1. Critical Design Review
Heavens Bound Halibut (HBH)
February 8, 2012

2. Changes Made Since PDR Changes made to vehicle criteria:
Rocket is 133 inches
The main parachute and drogue parachute have switched places.
Payload is located in the nose cone.
Rocket separates into four pieces
Fuselage weighs lbs
ACDS separated from parachute deployment
ACDS controller switched to BeagleBone
Changes made to payload criteria:
None
Changes made to activity plan:

3. Budget Description Cost Number Sub Cost Running Tally
Fiberglass Nosecone, 24/6
$99.95 1
Bluetube Body 6", length 48"
$66.95 3
$200.85
$300.80
Blue Tube 54mm
$23.95
$324.75
Thrust Ring Retainer, 54mm
$40.00
$364.75
1/2" 9-Ply Birch Centering Rings, 54mm
$8.67
$26.01
$390.76
1/2" 9-Ply Birch Bulkhead Plates
$6.34 4
$25.36
$416.12
20 ft. Rocketman Main Parachute
$300.00
$716.12
5 ft. Rocketman Drogue Parachute
$45.00
$761.12
L2200G-P reload kit (propellant)
$280.00
$1,041.12
RMS-75/5120 reload casing
$520.00
$1,561.12
Carbon fiber kits
$143.90
$1,705.02
Stratologger
$69.99
$279.96
$1,984.98
GPS Tracker
$2,284.98
linear actuator
$400.00
$2,684.98
processor
$100.00
$2,784.98
air speed sensor
$50.00
$2,834.98
analog device IMU sensor
$900.00
$3,734.98
siren
$60.00
$3,794.98
rocket beeper
$12.95
$3,807.93
XL Variable-Capacity Ejection Canister
$9.99
$29.97
$3,837.90

4. Timeline February 1st -30th: Component testing
February 3rd -28th: Rocket Assembly
February 14th – March 26th: Full Scale Launch
February 14th – March 24th : Parachute Tests
March 26th: Deliver FRR on Website

5. Gross Liftoff Weight (lb)
33.000
24.000
18.000
21.000
37.000
Vehicle Dimensions
Payload
Vehicle Properties
Diameter (in) 6
Length (in)
133
Gross Liftoff Weight (lb)
54.65
Launch Rail Size (in)
1.0
Motor Retention
thrust ring
Electronics and ACDS

6. Fins

7. CP and CG analysis
The center of pressure (CP) is located inches from the nose cone.
The center of gravity (CG) is located inches from the nose cone.
The stability margin has increased to 1.83.
Total Mass (Lbs)
54.64
Nose Cone
0.22
Payload
1.5
Parachute Bays
4.34
Main Parachute
8.14
Drogue Parachute
5.57
ACDS Tube
17.25
Motor Tube
17.62

8. Flight Simulations

9. Scale Model Results

10. FROSTE System Risk Matrix
Technical
Schedule
Likelihood Categories
5 Very High
No understanding of design or no experience implementing similar designs.
 No one is working on the subsystem
4 High
Little understanding of design or little experience implementing similar designs
 Only one student working on this who will graduate before it is expected to be done.
3 Moderate
Some understanding of design or some experience implementing similar designs
Only one student working on this who has many classes this semester.
2 Low
Great understanding of design or good experience implementing similar designs
 There are two (or more students working in this
1 Very Low
Previously implemented design or extensive experience implementing similar designs
 Subsystem almost done and a clear path to finalization is determined
Consequence Categories
Risk Type
1 Very Low
2 Low
3 Moderate
4 High
5 Very High
Technical
No impact to full mission success criteria
Minor impact to full mission success criteria
Moderate impact to full mission success criteria. Minimum mission success criteria is achievable with margin
Major impact to full mission success criteria. Minimum mission success criteria is achievable
Minimum mission success criteria is not achievable
Schedule
Negligible or no schedule impact
Minor impact to schedule milestones; accommodates within reserves; no impact to critical path
Impact to schedule milestones; accommodates within reserves; moderate impact to critical path
Major impact to schedule milestones; major impact to critical path
Cannot meet schedule and program milestones
Cost
<2% increase over allocated and negligible impact on reserve
Between 2% and 5% increase over allocated and can handle with reserve
Between 5% and 7% increase over allocated and can not handle with reserve
Between 7% and 10% increase over allocated, and/or exceeds proper reserves
>10% increase over allocated, and/or can’t handle with reserves
Goddard Space flight center 5x5 risk matrix
High Risks
Moderate Risks
Low Risks

11. FROSTE System: Risk AnalysisH O D
Trend
Rank
App
Risk Title  1 M
Development Delays 2
Motor Shipping Issues  3
Funding 4 A
Material Acquisition 5 W
Facilities Schedule Conflicts  6
Student Schedule Conflicts 7 R
FAA Waiver Issues 5 4 3 2 1 1 2 4 3 7 6 5
CONSEQUENCES
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month 11

12. Component testing The testing will be done in house
Blue tube and carbon fiber are the primary materials
The materials will have four tests: compression, tensile, torsion, and bending.
The ACDS linkages will be compressed to find point of highest strength vs. weight

13. Physical Payload Integration
Payload is in P-POD shell
Slides into nose cone
Secured by 8 quarter inch bolts

14. Payload
The Alaska Research CubeSat (ARC)

15. ARC Mission Objectives
Education Mission Objective 1 (EMO1): Provide an authentic, interdisciplinary, hands-on student experiences in science and engineering through the design, development, operation of a student small satellite mission.
Science Mission Objective 1 (SMO1): Characterize thermal and vibration environment inside the launch vehicle from ignition to orbit insertion.
Science Mission Objective 2 (SMO2): Validate a novel low power Attitude Control and Determination Systems (ACDS).
Science Mission Objective 3 (SMO3): Validate a high bandwidth communication system by obtaining images of changing snow/ice coverage in arctic regions.

16. ARC Launch Environment Data Logger (LEDL): Risk Analysis
Trend
Rank
App
Risk Title  1 R
Launch Detect 2 W
Software / testing  3 A
Memory 4
M / R
Sensor Header Failure 5 4 3 2 1 1 4 2 3
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month
CONSEQUENCES

17. Deployment Charges and Shear Pins
The modules are held together by 2-56 nylon shear pins, each having a shearing force of 25 pounds.
Each module will be held in place by 4 shear pins, totaling 100lb of force needed for separation.
To separate the modules, 4F black powder will be used.

18. Parachute System Dual Deployment Method
Main Parachute switched with Drogue
Drogue has 5’ diameter
Main has 20’ diameter
Terminal Velocity: 68.3 ft/s
Impact velocity: 16.7 ft/s
Max impact energy 74.7 ft-lb

19. Parachute Performance

20. Parachute: Risk AnalysisO D
Trend
Rank
App
Risk Title  1
R/M
Parachute folding technique  2 M
Air Brake interference with parachute
deployment 3
Bulkhead attachment strength 4 A
Altimeter failure 5
Deployment accelerations on rocket body 5 4 3 2 1 1 2 3 5 4
CONSEQUENCES
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month 20

21. AirBrake Linkage Four-Bar-Linkage 3 six inch long flaps
Slider
Rocket (ground linkage)
3 six inch long flaps
One link per flap

22. AirBrake Linkage Linear actuator drives slider down guide shaft
Links are forced out of rocket body
Flaps open up

23. Linkage Dimensions AirBrake compartment length is 15in
Flaps are 6in long
Connecting links are 6.52in long
Slider sleeve length is 6.125in
Guide shaft length is 3.5in
Slider displacement is 2.35in which allows flaps to open 56 degrees

24. ACDS: Electrical Diagram

25. ACDS Control
ACDS uses a proportional navigation algorithm in conjunction with a PID controller.
ACDS controller determines the altitude and orientation of the rocket by filtering and combining sensor data with an Unscented Kalman filter.
Sensor
Manufacturer
Model
Range -
Range +
Accuracy +-
Drift +-
Accelerometer
Bosch
BMA180
16 g
512 LSB/g +-3.0%
0.01 %/K
Gyroscope
STMicroelectronics
L3G4200D
2000 dps
70 mdps/digit
0.04 dps/C
Differential Pressure Sensor
Honeywell
24PCDFA6D
-30
30 Psi
N/A
Barometer
BMP085
300 hPa
1100 hPa
1.0 hPa
1.0 hPa in 12 months
Temperature
-40
85 C
1.0 C

26. Unscented Kalman Filter Block Diagram

27. ACDS: Risk Analysis L 5 I 4 K E 3 2 H O 1 D 1 2 3 4 5 CONSEQUENCES
Trend
Rank
App
Risk Title  1
R/M
Kalman filter implementation and tuning
issues  2 M
Erroneous control loop commands  3
INS Drift 4
I2C Implementation 5
Linear actuator weight limitations 6 R
Linear actuator force limitations 7
Unpredicted flight characteristics with airbrake use 5 4 3 2 1 3 1 2 5 6 7 4
CONSEQUENCES
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month 27

28. Educational Engagement & Outreach
OUTREACH GOALS:
Reach kids in Alaska’s interior & groups underrepresented in STEM outreach.
Show kids that they possess the skills to become future engineers and innovators and inspire them to pursue a STEM career.
Make a difference in Alaska’s interior schools and to enrich STEM education.
OUTREACH ACTIVITIES:
Rocketry Presentations
Hybrid Motor Demonstration
Rocket Building Workshops
Launch at Poker Flat Rocket Range

29. Educational Engagement & Outreach (Cont.)
SCHEDULE:
BUDGET: