Critical Design Review
Heavens Bound Halibut (HBH)
February 8, 2012
1
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 54.65 lbs
– ACDS separated from parachute deployment
– ACDS controller switched to BeagleBone
•
Changes made to payload criteria:
– None
Changes made to activity plan:
– None
•
2
Budget
Description
Fiberglass Nosecone, 24/6
Bluetube Body 6", length 48"
Blue Tube 54mm
Thrust Ring Retainer, 54mm
1/2" 9-Ply Birch Centering Rings, 54mm
1/2" 9-Ply Birch Bulkhead Plates
20 ft. Rocketman Main Parachute
5 ft. Rocketman Drogue Parachute
L2200G-P reload kit (propellant)
RMS-75/5120 reload casing
Carbon fiber kits
Stratologger
GPS Tracker
linear actuator
processor
air speed sensor
analog device IMU sensor
siren
rocket beeper
XL Variable-Capacity Ejection Canister
Cost
Number
$99.95
$66.95
$23.95
$40.00
$8.67
$6.34
$300.00
$45.00
$280.00
$520.00
$143.90
$69.99
$300.00
$400.00
$100.00
$50.00
$900.00
$60.00
$12.95
$9.99
Sub Cost
Running Tally
1
$99.95
$99.95
3
$200.85
$300.80
1
$23.95
$324.75
1
$40.00
$364.75
3
$26.01
$390.76
4
$25.36
$416.12
1
$300.00
$716.12
1
$45.00
$761.12
1
$280.00
$1,041.12
1
$520.00
$1,561.12
1
$143.90
$1,705.02
4
$279.96
$1,984.98
1
$300.00
$2,284.98
1
$400.00
$2,684.98
1
$100.00
$2,784.98
1
$50.00
$2,834.98
1
$900.00
$3,734.98
1
$60.00
$3,794.98
1
$12.95
$3,807.93
3
$29.97
$3,837.90
3
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
4
24.000
33.000
Vehicle Dimensions
Payload
18.000
133.000
21.000
Vehicle Properties
Diameter
6
(in)
37.000
Electronics and ACDS
Length (in)
133
Gross Liftoff
Weight (lb)
54.65
Launch Rail
Size (in)
Motor
Retention
1.0
thrust ring
5
Fins
6
CP and CG analysis
The center of pressure (CP) is located 90.83 inches from the nose cone.
The center of gravity (CG) is located 79.86 inches from the nose cone.
Total Mass (Lbs)
The stability margin has increased to 1.83.
Nose Cone
54.64
0.22
Payload
1.5
Parachute Bays
Main Parachute
Drogue Parachute
4.34
8.14
5.57
ACDS Tube
17.25
Motor Tube
17.62
7
Flight Simulations
8
Scale Model Results
9
FROSTE System Risk Matrix
Likelihood Categories
Technical
Schedule
5
No understanding of design or no experience
Very High implementing similar designs.
No one is working on the subsystem
4
High
Little understanding of design or little
experience implementing similar designs
3
Moderate
2
Low
1
Very Low
Some understanding of design or some
experience implementing similar designs
Only one student working on this who
will graduate before it is expected to be
done.
Only one student working on this who
has many classes this semester.
Great understanding of design or good
experience implementing similar designs
There are two (or more students
working in this
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
Moderate impact to full
mission success criteria.
No impact to full
Minor impact to full
Minimum mission
Technical
mission success criteria mission success criteria
success criteria is
achievable with margin
Minor impact to
schedule milestones;
accommodates within
reserves; no impact to
critical path
Schedule
Negligible or no
schedule impact
Cost
Between 2% and 5%
<2% increase over
increase over allocated
allocated and negligible
and can handle with
impact on reserve
reserve
Impact to schedule
milestones;
accommodates within
reserves; moderate
impact to critical path
4
High
5
Very High
Major impact to full
mission success criteria. Minimum mission
Minimum mission
success criteria is not
success criteria is
achievable
achievable
Major impact to
Cannot meet schedule
schedule milestones;
and program
major impact to critical
milestones
path
Between 5% and 7%
Between 7% and 10%
>10% increase over
increase over allocated increase over allocated,
allocated, and/or can’t
and can not handle with and/or exceeds proper
handle with reserves
reserve
reserves
High Risks
Moderate Risks
Low Risks
10
FROSTE System: Risk Analysis
L
I
K
E
L
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H
O
O
D
Trend
5
Rank
App
Risk Title

1
M
Development Delays

2
M
Motor Shipping Issues

3
M
Funding

4
A
Material Acquisition

5
W
Facilities Schedule Conflicts

6
W
Student Schedule Conflicts

7
R
FAA Waiver Issues
1
4
2
3
4
2
1
7
1
2
3
3
6
5
4
5
CONSEQUENCES
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
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
12
Physical Payload Integration
• Payload is in P-POD shell
• Slides into nose cone
• Secured by 8 quarter
inch bolts
13
Payload
The Alaska Research CubeSat (ARC)
14
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.
15
ARC Launch Environment Data Logger (LEDL):
Risk Analysis
L
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K
E
L
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H
O
O
D
Trend
5
4
3
2
Rank
App
Risk Title

1
R
Launch Detect

2
W
Software / testing

3
A
Memory

4
M/R
Sensor Header Failure
1
1
1
2
4
2
3
3
4
5
CONSEQUENCES
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
16
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.
17
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
18
Parachute Performance
Recovery System Properties (no wind)
Recovery System Properties (no wind)
Drogue Parachute
Main Parachute
M anufacturer/M odel
Rocketman
M anufacturer/M odel
Rocketman
Diameter Size (ft)
5
Diameter Size (ft)
20
Altitude at Deployment (ft)
5,260
Altitude at Deployment (ft)
1,000
Velocity at Deployment (ft/s)
8.79
Velocity at Deployment (ft/s)
67.6
Terminal Velocity (ft/s)
68.3
Landing Velocity (ft/s)
16.7
Recovery Harness M aterial
Nylon
Recovery Harness M aterial
Nylon
Harness Size/Thickness (in)
1"
Harness Size/Thickness (in)
1"
Recovery Harness Length (ft)
12
shrouds attached to bulkhead
Harness/Airframe
Interfaces
Kin e tic
En e rg y
Du rin g
De s c e n t (ftlb )
Section 1
Section 2
1028
2525
Section 3
Section 4
Recovery Harness Length (ft)
45
shrouds attached to bulkhead
Harness/Airframe
Interfaces
Kin e tic
En e rg y Up o n
La n d in g (ftlb )
Section 1
Section 2
Section 3
Section 4
7.45
18.8
74.7
54.65
19
Parachute: Risk Analysis
L
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L
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O
O
D
Trend
5
4
3
1
2
2
1
2
3
App
Risk Title

1
R/M

2
M
Air Brake interference with parachute
deployment

3
M
Bulkhead attachment strength

4
A
Altimeter failure

5
M
Deployment accelerations on rocket
body
Parachute folding technique
3
5
1
Rank
4
4
5
CONSEQUENCES
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
AirBrake Linkage
• Four-Bar-Linkage
– Flap
– Link
– Slider
– Rocket (ground linkage)
• 3 six inch long flaps
• One link per flap
AirBrake Linkage
1. Linear actuator drives slider down guide shaft
2. Links are forced out of rocket body
3. Flaps open up
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
ACDS: Electrical Diagram
24
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
Accelerometer
Gyroscope
Differential Pressure
Model
Range -
Bosch BMA180
Accuracy +-
Drift +-
16 g
512 LSB/g +-3.0%
0.01 %/K
2000 dps
70 mdps/digit
0.04 dps/C
-30
30 Psi
N/A
N/A
300 hPa
1100 hPa
1.0 hPa
1.0 hPa in 12
STMicroelectronics L3G4200D
Honeywell 24PCDFA6D
Range +
Sensor
Barometer
Bosch BMP085
months
Temperature
Bosch BMP085
-40
85 C
1.0 C
N/A
25
Unscented
Kalman Filter
Block Diagram
26
ACDS: Risk Analysis
L
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L
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O
O
D
5
Trend
3
Rank
App
3
2
2
5
1
6
7
1
R/M

2
M
Erroneous control loop commands

3
M
INS Drift

4
R/M

5
M
Linear actuator weight limitations

6
R
Linear actuator force limitations

7
R
Unpredicted flight characteristics with
airbrake use
4
1
2
3
4
Kalman filter implementation and tuning
issues

1
4
Risk Title
I2C Implementation
5
CONSEQUENCES
Criticality
High
Med
Low
L x C Trend
 Decreasing (Improving)
 Increasing (Worsening)
 Unchanged
* New since last month
Approach
M – Mitigate
W – Watch
A – Accept
R – Research
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 innovator
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
Educational Engagement & Outreach (Cont.)
SCHEDULE:
BUDGET: