RocketSat VI · •Magic Sounding Rocket –Goal: to answer questions about the properties of smoke –Used dust detectors to direct measure the meteoric smoke particles •Other

RocketSat VI Preliminary Design Review

CU Boulder October 28, 2009

Colorado Space Grant Consortium RocketSat VI

Team Organization


2

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


3

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


4

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.


5

Mission Overview: Science

•  Particle Size –  Formation near 88km –  Particles Descend and

increase in size as more water is frozen to the exterior


6

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


7

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


8

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


9

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


10

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


11

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


12

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


13

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


14

Testing

•  Calibration of current amplifier •  Test detectors, make sure they function

properly •  Test magnetometers

– Create a model of results that magnetometer will provide


15

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)


16

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


17

Project Requirements


18

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


19

Concept of Operations


20

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


21

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


22

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


23

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)


24

Design Driver: Detector

•  All detectors need direct exposure to environment

•  Depending on detector, payload layout must be adjusted, changes data analysis


25

Faraday Cup Mass Spectrometer Patch Detector

Large Particle Detector Selection


26

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


27

Al cup

Magnets

Plastic insert Graphite patch

Iron base plate

Connector

Attitude Determination System


28

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


29

System Layout


30

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


31

CDH Subsystem Requirements


32

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.


33

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


34

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 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


Flash Memory Selection


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


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


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


43

Wallops RBF Interface

AVR


44

AVR PCB


45

Current Amplifier


46

Science Board


47

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


48

Software Flow Chart


49

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


50

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


51

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

RocketSat VI 52

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


53

Structures Subsystem Requirements


54

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


55

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


56

Payload Layout


Batteries

Particle Board

Inertia Sensor

Accelerometer

AVR

Electronics Stack


Sensors


Particle Sensor

Inertia Sensor

Mass Estimation


60

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


61

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)


62

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


63

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


64

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


65

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


66

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


67

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


Schedule


69

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


70

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


71

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


72

Margin in confirmed budget: $700


73

QUESTIONS?

Back-Up Slides

•  CDH •  Structures •  MS •  Wallops Compliance


Low Range Accelerometer Selection


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


Temperature Sensor Selection


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


Pressure Sensor Selection


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


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


Regulator: MAX743C

•  Maxim •  Dual output Switch mode Regulator •  Input 4.2V - 6V •  Efficiency 82% •  2 outputs •  Selectable +12V, +15V •  Low noise


Microcontroller (TBR)

•  We will use the same microcontroller as the previous RocketSats


CDH Back-up

•  Additional options for all sensors •  Additional TS for components


Temperature Sensors

•  Criteria – Range – Price – Accuracy – Voltage Supply

GRADING SYSTEM

1 2 3 4 5


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


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


Pressure Sensors

•  Criteria – Range – Price – Accuracy – Voltage Supply

GRADING SYSTEM

1 2 3 4 5


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


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


Flash Memory

•  Criteria – Size – Speed – Interface – Price

GRADING SYSTEM

1 2 3 4 5


AT25DF161-SH-T-ND

 Size ▪  16 M ▪  Score: 4

 Speed ▪  100 MHz ▪  Score: 5

  Interface ▪  SPI, RapidS ▪  Score: 4

 Price ▪  $1.29 ▪  Score: 5


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


Accelerometers

•  Criteria – Range – Price – Noise – Voltage Supply

GRADING SYSTEM

1 2 3 4 5


551-1012-2-ND(1 Axis) – Low Range

•  Range –  +/- 1.7g


–  32.60$ •  Score: 2

•  Noise –  1mv-3mv


–  0.3v – 7.0v •  Score: 5


551-1026-1-ND (1 Axis) – Low Range

•  Range –  +/- 1.5g


–  15.95$ •  Score: 3

•  Noise –  1mv-3mv


–  4.75– 5.25v •  Score: 5


551-1008-2-ND (2 Axis) – Low Range

•  Range –  +/- 1.7g


–  55.31$ •  Score: 1

•  Noise –  80 Hz


–  4.75v – 5.25v •  Score: 5


ADIS16003CCCZ-ND (2-Axis) – Low Range

•  Range –  +/- 1.7g


–  33.02$ •  Score:3

•  Noise –  80 Hz


–  3v – 5.25v •  Score: 5


AD22280-R2TR-ND (1-Axis) – High Range

•  Range –  +/- 50g


–  9.02$ •  Score: 5

•  Noise –  10Hz – 400 Hz


–  5v •  Score: 5


High Range Accelerometer


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


–  37.88$ •  Score: 2

•  Noise –  10Hz – 400 Hz


–  3.0 – 3.6 •  Score: 5

•  Shock Resistant


AD22285-R2TR-ND (2-Axis) – High Range

•  Range –  +/- 50g


–  15.95$ •  Score: 5

•  Noise –  10Hz – 400 Hz


–  5V •  Score: 5


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


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


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%


TPS65131

•  Texas Instrument •  Positive and Negative DC/DC converter •  Vpos =15V, Vneg = -15V •  DC output accuracy 3%


LM7912

•  National Instruments •  Fixed Linear regulator -12V •  Less efficient •  Input :-18 to -30V

– 2


Documents

RocketSat VI · •Magic Sounding Rocket –Goal: to answer questions about the properties of smoke –Used dust detectors to direct measure the meteoric smoke particles •Other