainer
• Machined Aluminum
forward motor retainer
• Attaches to motor
casing
• Screwed into airframe
– No epoxy or other
permanent bonds
• Acts as an Av bay aft
bulk plate
6
Tail Cone
• CNC machined aluminum
aft motor retainer
• Reduces drag up to 50% for
subsonic flight [1]
• Threads onto aft of booster
section
– No epoxy or other
permanent bonds
• Opens up more room in
airframe
7
Structures
• Rocket Flight Static Stability
– 1.4
3000
2500
Predicted Drift (ft)
• Current Simulated Mass: 29.3
pounds
• Mass Margin: 2.6 pounds
• Predicted Drift
2425
2000
1500
1480
1000
930
500
425
0
0
5
10
15
20
25
Wind Speed (mph)
Predicted drift as a function of wind speed for the current
mass estimate (483 ounces).
8
Propulsion
• Motor choice: AMW L777
• Thrust-to-weight ratio: 5.96
(average)
• Rail exit velocity: 55.25 ft/s
9
Propulsion
Full Scale Motor: Animal Works L777 (75mm)
• Determined By Open Rocket Models
10
Propulsion
Sub-Scale Motor: Aerotech J315 (54mm)
• Determined By Open Rocket Models
11
Propulsion
Full Scale Contingency Motor: Cesaroni L935
12
Propulsion
Full Scale Contingency Motor: Cesaroni L935
13
Avionics & Recovery
– Main Parachute: Fruity Chutes 84” Iris
Ultra
– Drogue Parachute: Rocketman 3’
Ballistic Mach II Chute
– Recovery Harness: 50’ of ½” tubular
Kevlar
– Altimeters: 2x PerfectFlite
StratoLogger
– Down-body Camera: PD80
– Recovery Aids:
• Garmin Astro DC-20 GPS System
• BeepX Sonic Beacon
14
Avionics & Recovery
Sled and Bay Design
BeepX Sonic Beacon
Altimeters
Switches
9V Battery
Holders
BP Ejection Canister
BeepX 12V
23A Battery
CO2 Canister
CD3 Ejection
System
Note: Aft Bulkhead is actually an aluminum bulkhead that interfaces with the motor casing and screws into the airframe
15
Avionics & Recovery
–Apogee
• CD3 CO2 ejection device
• Black powder ejection charge
• Drogue is released and main is
held within the airframe by the
main parachute containment
harness.
–750 ft AGL
• Tender Descender releases the
main and the drogue pulls it out
of the airframe and deployment
bag
16
Avionics & Recovery
– Descent Rate
• 64 ft/s under drogue
• 15 ft/s under main
– Kinetic Energy
• Booster Section: 73.8 ft-lbs
• Nosecone/Payload: 15.6 ft-lbs
Avionics & Recovery
– Altimeter test
• Tested functionality of
altimeters and ability to fire
e-matches
– CD3 independent test
• Tested stand-alone
functionality of CD3 system
– Sub-scale ground test
• Tested the ability of the
CD3 system to eject the
nosecone
18
Payload
NASA SMD Mission Payload:
• Measure atmospheric parameters
• Will collect following data:
–
–
–
–
–
Pressure
Temperature
Relative Humidity
Solar Irradiance
Ultra-violet Radiation
Payload
900MHz
Transmitter
Power
Supply
HASB
HASB
Arduino
Control
Arduino
Control
Light
Sensor
Power
Supply
Light
Sensor
Name
Data
Logger
Data
Logger
Model
Ultra-Violet Light Sensor
SU-110
Logomatic v2 Serial SD Datalogger
WIG-10216
Arduino Pro 3.3V/ 8Mhz
DEV-09221
Polymer Lithium Ion Battery - 2000mAh
PRT-08483
XBee Pro 900 XSC Wire Antenna
WRL-09085
4GB microSD Card
SDSDQ-4096-E11M
High Altitude Sensing Board
SEN-09944
~Ambient Light Sensor
TEMT-6000
~Humidity Sensor
HIH-4030
~Pressure Sensor
BMP-085
~Accelerometer
ADXl345
~Temperature Sensor
TMP-102
Quantity
2
2
2
2
1
2
2
2
2
2
2
2
Payload
Payload
Scientific Value:
• Analyze collected information to
profile atmospheric boundary
layer
• Determine stability and depth of
atmospheric boundary layer
• Construct a Skew-T diagram of the
boundary layer as visual aid to
determine weather severity
[www.met.psu.edu]
Safety & Quality Assurance
• CO2 Canisters for
CD3 System
Pressure vs %Fill for varying Temperature
– Manufactured to
UL1191 Standard
– Burst pressure:
7000psi
– 75% Fill
– 30 min @ 100 ⁰C,
15min @ 150 ⁰C
23
Safety & Quality Assurance
Subsystem
Component
Verification
Test
Shear Pins
Ground Testing (Feb.)
Forward Motor
Retainer
Static Fire (Feb.)
Avionics & Recovery
Recovery System
Ground Testing (Feb.)
Propulsion
Motor
Static Fire (Feb.)
Structures
24
Upcoming Milestones
• Verification Testing as in explained in
Appendix D: Test Matrix (February)
• MDRA Launch (March 10-11)
• METRA Launch (March 24)
• FRR (March 26)
25
Educational Engagement
• Discovery Space Museum Workshops
– January 27, February 8 & 22, March 21
• Spikes Fest
– February 12
• Park Forest Middle School STEM Fair
– March 14
26
Expenses
Full Scale Rocket Expenses by Subsystem
Overall Club Expenses
Section
Total
Full Scale
$
4,546.23
Subscale
$
2,612.09
Testing
$
1,040.66
Ground Support Equipment $
2,461.91
Travel
$
3,815.00
Outreach
$
248.98
Total
$ 14,724.87
Subsystem
Structures & Aerodynamics
Avionics & Recovery
Payload
Propulsion
Total
$ 1,853.99
$ 975.31
$ 1,266.93
$ 450.00
Total
$ 4,546.23
27
Conclusion
• Tests show that rocket is structurally sound
and ejection/internal circuitry works.
• Further testing for drogue parachute size,
landing radius distance, and motor
performance.
28
References
[1] Fleeman, l.E., Tactical Missile Design – Second Edition,
American Institute of Aeronautics and Astronautics, Inc.,
VA 2006
[2] www.fruitychutes.com
[3] www.apogeerockets.com
[4] www.met.psu.edu
[5] www.wildmanrocketry.com
[6] www.pro38.com
[7] www.giantleaprocketry.com
[8] www.eurorocketry.org
29

similar documents