Transcript Team Name - Colorado Space Grant Consortium

The BRASS Project
Balloon and Rocket Atmospheric Sampling and Sensing
Critical Design Review
University of North Dakota
Matthew Voigt
Nathan Ambler
Ron Fevig
John Nordlie
Tim Young
Nirmal Patel (University of North Florida)
Baike Xi
Joshua Peterson
David Delene
Len Hillhouse
Telang Kaiwalya
Gökhan Sever
December 16th, 2008
Mission Overview
The Objective
• The altitude of the mesosphere is from 50 km to approximately 90 km.
The mesosphere is a poorly studied layer of the atmosphere since it is
too high for an aircraft or balloon and too low for an orbiting spacecraft.
– To measure concentrations of H2, Ch4, CO (reducing)*, O3, O2, N2O
(oxidizing)*, in the mesosphere in nearly real-time using
nanocrystalline oxide semiconductor sensors arrays and also
simultaneously obtain information on the magnetic field strength.
• Furthermore two additional payloads are being integrated
• To measure the number of particulates in the air, using a particle counter
• To inspect the ‘hardiness’ of cellular material by using lettuce sprouts
* Currently we are addressing which of these six will be measured.
Mission Overview
To Prove
– Capability of in-situ atmospheric measurements on sounding rockets
which has already been proven successful on high altitude balloons.
To Discover
– The relative amounts of H2, Ch4, CO (reducing)*, O3, O2, N2O
(oxidizing)*, gasses in the mesosphere.
Related Research
– Nanocrystalline solid state gas sensor arrays developed and
fabricated by Dr. Nirmal Patel at University of North Florida
(U.S. patent pending) had three balloon flights so far:
• 2007 in Florida (telemetry issues)
• 2008 in North Dakota (telemetry issues)
• 2008 HASP – successful flight and data obtained
Mission Overview
•The theory of the payload
Nanocrystalline Oxide semiconductors such as Indium-tin oxide solid state
sensor arrays with different types of catalytic layers and stimulators for the
detection of specific gases. Sensors will be calibrated in the lab. Also, a
selectivity algorithm will be determined.
Change in the electrical resistance with respect to change in the concentration
of gas gives the electrical signal for the sensors.
Resistance values will be recorded using a flash memory. After data recovery
and analysis, the concentration of different gases will be determined using the
calibrated plots and selectivity algorithm.
Some of the particulate will be collected on the adhesive surface of tape. The
morphology of particulate will be examined using scanning electron microscope
(SEM), while chemical composition will be determined using energy dispersive
analysis of x-rays (EDAX).
The bio payload will undergo decompression, exposing the payload to vacuum.
Mission Overview
The theory of the data
The data can assist to the models of our current atmosphere.
The surface morphology of sensors before launch and after recovery will
be examined using SEM, while EDAX will be used to check the chemical
composition of the surface of sensors.
The particle counter uses a laser which interacts with the particulates that
pass by, scattering the light downward onto the optical sensor, measuring
the particulate.
Scientific Requirements Matrix
Scientific Requirements
Method
The vessels must maintain pressure during ascent.
Design,
Test
The vessels must be fully purged at apogee. Specifically
the biological payload first, followed by the remaining gas
sensor vessels.
Design,
Test
The vessels must maintain vacuum when evacuated.
Design,
Test
The microcontroller and subsequent electronics must be
turned on at lift off by the use of a RBF pin and G-Switch.
Design,
Test,
Simulation
Nonconductive, no out gassing tubing used.
Design
Status
Payload Requirements Matrix
Payload Requirements
Method
The payload center of gravity (CG) for half canister shall be within 1” of the
geometric central axis of the half ICU. (current simulations show within ½”)
Design
The allowable physical envelope of the canister is a cylindrical right prism
with a diameter of 9.2” and a height of 4.7” for half canister customers
Design
The payload must not exceed a weight of 6.375 lbs
Current Payload weight : 5.0683 lbs
Design,
analysis
Payload to comply with WFF “No Volt” requirements.
Design,
Analyze, Test
Payload components must be resistant of 20G loads in all Axes.
Design,
Simulation
Payload component exhibit thermal compliance.
Design, Test
Wire Harnesses.
Design, Test
The payload must be capable of meeting all mission
objectives. Terrier-Orion default plumbing internal volume
not known hence the status is partially compliant.
Design, Test
Stress, Cracking, Corrosion (SCC) analysis.
Design,
Simulation
Status
Payload Function Diagram
1
1. Electrical subsystem
3
2
•
Batteries
•
Remove Before Flights
•
G-Switches
•
PIC micro controller
•
Data logging
•
Analog switch
2. Sensors subsystem
• Nanocrystalline Oxide
semiconductors
• Vacuum vessels
3. Solenoid subsystem
4
4. Particle counter subsystem
•
Optical particle counter
Payload Mechanical Design
The assembly was created using ProE Wildfire 4.0. Payload assembly
shown in the next couple of slides comprises of different materials.
Green: PCB, Sky Blue (dull): Subassembly of different materials, Navy
blue (dark): Steel components, Metallic gray: Al 6061, Transparent
gray: Polycarbonate plates.
Payload height and interfacing are illustrated and explained on the
following figures.
All the structural components will be manufactured in-house.
Interfacing details with canister bottom bulk head
and the sharing customer
Canister and payload
assembly
Payload height for half canister = 4.7”
Payload
exploded view
Main Electrical Schematics
View
Analog and Serial
Interfacing Schematics
Sensor Interfacing
Schematics
Main Controller Circuitry
Power Interface
Schematics
Subsystems Overview
Subsystem power and temperature ranges
– Solenoid Valves
• Power requirements 24 VDC
• Thermal ranges- -0.4°C – 50°C
– Particle Counter
• Power requirements 11-15 VDC at 450 mA
• Thermal ranges 0° to 50° C
– TC72-2.8MUA Temperature Sensor
• Power requirements 5 V at 250 μA
• Thermal ranges -55° to 125° C (+/- 3° C)
– Honeywell HEL-705-T-0-12-00 Temperature Sensor
• -200 °C to 260 °C temperature range
– Intersema MS5534B Pressure Sensor
• Power Requirements: 2.2-3.6 V at 1 mA
• –40° C to 125° C
Parts List
Parts
Company
Flow selection Solenoid valve Bio-Chem valve Inc.
Tubing (PTFE)
Bio-Chem Fluidics
Omnilok- Type P Fitting
Bio-Chem Fluidics
Temperature Sensor
Pressure Sensor
RS232 Connection
EEPROM
A/D Voltage Conditioner
Multiplexer
PIC Microcontroller
Voltage Regulator
HoneyWell
Intersema
Maxim-IC
Microchip Inc.
Analog Devices
Maxim-IC
Microchip Inc.
Microchip Inc.
Model
080T81232
008716-080-20
008NF16-YC5
P Type ferrule008FT16
HEL-705-T-0-12-00
MS5534B
MAX232A
25LC1024
AD621
MAX305
PIC18F4520
MCP1541
BRASS Team Management
Mentor Team lead
Ron Fevig
Student Team Lead
Matthew Voigt
Physics Advisor
Tim Young
Particle Detector
Specialist
David Delene
Student Sensor
Specialist
Nathan Ambler
Electrical Engineer
Joshua Peterson
General Guru of
Electronics
John Nordlie
Sensor Specialist
Dr. Patel
Mechanical Engineer
Telang Kaiwalya
Atmospheric Sciences
and secondary EE
Gökhan Sever
Biological Payload
Specialist
Len Hillhouse
Test Plans
Testing Plans- Mechanical
Computer simulations for SCC – Monday January 21st
Mass Moment of Inertia Testing – Monday April 7th
Vibration table testing – looking into UND’s abilities – Monday April 14th
Pressure/Vacuum, Testing – Monday April 21st
Temperature Testing – Monday April 28th
Day in the Life Testing Event – Monday May 12th
Testing Plans – Electrical
Prototype Friday February 18th
Working Circuit Tuesday March 3rd
Manufacture Printed Circuit Tuesday March 17th
Populated Circuit board Tuesday March 31st
Potential Points of Failure
Particle counter being vacuum ready
Computer can lock up and stop running (soft errors)
Issues and Concerns
– Issues and concerns
Possibility of flight
Plumbing volume in rocket
Argon gas venting
Battery chemistry
Coordination with canister partner
Apogee detection