NASA USLI Critical Design Review...
-
Upload
hoangkhanh -
Category
Documents
-
view
216 -
download
1
Transcript of NASA USLI Critical Design Review...
NASA USLI Flight Readiness
Review Presentation
1
University of California, Davis
Overview
• Compliance Matrix
• Project Plan
• Launch Vehicle Design
• Rocket Performance and Stability
• Test Plans and Procedures
• Moving
• Compliance Matrix
• Closing
2
Compliance Matrix (1/2)
3
Item Slide Numbers
Launch vehicle dimensions 11,12
Key design features 13,14
Motor Description 15
Flight stability + static margin 15
Thrust-to-weight and rail exit velocity 15
Mass statement 18
Parachute size, Descent rates 19
Kinetic energy at key phases of mission and landing
20-24
Compliance Matrix (2/3)
Item Slide Numbers
Predicted altitude in 5,10,15,20 MPH 26
Predicted drift in 5,10,15,20 MPH 26
Test plans and procedures 27
Full scale flight test 27
Recovery system tests 27,28
Requirements Verification 27,28
Payload design and dimensions 37
Key design features of payload 38
Payload integration 39
4
Compliance Matrix (3/3)
Item Slide Numbers
Interfaces with ground systems 41
5
PROJECT PLAN
6
Budget and Funding – on track
• Total Expenses of Rocket: $1363.97
• Rocket Expenses guaranteed
• Travel Expenses guaranteed
7
Current Sponsorship Money
University of California Davis College of Engineering: $1000.00
University of California Davis MAE Department: $1000.00
University of California Davis Club Finance Council: $1725.56
California Space Grant Consortium $10,000.00 Total Operating Budget $13,725.56
Milestones – on track
8
10-22-12 Web Presence Established Completed
10-29-12 PDR Report Posted Completed
11-16-12 PDR Presentation Completed Completed
1-5-13 Prototype Launch Completed
1-14-13 CDR Report Posted Completed
1-31-13 CDR Presentation Complete Completed
3-3-13 Initial Payload Testing Completed
3-9-13 Full Scale launch with payload Completed
3-18-13 FRR Posted Completed
3-30-13 Full Scale launch with payload (2) Completed
4-3-13 FRR Presentation Complete In Progress
4-17-13 LRR Conducted On Track
4-20-13 Launch Date On Track
5-6-13 PLAR Posted On Track
Educational Engagement
• Engaged 367 elementary and middle school students
• Conducted rocket launch demonstrations
• Led classroom rocket construction projects
• Led field trip/tour of U.C. Davis rocket team facilities
9
Launch Vehicle Design
10
Launch Configuration Total Height 71.5”
Diameter 4”
Number of fins 4
Fin attachment Slotted body tube + Epoxy Fillets
Fin Span 14.43”
Total Launch Weight (without motor) 228 oz
Total Launch Weight (with motor) 281 oz
Rail Size 1” (Can be modified for larger)
11
Launch Dimensions
12
Key Design Features (1/2)
• Aerodynamics
– Modeled using RockSim software to ensure
stability, drift radius, and target altitude
• Structures
– Adjustable nosecone ballast system
– Custom fin jig for precise alignment
– West Systems 105/206 epoxy specification
13
Key Design Features (2/2)
• Structures cont.
– West Systems Epoxy with Colloidal Silica
• Propulsion
– Aerotech K550W motor • RockSim Calculations
• Full Scale Test
• Launch Operations
– Detailed set-up and prelaunch checklist
– Test launches
14
Motor Description
Manufacturer AeroTech
Mfr. Designation K550W
Motor Type Reload
Diameter 54.0 mm
Length 41.0 cm
Total Weight 1487 g
Prop. Weight 889 g
Average Thrust 396.8 N
Maximum Thrust 655.3 N
Total Impulse 1539.1
Burn Time 3.9 s
Rocket Flight Stability
• CG: 45.12 in from nose tip
• CP: 56.22 in from nose tip
• Static margin: 3.77 Calibers
Rocket Performance
• Thrust-to-weight Ratio: 5.04
• Rail exit velocity: 74 ft/s
• Reached an altitude of almost 4800 feet
• Overweight rocket (improvements being
made)
Mass Statement • Below is the weight of the rocket at the March
2nd full scale launch
• Mass margin to be presented
Component Weight (lbf)
Nose Cone 1.20
Forward Body Tube 1.48
Aft Body Tube (with fins and boat-tail) 4.00
Motor Casing 0.97
Main Parachute and Drogue Parachute 3.19
Payload 2.02
E-bay 1.56
Motor 3.34
Total: 14.41
19
Parachute Sizes and Descent
Rates
• Main parachute: Iris Ultra 72'' Parachute
• Drogue parachute: Classic Elliptical 18”
20
Descent Rates, KE (1/6)
Time (s)
Drogue charges fire Time: 17.20 s Altitude: 4425 ft
Main charges fire, no descent rate change Time: 78.0 s Altitude: 831 ft
Landing Time: 92.0 s Altitude: 60 ft
Alt
itu
de
(ft
AG
L), A
xial
A
cce
lera
tio
n (
G’s
)
Full-Scale Prototype Rocket Test Launch
21
• Drogue Descent for Full-Scale Prototype Test Launch • Descends for: 3594 ft • Apogee to main chute ejection charges: 60.80 s
• 59.87 s in simulation • Drogue descent rate: 59 ft/s
• 72 ft/s in simulation • Drogue descent KE: 676.7 ft-lbf
• Main Descent for Full-Scale Prototype Test Launch • Main chute did not deploy
Descent Rates, KE (2/6)
22
Time (s)
Drogue charges fire Time: 18.14 s Altitude: 4765 ft
Main charges fire Time: 82.77 s Altitude: 818 ft
Alt
itu
de
(ft
AG
L), A
xial
A
cce
lera
tio
n (
G’s
)
Backup charge fires and Raven stops collecting data
Final Competition Rocket Test Launch
Descent Rates, KE (3/6)
23
0
200
400
600
800
1000
1200
1400
1600
1800
0 50 100 150 200 250
Alt
itu
de
(m
)
Time (s)
Altitude vs Time (Final Competition Rocket Test Launch)
Descent Rates, KE (4/6) Data from our Payload Controller:
24
Descent Rates, KE (5/6)
• Drogue Descent for Final Competition Rocket Test Launch • Descends for: 3947 ft • Apogee to main chute ejection charges: 64.63 s
• 66.62 s in simulation • Drogue descent rate: 61 ft/s
• 78 ft/s in simulation • Drogue descent KE: 824.02 ft-lbf
• Main Descent for Final Competition Rocket Test Launch • Data point 1 during main decent: 527.72 ft, 92.91 s • Data point 2 during main decent: 325.23 ft, 106.69 s
• Main chute decent rate: 14.69 ft/s • KE at landing: 47.79 ft-lbf
25
Prototype Test Launch (01/05/13)
• KE at Burnout (max KE): 75,210 ft-lbf • Drogue descent rate: 59 ft/s • Drogue descent KE: 676.7 ft-lbf • Main descent rate: Main did not deploy • KE at landing (w/o main): 588 ft-lbf
Full Scale Competition Rocket Test Launch (03/02/13) • KE at Burnout (max KE): 103,911 ft-lbf • Drogue descent rate: 61 ft/s • Drogue descent KE: 824.02 ft-lbf • Main descent rate: 14.69 ft/s • KE at landing: 47.79 ft-lbf
Summary
Descent Rates, KE (6/6)
Drogue Chute: 18’’ Diameter Main Chute: 72’’ Diameter
26
Simulated Altitude and Drift of Final Competition Rocket Using RockSim
5 mph Wind 10 mph Wind 15 mph Wind 20 mph Wind
Predicted Altitude
(ft) 4813.73 4732.49 4599.3 4422.04
Predicted Drift (ft) 73.93 346.16 565.45 567.91
Predicted Altitude and Drift (1/1)
27
Test Plans and Procedures
• First Test Launch
– Goal: Gain experience with launch procedure and
verify functionality of launch components
– Exposed configuration falws and gave real world
results
– Discrepancy between simulation and results
Altitude Projected Altitude
Launch 1 4400 ft 5137 ft
28
• Second Test Launch
• Goal: Implement changes made
• Payload integration
• Main chute, backup altimeter
• Improve launch operations
• Fly the K550 motor
Test Plans and Procedures
Altitude Projected Altitude
Launch 1 4763 ft 5450 ft
29
Simulation Discrepancies
• True cause of simulation discrepancy
• Plan to reach 1 mile 281 oz (-0)
(17.56 lbf)
276 oz (-5)
(17.25 lbf)
271 oz (-10)
(16.94 lbf)
266 oz (-15)
(16.63 lbf)
261 oz (-20)
(16.31 lbf)
Extreme High 4910.17 5039.2 5171.2 5306.1 5443.7
0 MPH Wind 4841.4 4979.0 5107.4 5238.5 5372.1
5 MPH Wind 4817.68 4955.5 5084.2 5215.5 5349.5
10 MPH Wind 4744.36 4888.9 5012.1 5144.2 5279.0
15 MPH Wind 4622.44 4761.7 4891.5 5024.4 5160.1
20 MPH Wind 4458.01 4597.6 4727.7 4861.1 4977.5
Extreme Low 4407.27 4527.6 4655.1 4784.48 4916.5
Weight Reduction/Mass Margin
30
Component Weight (lbf) Est. Reduction (lbf)
Nose Cone 1.20 -.188
Forward Body Tube 1.48 0
Aft Body Tube (with fins
and boat-tail) 3.80 0
Motor Casing 0.97 0
Main Parachute and
Drogue Parachute 3.19 -.156
Payload 2.02 -.500
E-bay 1.56 -.375
Motor 3.34 0
Total: 17.56 -1.219
Total after reduction: 16.33
Weight Reduction/Mass Margin
Weight [oz (lbf)]
Worst conditions 253.0 (15.8125)
Best conditions 268.0 (16.75)
31
To achieve 5,280 ft:
Ideal mass margin: 15oz (.9375lb)
32
Recovery System Tests
• Ejection charge tests
• Altimeter testing
33
Structural Test
• Epoxy Testing
• Improve technique and test strength
• Combined fin jig testing
34
Summary of Requirements Verification
Deliver payload to 5280ft Designed (4763ft max thus far)
Carry at least one altimeter Verified
Obtain altitude by beeps Verified
Remain subsonic Verified
Recoverable and Reusable Verified
Maximum 4 independent sections Verified
Preperation time of 2 hours Verfied
Capable of remaining in launch config for 1 hour
Verified
Compatible with 8ft, 1 in launch rail Verified
Launched by a 12 volt DC system Verified
Criteria for full scale flight met Verified
Maximum budget of $5000 Verified
No prohibitions violated Verified
PAYLOAD DESIGN
35
Design: Electronics • ArduPilot 2.0 with MediaTek GP
• Embedded MPU-6000 Gyroscope and Accelerometer
• Embedded MS5611 Barometric Pressure Sensor
• Includes MediaTek MT3329 GPS Daughter Board
• TSL250R Light to Voltage Sensor
• LM61CIZ Analog Temperature Sensor
• HIH-5030 Analog Humidity Sensor
• 3DR Radio Transmitter and Antenna
• 3DR USB Receiver and Antenna
• Ground Station computer
36
ArduPilot
Analog Inputs
+ADCs
External Analog Sensors
TSL250R
Light-to-
Voltage
Analog
Temperature
and Humidity
Sensors
Integrated Sensors on ArduPilot
3DR Radio
Transmitter +
Antenna
3DR Radio USB
Receiver +
Computer
Design: Flow Chart
5V
2600mAh
Lithium
Battery
+5v
GND
MPU-6000 3-axis
gyro and
accelerometer
37
MediaTek
MT3329 GPS on
Daughterboard
MS5611
Barometric
Pressure Sensor
Design: Measurements
38
Acceleration MPU-6000 3 Axis Gyro and Accelerometer
Flight path MediaTek MT3329 10 Hz GPS
Solar Irradiance TSL250R Light to Voltage Sensor
Barometric Pressure MS5611 Barometric Pressure Sensor
Temperature LM61CIZ Analog Temperature Sensor
Humidity HIH-5030 Analog Humidity Sensor
Angular Rotation MPU-6000 3 Axis Gyro and Accelerometer
Design: Features • Automatic pre-launch board reset
capability.
• Light weight construction utilizing G10
fiberglass, aluminum, and lithium
polymer cells.
• Vibration dampening mounts for APM
2.0.
39
• Multi-level dense electronic packing for easy installation/removal.
• Payload bay kraft casing providing a high strength to weight ratio.
• Steel rods distributing the load axially along payload bay.
Payload Integration • Location:
– Above the motor casing and below the drogue parachute
• Assembly: – Forward bulkhead attached to drogue parachute a steel u-bolt
and a chute quick link.
– The payload bay is secured using four removable nylon rivets. The rivets breach the fiberglass rocket shell and anchor to the internal payload bay. The simplicity allows for ease of integration/removal.
• Static Ports: – Two 180 ° drilled holes through rocket body tube and payload
bay allowing for ambient pressure readings.
• Sunlight: – Drilled hole for the allowance of sunlight on the TSL250R
40
Interfaces with Ground Station
• 3DR-
– The APM 2.0 directly transmits at a 57600 baud rate to the
ground control station.
– One way communication.
– Maximum transmit power of 100 mW with 1 mile range.
• Ground Control-
– QGoundControl: The ground station software receiving the live
data stream for all the internal and external sensors.
– 57600 8N1 Serial protocol .
– Live data transmitted in the graphical interface is stored as log
files for post processing.
41
42
Compliance Matrix (1/2)
43
Item Slide Numbers
Launch vehicle dimensions 11,12
Key design features 13,14
Motor Description 15
Flight stability + static margin 15
Thrust-to-weight and rail exit velocity 15
Mass statement 18
Parachute size, Descent rates 19
Kinetic energy at key phases of mission and landing
20-24
Compliance Matrix (2/3)
Item Slide Numbers
Predicted altitude in 5,10,15,20 MPH 26
Predicted drift in 5,10,15,20 MPH 26
Test plans and procedures 27
Full scale flight test 27
Recovery system tests 27,28
Requirements Verification 27,28
Payload design and dimensions 37
Key design features of payload 38
Payload integration 39
44
Compliance Matrix (3/3)
Item Slide Numbers
Interfaces with ground systems 41
45
Moving Forward
• Second Full Scale Test Launch • Launch Operations Refinement • Performance Optimization
• Payload
• Complete assembly and integration • Complete firmware development • Complete ground station software development
Thank You!!!
47