RocketSat VI Preliminary Design Review
CU Boulder October 28, 2009
Colorado Space Grant Consortium RocketSat VI
Team Organization
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Primary Investigators (Customers) Chris Koehler, Brian Sanders, Kendra Kilbride,
Zoltan Sternovsky
Project Manager Emily Logan
STR Chris Young
Chris LaPanse Michael Rice
SFT/CDH Frankie Ning
Michael Murry Riley Pack
Jared Yenzer
Mission Specialists Kirstyn Johnson Marcus Flores
Marcell Smalley Kyle Wolma
Design Team
Mission Statement
• The objective of RSVI is to measure large aerosol particle density and charge from 75 to 95 km to determine if the presence of these particles is related to mesospheric charge balance and phenomena and increased levels of carbon dioxide and methane in the atmosphere
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Mission Overview
• Objective – Measure Meteoric Smoke Particle densities
and charge to evaluate the mesosphere – Attempt to characterize the atmosphere and
relate the characterizations to understanding of global warming and creation of noctilucent clouds
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Mission Overview: Noctilucent Clouds
• Minimum temperatures nearing 140 K allow for heterogeneous nucleation of ice – Meteoric smoke particles
most likely serve as nucleus
– Growth to a radius of up to 50 nm
• Particles visible as noctilucent clouds(NLC) – Also known as polar
mesospheric clouds (PMC)
Credit: NASA/Donald Petit.
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Mission Overview: Science
• Particle Size – Formation near 88km – Particles Descend and
increase in size as more water is frozen to the exterior
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Polar Mesosphere summer echoes (PSME): review of observations and current understandings M. Rapp abd F.-J. Lϋbken Beibniz Institue of Atmospheric Physics
Mission Overview: Metal Budget
• Meteoric evaporation between 70 and 110 km – 100 metric tons of
meteoric debris per day
– Layers of Fe, Na, K, Ca, Si, Mg
– Measured from the ground with lidar
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Athena Space Programmes Unit Upper Atmosphere Wiki
Mission Overview: Metal Budget
• Sodium layer – 90-95 km – Believed to be
nucleus of larger charged particles
– Decrease in Na density correlated with PMC’s
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Athena Space Programmes Unit Upper Atmosphere Wiki
Mission Overview: Science
• Particle Densities – Charged Particles
• two dense negative regions centered at 87.5 km and 85.5 km
– Electron Density • Biteout at
corresponding altitudes
– Charged particles electron Sink
– Positive particle region boost electrons
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Polar Mesosphere summer echoes (PSME): review of observations and current understandings M. Rapp abd F.-J. Lϋbken Beibniz Institute of Atmospheric Physics
Expected Results
• Signals – Expecting both positive and negative
regions – Two negative regions at 87.5 km and 85.5
km • Densities from 3000 cm-3 to 5000 cm-3
– Positive region between the two negative regions • Densities from 1000 cm-3 to 2000 cm-3
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Expected Results
• Charge Density Results – Densities reveal amounts of particles at
distinct altitudes in the mesosphere – Comparison to previous sounding rocket
mission results to monitor changes in the atmosphere. • Less charged ice particles translates to warmer
temperatures in the mesosphere – Comparison with NLC occurrence rate
changes to correlate ice particles and NLC’s
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Incident Flow
• – I = current – Aeffective = area as a function of velocity – v = velocity – n = numerical density – q = charge
• Effective area is surface area normal to the flow. • Higher Current means more particles • Before Orion burnout the effective area is nearly
zero – After burnout effective area increases and current
increases
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Data Analysis
• Graphite Patch Detector – Convert voltage data back to current – Plot current vs. altitude
• Higher current is equivalent to more particles
• Attitude Determination Sensor – Calculate the angle of attack from attitude
data – Plot the angle of attack vs. altitude
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Potential Problems
• Data Anomalies – Not all ions will be deflected by detectors, will
contribute to collected current and voltage – Photoelectric current will affect detectors every
time detectors are facing upwards • can make a model based on spin rate of rocket,
determine how often would experience the anomaly, filter it out of data
– One of graphite patch detectors will fly with a voltage bias of 2 V, other will fly normally
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Testing
• Calibration of current amplifier • Test detectors, make sure they function
properly • Test magnetometers
– Create a model of results that magnetometer will provide
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Background Research • AIM
– Study of noctilucent clouds, determine why PMCs (polar mesospheric clouds) form and why they vary, quantify connection between clouds and meteorology of mesosphere – Measure particle size distributions, cosmic dust influx
• Magic Sounding Rocket
– Goal: to answer questions about the properties of smoke – Used dust detectors to direct measure the meteoric smoke particles
• Other Projects: -SAL (Sporadic Atom Layers) -ECOMA (Existence and Charge of Meteoric Smoke Particles in the
Middle Atmosphere)
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Benefits
• First meteoritic smoke particle data collected at this latitude
• Provides support for studies on noctilucent clouds and global warming
• Provides information on Mesospheric characteristics and how they have changed due to these particles
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Project Requirements
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Project Level Requirements
Requirement Descrip5on Parent Req. Verifica5on
P1
The payload shall measure meteori3c smoke par3cle density
Mission Statement
Verified through verifica3on of requirements S1, S3, S6, S7, S9, S10
P2
The payload shall measure meteori3c smoke par3cle charge
Mission Statement
Verified through verifica3on of requirements S2, S6, S7, S9, S10
P3
The payload shall be designed to conform to the RockSat 2010 User's Guide as set forth by Wallops Flight Facility
Mission Statement
Verified through verifica3on of requirements S11-‐S13
Launch Vehicle
• Terrier-improved Orion – Two stage – Two payload sections
(RockOn and Rocksat) – Predicted apogee
117-130 km • Recovered, payloads de-
integrated ~7 hours after launch
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Concept of Operations
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On launch pad, all systems off
Launch, all systems powered on by g-switch, data collection begins
Data collected System powers down at 15 minutes
Data Direction of payload Power
System Requirements
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System Level Requirements Requirement Descrip5on Parent Req Verifica5on
S1
The payload shall be able to detect meteori3c smoke par3cles P1
Verified through verifica3on of DS1-‐DS2
S2
the payload shall be able to measure charge of meteori3c par3cles P2
Verified through verifica3on of DS3
S3
The payload shall be able to determine the angle of aOack of the detector P1
Verified through verfica3on of DS5
S4
The payload shall convert detector output to a digital signal
Verified through verifica3on of CDH6
S5 The payload shall store the digital signal Verifica3on of CDH6
S6
The payload shall perform in situ measurements from 75-‐95 km P1, P2
Verified through verifica3on of DS1
S7
The payload shall not alter the par3cles during measurement P1, P2 A
S8
The system shall fly on a sounding rocket with an apogee of at least 95 km P3
Verified by RockSat Coordinator and WFF
S8.1
The payload shall survive the flight
S8
Verified through verifica3on of ST1, ST2
S8.2
The payload shall be able to perform with a temperature range of 60-‐100 degrees F P1, P2
Verified by individual component analysis
System Requirements
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System Level Requirements Requirement Descrip5on Parent Req Verifica5on
S9
The system shall characterize the flight environment
P1, P2
Verified through verifica3on of CDH1-‐CDH4
S10
The system shall make the measured data available aZer collec3on P1, P2
Verified through verifica3on of CDH6
S11
The system shall be electrically isolated from the rocket P3
S12
The system shall be contained in a canister with a diameter of 9.3 inches and a height of 9.5 inches. P3 I,A
S13
The payload shall not weigh more than 20 lbs P3 I
S14
The system shall have a center of gravity that lies within a 1x1x1 inch envelope of the geometric centroid of the integrated RockSat payload canister P3 I,A
Science Subsystem Requirements
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Detector Subsystem Requirements Requirement Descrip5on Parent Req Verifica5on
DS1
The payload shall have a detector that measures par3cles every meter from 75-‐95 km
S1 T
DS1.1 The detector shall be able to sample at a rate of 1 kHz
DS1 T
DS1.2 The detector shall be ac3vated at launch
DS1 T
DS2
The detector shall only register par3cles with a diameter larger than 1 nm
S1 T
DS3
The detector shall produce a different output for posi3ve and nega3ve charge
S2 T
DS4
The payload shall determine the a^tude of the detector with a precision to at least 1 degree
S3 T
DS4.1 The a^tude determina3on system shall be ac3vated at launch
DS4
DS5 The a^tude shall be detected every 1 meter from 75 to 95 km
S3 T
DS5.1
The payload shall be able to sample the a^tude at a rate of 1 kHz DS5 T
DS6
The system shall amplify current reading and convert to voltage
CDH6 A,T
DS6.1
The system shall have current/voltage amplifier outputs +/-‐ 10 V
DS6 A,T
DS7
The a^tude determina3on system shall be internal to the payload S3 I, A
DS8
The a^tude determina3on system shall not interfere with internal electronics
S3 A,D
DS9
The power subsystem shall provide 250 mW of power to the a^tude determina3on system
S3, DS4 A,T
Science Subsystem Requirements Break-down
• Particle detector – Only registers large particles – Can distinguish between positive and negative
charge – Sample at a rate of 1 kHz (affects CDH)
• Attitude determination – Internal – Does not interfere with other electronics (STR) – Does not require more than 350 mW power
(CDH) – Sample at a rate of 1 kHz (CDH)
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Design Driver: Detector
• All detectors need direct exposure to environment
• Depending on detector, payload layout must be adjusted, changes data analysis
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Faraday Cup Mass Spectrometer Patch Detector
Large Particle Detector Selection
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Component Graphite Patch Faraday Cups Mass Spectrometer Cost (10%) 5 2 1 Compliance (10%) 1 1 1 Availability (10%) 5 5 5 Time (10%) 4 4 4 Size (10%) 4 4 1 Construction (9%) 4 4 4 Integration (9%) 3 3 3 Testing (7%) 4 4 4 Success (5%) 2 2 2 Detection (5%) 4 4 1 Rate (5%) 3 3 3 Power (7%) 5 5 5
TOTAL 3.61 3.31 2.76
Particle Detector: Graphite Patch Detector
• Size: 1.5x2.25 inches – On mounting block: currently
2.25x2.5 inches (TBR) • Graphite patch must be
flush with rocket skin • Uses magnetic field to
deflect small ions and electrons
• Large particles are not deflected because of weight and, due to shell, are less sensitive to the magnetic field
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Al cup
Magnets
Plastic insert Graphite patch
Iron base plate
Connector
Attitude Determination System
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Component Horizon Sensor Star Tracker Magnetometer Gyroscope
Cost (10%) 3 3 3 3 Compliance (10%) 1 1 5 5 Availability (10%) 4 5 5 5 Time (10%) 4 4 4 4 Size (10%) 3 4 5 5 Construction (9%) 3 5 4 4 Integration (9%) 4 4 3 3 Testing (7%) 3 4 3 3 Success (5%) 3 3 3 3 Precision (5%) 5 5 5 5 Power (7%) 5 5 5 5
TOTAL 3.09 3.54 3.79 3.79
Attitude Determination: Inertial Sensor
• Voltage – 5 ± 0.25 V
• Magnetometer Sensitivity – ± 2.5 gauss
• Gyroscope Sensitivity – ±300º/s
• Includes accelerometers – 18 g’s
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System Layout
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Inertial Sensor
Connection to flight boards
Flight Boards
Skin of Rocket
SMA Cable
Detector
Special Requests
• Graphite Patch Detectors – Need to be mounted flush with the skin of
the rocket – Will require leak proof interface to prevent
payload section flooding
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CDH Subsystem Requirements
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CDH Subsystem Requirements Requirement Descrip5on Parent Req Verifica5on
CDH1
Accelerometers z axis shall record +/-‐ 50 G and +/-‐35G on xy-‐axis to indicate significant events S9 T
CDH1.1
Shall be sensi3ve from 0 to 5V with 2.5V offset
CDH1 T CDH1.2 Shall have a sensi3vity of 27mV/G CDH1 T
CDH2
Accelerometers (xyz axis) shall record +/-‐ 1.7G vibra3ons S9 T
CDH2.1
Shall be sensi3ve from 0 to 5V with 2.5V offset
CDH2 T CDH2.2 Shall have a sensi3vity of 1V/G CDH2 T
CDH3
The payload shall record temperature from -‐40 degC to 125 degC S9 T
CDH3.1
Shall use analog output voltage .1-‐1.75 V range
CDH3 T
CDH4
The payload shall record pressure from 0-‐15 psi S9 T
CDH4.1
Shall output from 0 to 5V with a sensi3vity of .267V/psi precision
CDH4 T
CDH Subsystem Requirements cont.
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CDH Subsystem Requirements
Requirement Descrip5on Parent Req Verifica5on
CDH5 The system shall be able to sample at 1 kHz
DS1.1, DS6.1 T
CDH5.1
The ADC shall have a throughput rate much greater than 1kHz CDH5 T
CHD5.2 The SPI bus must be able to process 16kbit/s
CDH5 T
CDH6
The system shall be able to store all digital values received from detector, a^tude determina3on system,
and all sensors in flash memory S10 A,T
CDH6.1
The system shall use SPI bus from ADC microcontroller to flash memory CDH6
CDH6.2
The system shall read bipolar -‐10V to 10V analog signals from the current to voltage amplifier
CDH6, DS6 T
CDH6.3
The system shall be able to convert the analog signals to digital signals CDH6 T
CDH7
The system shall record all freedoms of a^tude of the payload DS7 T
CDH7.1
Two Gyroscopes shall be used to measure the zenith and polar angles. CDH7 T
CDH7.2 Gryoscopes shall sample faster than 6Hz CDH7 T
CDH8
The smoke par3cle detector shall output a nano-‐amp of current DS1 T
CDH8.1
The nano-‐amp shall be converted and amplified to an output voltage of +/-‐ 10v CDH8 T
Parts Power Consumption Operating Temperature
AT25DF641 (Memory) 16.5 mW -40°C to +85°C
ASDX015 (Pressure) 30 mW -20°C to +105°C
LM50 (Temperature) 0.65 mW -40°C to +125°C
ADXL203CE (Low Accelerometer, Two Axis)
3.5mW -40°C to +125°C
AD22281 (High Accelerometer, One Axis)
6.5 mW -40°C to +125°C
AD974 (ADC) 70 mW -40°C to +85°C
MAX743EPE (Regulator) 20 mW -40°C to +85°C
ATMEGA32A (Microcontroller) 37.5 mW -55°C to +125°C
LM2937ES-3.3 (3.3V Regulator) 500 mW -40°C to +125°C
LM2937ES-5 (5 V Regulator) 400 mW -40°C ~ 125°C
OPA129 (OP-Amp) 6 mW -40°C to +125°C
BUF634 75 mW -40°C to +125°C
Total Power Consumption Operating Temperature Supplied Power Time
1.17 W 74°F 9.2 Hours
Parts List: Operating Temp & Power Consumption
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ADC Requirements
Smoke Detector after current to voltage amplifier • Random noise of 5 mV • There are also spikes on the
noise 20 microseconds apart with amplitude of 35 mV p-p
• +/-10V output
ADC bit accuracy • 12 bits from +/- 10V
– Sensitive to 4.8mV • 14 bits from +/-10V s
– Sensitive to 1.2mV • 16 bits from +/-10V
– Sensitive to 0.3mV • 0-10V
Colorado Space Grant Consortium RocketSat VI
“Colorado Flight Unit Manual”. Sternovsky, Zoltan, Scott Knappmiller and Scott Robertson. University of Colorado at Boulder
ADC: AD974
• 16 bits • Throughput 200kSPS • Input analog signal 0-5, +/-10V • Single 5V supply • 4 input channels if 0-5V • 120mW maximum dissipation • –40°C to +85°C • Package N-28 DIP or R-28 SOIC • Flight heritage
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Flash Memory Selection
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Component
AT25DF641-‐MWH-‐T-‐ND
AT25DF161-‐SH-‐T-‐ND
AT26DF081A-‐SU-‐ND
Size 5 4 3 Speed 5 5 4 Interface 4 4 4 Price 3 5 4.9
TOTAL 18 18 15.9
Flash Memory: AT25DF641-MWH-T-ND
• Size • 64 M
• Speed • 100 ATAMHz
• Interface • SPI, 3-Wire Serial
• Price • $ 3.57
• Mouser.com
Colorado Space Grant Consortium RocketSat VI
Regulator
• +/-12V voltage rails for op amp for current amplifier and voltage buffer
• Options: – Inverting and boost DC/DC converter from
current 9V, 5V, or 3.3V – Linear step down from 18V (2 9V in series)
to 12V – Buck and inverting regulator from 18V to
12V
Colorado Space Grant Consortium RocketSat VI
MAX743C
• Maxim • Dual output Switch mode Regulator • Input 4.2V - 6V • Efficiency 82% • 2 outputs • Selectable +12V, +15V • Low noise
Functional Block Diagram
s Microcontroller
9V Power G-Switch RBF (Wallops)
ADC
Dust Collector
ADC
Flash Memory
Buffer
Current to Voltage Amplifier
Buffer
Current to Voltage Amplifier Dust Collector
Microcontroller
Dust Board
Flash memory
+ 12V DC/DC
Converter
AVR Board
Pressure Sensor
Temperature Sensor
3.3V Voltage regulator
Level Shifter
5V Voltage regulator
6DOF sensor
3.3V
9V 5V
+12V
Flash memory
Data
Power Functional Block Diagram
9V Wallops Circuitry
3.3 V Linear Regulator
5V Linear Regulator
+/- 12V DC/DC converter
AVR Board SMOK Board
5V Power line
3.3V Power Line
Power Source: 9V batteries
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Wallops RBF Interface
AVR
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AVR PCB
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Current Amplifier
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Science Board
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Software flow
• System is active when: – RBF pin inserted – G-switch triggered
• Initial UART and ISMP checks • Set and start timer for sampling rate • Main loop
– Flush memory to flash memory – Check memory usage
• Interrupt to retrieve data from SPI bus
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Software Flow Chart
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Power Activated
Initialize Serial connections
Check for ISMP connection
Yes Program
mode
No Latch check
Halt Program
Set timer
If memory is full
Else
Set Interrupts for Sensors
While loop
Write to flash
memory Latch
Update
Interrupt at 1Khz
Sample from AD974
Sample from ADIS16400
SMOK
AVR
Memory not full
Stop writing
Memory is full
Memory Usage
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6DOF 9x16 bits +optional
temperature data
330Hz
current amplifier 2x16bits 1KHz
64 Mbit flash memory
Micro controller
20.51 minutes
Pressure, Temperature
2x10 bits
Micro controller
1KHz
ADC
64 Mbit flash memory
47520 bits/s
52000 bits/s
22.45 minutes
Software Latch Flow Chart
Checks two byte in
EEPROM.
Status = not launch
Status launched
Retrieves last written address to the flash
memory
Low z-axis bits
Latch Check
Latch update 2 Hz
Every 20s records current
address >40minutes
High z-axis bits
Check if acceleration > 5G set bits
Make sure Flash
memory overflow
(base time
Both bits are not
set
Both bits are
set
Status = unknown
Run Main Code
Time < 33 minutes
No
Stops writing to memory
Yes
Microcontroller On
Yes
Halts program
No
Else
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Risk & Concerns
Risks & Concerns
• Noise on current amplifier
• Power management • Memory protection • Maximum sampling
rates of ATmega32 using the SPI bus
Solutions
• Testing, usually periodic and can be defined
• Redundancy of two isolated 9V inputs, Sequencer, power supply monitor PMBus,
• Latch and counter to ensure no memory overwrite
• Testing RockOn board Colorado Space Grant Consortium
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Testing
• Noise checks on ground and regulator outputs
• EEPROM verifications • Data Acquisition test of full system • Software testing of latches and
interrupts • FlatSat • Full Simulation Test
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Structures Subsystem Requirements
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Structures Subsystem Requirements Requirement Descrip5on Parent Req Verifica5on
ST1
The system shall use building materials that can withstand a temperature of at least 100degC
S8.1 A,T
ST2
The sytem shall use building materials that can withstand Gloading of at least 25 G
S8.1 A,T
ST3
The system shall support CDH boards with nonconduc3ve material
CDH6 A
ST4
The system shall secure the CDH boards to the canister
S8.1 A
Structures Material Selection
Resis5ve Material
G-‐10/FR4 Garolite
20% Glass Filled Makrolon (9425)
Resis3vity (10%) 10 10 Tensile Strength (40%) 9 3
Density (20%) 6 8
Price (30%) 9 6
TOTAL 8.5 5.6
Other Material
Aluminum 6061 T6
G-‐5 Titanium
Tensile Strength (40%) 4 10
Density (30%) 10 6
Price (30%) 10 1
TOTAL 7.6 6.1
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Materials: Garolite and Aluminum
Resistive Material • G-10/FR4 Garolite
(12”x12”x1/8”) • Cost
– $16.70 • Temperature Range
– Up to 284F • Yield Strength
– 50,000 psi
Conductive Material • Aluminum 6061 T6
(12”x12”x1/8”) • Cost
– $26.06 • Temperature Range
– -320F to 300F • Yield Strength
– 35,000 to 40,000 psi
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Payload Layout
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Batteries
Particle Board
Inertia Sensor
Accelerometer
AVR
Electronics Stack
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Sensors
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Particle Sensor
Inertia Sensor
Mass Estimation
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Object Unit Weight Mass AVR Board (including support plates) n/a 3 lbs
Lithium batteries (2) 0.7545 lb/battery .159 lbs Canister n/a 6.9 lbs Sensors 1.335 lbs -Attitude Sensor .035 lbs -Particle Sensors 1.3 lbs Aluminum .0975 lb/in^3 1.225 lbs G-10/FR4 .065 lb/in^3 .817 lbs Standoffs .0125 lb/standoff .1 lbs
Total 13.536 lbs
Since the canister will be very close to symmetrical the center of gravity will be within an inch of the center.
Margins
• Total mass without canister: 6.636 lbs – Total mass allowed after factoring in the
weight of the canister: 13.1 lbs – Our predicted weight is 50.7% of the weight
allowed for the internal payloads – Could share our canister with another
university • Total margin with Wallops: 6.464 lbs
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Risks and Concerns
Risks and Concerns • Support plate spider
web fracture • Wire disconnection • Sensors mounted
externally
Solutions • SolidWorks structures &
materials testing • Vibration testing (at
Wallops and possibly design our own preliminary)
• Plate load test (loading weight on support plates to find pressure plates and supports can withstand)
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Transportation to Wallops
• Integrate canister and carry on in RocketSat transport box
• ESD protection for payload • Packing material for structural
protection • Documentation for airport
security – Letters from Chris Koehler,
Brian Sanders, Zoltan Sternovsky
– NASA and COSGC symbols – Note for Fragile Satellite
Instrument
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Launch Vehicle Interface
• Each canister attached to Sub-SEM ring assembly in a stacked configuration
• Sub-SEM rings attached to longerons that span length of payload section
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Launch Vehicle Interface
• Attachment of detectors TBD
• Most likely will be inserted into pre-existing window in the place of an optical or atmospheric port
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detector window
Integrated window
Launch Vehicle Testing and Integration
• Vibe test performed at Wallops – 3 axis test that ensures payload
will survive vibrations of flight • Integration after payload passes
vibe test 1. Canister fully integrated 2. Canister connected to Sub-SEM
assembly 3. Skin installed 4. Detectors installed windows 5. Windows installed to skin
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Launch Vehicle De-integration
1. Window disconnected from skin
2. Detector disconnected from window
3. Skin removed 4. Payload disconnected from
Sub-SEM 5. Canister de-integrated and
condition documented 6. Electronics stack removed,
data recovered
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Wallops Compliance
• Data collection begins upon launch with payload activation using g-switch
• Run SMA cable from the graphite patch collectors into the rocket to connect with the electrometers
• Use an RBF pin to comply with no-volt requirement
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Schedule
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FALL SEMESTER
Month Day Task September
9 IFF due
October 5 Concept Pitch slides due 7 Concept Pitch
12 CoDR slides due 14 CoDR Presenta3on 14 Select final mission
November 3 PDR slides due 4 PDR Presenta3on 9 CDR slides due
11 CDR Presenta3on 30 Begin ordering hardware, preliminary science tes3ng
Schedule
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SPRING SEMESTER Month Day Task January 12 Begin building science boards
12 Begin tes3ng iner3al sensor (1), detectors (2), begin developing model (3) 12 Begin machining component plates (1), modified detector mounts (2) 30 Science boards constructed (flight and backup) 30 Iner3al sensor tested and model par3ally developed for output 30 Component plates constructed
February 1 Begin building AVR board 15 Preliminary systems tests completed, begin characteriza3on of converters 15 AVR boards constructed (flight and backup) 20 Detector mounts complete and detector installed 20 Begin tes3ng structure, develop method for vibe test and test 28 Characteriza3on complete, begin prepara3on for flat sat and full mission sim test 28 Iner3al sensor model finished
Schedule
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SPRING SEMESTER (cont) Month Day Task March 1 Flat Sat tes3ng with boards and detectors
15 Full mission simula5on test (including test for detector fi\ng for WFF) 15 Begin analysis of results from full mission sim
April 1 Debugging of boards complete 1 Results of mission sim analyzed, complete system changes/modifica3ons
15 Final structures tes3ng completed (loading, preliminary vibe) 30 All tes5ng completed, finalize and complete modifica5ons
May 15 All systems ready for integra5on, begin integra5on 25 Calculate final mass, center of gravity 27 LRR slides due 31 LRR Presenta5on
June 24 LAUNCH
Estimated Budget Expenses Item Predicted Amount
Structures $350 Raw materials: Aluminum, Garolite $150 Building materials: standoffs, washers, spacers, tools
$200 CDH $650 Microcontrollers, temperature sensors, pressure sensors, regulators, ADC
$250 PCBs, spare parts, small components
$400 Mission Specialists $600 Par3cle Detectors $0 A^tude Determina3on System
$500 Addi3onal Parts (tes3ng equipment, modifica3ons to hardware)
$100 Flight $12,000 Miscellaneous $200
Total $13,800
Funding Organiza5on Amount Confirmed
Space Grant $13,000 Y
UROP $1,500 Y EEF
$2,000 N Other
n/a donated detectors
Y
Total $16,500
Colorado Space Grant Consortium RocketSat VI
72
Margin in confirmed budget: $700
Colorado Space Grant Consortium RocketSat VI
73
QUESTIONS?
Back-Up Slides
• CDH • Structures • MS • Wallops Compliance
Colorado Space Grant Consortium RocketSat VI
Low Range Accelerometer Selection
Colorado Space Grant Consortium RocketSat VI
Component
551-‐1012-‐2-‐ND (1 Axis)
551-‐1026-‐1-‐ND (1 Axis)
ADXL203CE (2 Axis)
551-‐1008-‐2-‐ND (2 Axis)
ADIS16003CCCZ-‐ND (2-‐Axis)
Range 5 3 5 5 5
Price 2 3 5 1 3
Noise 3 4 5 4 4
Voltage Supply 5 5 5 5 5
TOTAL 15 15 20 15 17
Low Range Accelerometer: ADXL203CE (2 Axis)
• Range – +/- 1.7g
• Score: 5 • Price
– 16.26$ • Score: 5
• Noise – < 4kHz, 1mv-3mv
• Score: 5 • Voltage Supply
– 3.0v – 5v • Score: 5
Colorado Space Grant Consortium RocketSat VI
Temperature Sensor Selection
Colorado Space Grant Consortium RocketSat VI
Component BD1020HFV TC07 LM50C
Range 5 4 5 Price 4 1 5 Noise 2 5 4 Voltage Supply 5 5 5
TOTAL 16 15 19
Temperature Sensor: LM50C
Range ▪ -40 ~ 125 degrees Celsius
Price ▪ $1.05
Accuracy ▪ +\- 2 degrees Celsius
Voltage Supply ▪ 0.2V~ 12V
Colorado Space Grant Consortium RocketSat VI
Pressure Sensor Selection
Colorado Space Grant Consortium RocketSat VI
Component ASDX015A24R MPXAZ4100A6-‐ND 480-‐2655-‐5-‐ND
Range 5 4 5 Price 4 4 4 Noise 5 5 3 Voltage Supply 5 5 5
TOTAL 19 18 17
Pressure Sensor: ASDX015A24R
Range ▪ 0 – 15 psi ▪ Score: 5
Price ▪ $32.09 ▪ Score: 5
Accuracy ▪ +\- 2 % V ▪ Score: 5
Voltage Supply ▪ 4.75 ~ 5.25 V ▪ Score: 5
Colorado Space Grant Consortium RocketSat VI
Regulator
• +/-12V voltage rails for op amp for current amplifier and voltage buffer
• Options: – Inverting and boost DC/DC converter from
current 9V, 5V, or 3.3V – Linear step down from 18V (2 9V in series)
to 12V – Buck and inverting regulator from 18V to
12V
Colorado Space Grant Consortium RocketSat VI
Regulator: MAX743C
• Maxim • Dual output Switch mode Regulator • Input 4.2V - 6V • Efficiency 82% • 2 outputs • Selectable +12V, +15V • Low noise
Colorado Space Grant Consortium RocketSat VI
Microcontroller (TBR)
• We will use the same microcontroller as the previous RocketSats
Colorado Space Grant Consortium RocketSat VI
CDH Back-up
• Additional options for all sensors • Additional TS for components
Colorado Space Grant Consortium RocketSat VI
Temperature Sensors
• Criteria – Range – Price – Accuracy – Voltage Supply
GRADING SYSTEM
1 2 3 4 5
Colorado Space Grant Consortium RocketSat VI
BD1020HFV
Range ▪ -30 ~ +100 degrees Celsius ▪ Score: 5
Price ▪ 64 cents ▪ Score: 4
Accuracy ▪ +\- 2 degrees Celsius ▪ Score: 2
Voltage Supply ▪ 2.4V ~ 5.5V ▪ Score: 5
Colorado Space Grant Consortium RocketSat VI
TC07
Range ▪ -40 ~ +125 degrees Celsius ▪ Score: 4
Price ▪ Call For Price ▪ Score: 1
Accuracy ▪ +\- 1 degrees Celsius ▪ Score: 5
Voltage Supply ▪ 2.7V ~ 5.5V ▪ Score: 5
Colorado Space Grant Consortium RocketSat VI
Pressure Sensors
• Criteria – Range – Price – Accuracy – Voltage Supply
GRADING SYSTEM
1 2 3 4 5
Colorado Space Grant Consortium RocketSat VI
MPXAZ4100A6U-ND
Range ▪ 2.9 – 15.2 psi ▪ Score: 4
Price ▪ $12.37 ▪ Score: 4
Accuracy ▪ +\- 1.8 % V ▪ Score: 5
Voltage Supply ▪ 4.85 ~ 5.35 V ▪ Score: 5
Colorado Space Grant Consortium RocketSat VI
480-2655-5-ND
Range ▪ 0 – 15 psi ▪ Score: 5
Price ▪ $23.50 ▪ Score: 4
Accuracy ▪ +\- 1 % V ▪ Score: 5
Voltage Supply ▪ 3 ~ 12 V ▪ Score: 5
Colorado Space Grant Consortium RocketSat VI
Flash Memory
• Criteria – Size – Speed – Interface – Price
GRADING SYSTEM
1 2 3 4 5
Colorado Space Grant Consortium RocketSat VI
AT25DF161-SH-T-ND
Size ▪ 16 M ▪ Score: 4
Speed ▪ 100 MHz ▪ Score: 5
Interface ▪ SPI, RapidS ▪ Score: 4
Price ▪ $1.29 ▪ Score: 5
Colorado Space Grant Consortium RocketSat VI
AT26DF081A-SU-ND
Size ▪ 8 M ▪ Score: 3
Speed ▪ 70 MHz ▪ Score: 4
Interface ▪ SPI, 3-Wire Serial ▪ Score: 4
Price ▪ $1.30 ▪ Score: 4.9
Colorado Space Grant Consortium RocketSat VI
Accelerometers
• Criteria – Range – Price – Noise – Voltage Supply
GRADING SYSTEM
1 2 3 4 5
Colorado Space Grant Consortium RocketSat VI
551-1012-2-ND(1 Axis) – Low Range
• Range – +/- 1.7g
• Score: 5 • Price
– 32.60$ • Score: 2
• Noise – 1mv-3mv
• Score: 3 • Voltage Supply
– 0.3v – 7.0v • Score: 5
Colorado Space Grant Consortium RocketSat VI
551-1026-1-ND (1 Axis) – Low Range
• Range – +/- 1.5g
• Score: 3 • Price
– 15.95$ • Score: 3
• Noise – 1mv-3mv
• Score: 4 • Voltage Supply
– 4.75– 5.25v • Score: 5
Colorado Space Grant Consortium RocketSat VI
551-1008-2-ND (2 Axis) – Low Range
• Range – +/- 1.7g
• Score: 5 • Price
– 55.31$ • Score: 1
• Noise – 80 Hz
• Score: 4 • Voltage Supply
– 4.75v – 5.25v • Score: 5
Colorado Space Grant Consortium RocketSat VI
ADIS16003CCCZ-ND (2-Axis) – Low Range
• Range – +/- 1.7g
• Score: 5 • Price
– 33.02$ • Score:3
• Noise – 80 Hz
• Score: 4 • Voltage Supply
– 3v – 5.25v • Score: 5
Colorado Space Grant Consortium RocketSat VI
AD22280-R2TR-ND (1-Axis) – High Range
• Range – +/- 50g
• Score: 3 • Price
– 9.02$ • Score: 5
• Noise – 10Hz – 400 Hz
• Score: 5 • Voltage Supply
– 5v • Score: 5
Colorado Space Grant Consortium RocketSat VI
High Range Accelerometer
Colorado Space Grant Consortium RocketSat VI
Component
AD22280-‐R2TR-‐ND (1-‐Axis)
AD22281-‐R2CT-‐ND (1-‐Axis)
ADIS16204BCCZ-‐ND (2-‐Axis)
AD22285-‐R2TR-‐ND (2-‐Axis)
AD22284-‐A-‐R2CT-‐ND (2-‐Axis)
Range 3 5 2 3 5
Price 5 4 2 5 5
Noise 5 5 5 5 5 Voltage Supply 5 5 5 5 5
TOTAL 18 19 14 18 20
ADIS16204BCCZ-ND (2-Axis) – High Range
• Range – +/- 70g, 35g
• Score: 2 • Price
– 37.88$ • Score: 2
• Noise – 10Hz – 400 Hz
• Score: 5 • Voltage Supply
– 3.0 – 3.6 • Score: 5
• Shock Resistant
Colorado Space Grant Consortium RocketSat VI
AD22285-R2TR-ND (2-Axis) – High Range
• Range – +/- 50g
• Score: 3 • Price
– 15.95$ • Score: 5
• Noise – 10Hz – 400 Hz
• Score: 5 • Voltage Supply
– 5V • Score: 5
Colorado Space Grant Consortium RocketSat VI
598-1100-5-ND
• 16 bits – Score: 5
• Throughput 200kSPS – Score: 5
• Input analog signal 0-2.5, +/-2.5V – Score: 2
• Either 5V or 3.3Vsupply – Score: 5
• 2 input channels if 0-5V – Score: 3
• 2.25 mW maximum dissipation – Score: 3
• –40°C to +85°C – Score: 5
• Package N-28 DIP or R-28 SOIC – Score: 5
Colorado Space Grant Consortium RocketSat VI
AD7884AP-ND
• 16 bits – Score: 5
• Throughput 160kSPS – Score: 3
• Input analog signal 0-2.5, +/-2.5V – Score: 2
• Either 5V or 3.3Vsupply – Score: 4
• 2 input channels if 0-5V – Score: 3
• 32.5 mW maximum dissipation – Score: 4
• –40°C to +85°C – Score: 5
• Package N-28 DIP or R-28 SOIC – Score: 5
Colorado Space Grant Consortium RocketSat VI
DCP010512DBP
• Texas Instruments • Isolated Unregulated DC/DC converter • Input 4.5 – 5.5V • +V and –V output • 1W, 82% efficiency • +/-12V output • Ripple 20mVpp • Operating -40-100oC • Package PDIP vs SOP • line regulation max 15%
Colorado Space Grant Consortium RocketSat VI
TPS65131
• Texas Instrument • Positive and Negative DC/DC converter • Vpos =15V, Vneg = -15V • DC output accuracy 3%
Colorado Space Grant Consortium RocketSat VI
LM7912
• National Instruments • Fixed Linear regulator -12V • Less efficient • Input :-18 to -30V
– 2
Colorado Space Grant Consortium RocketSat VI