The BRASS ProjectThe BRASS Project

University of North DakotaUniversity of North DakotaMatthew VoigtNathan Ambler

Ron FevigJohn NordlieTim Young

Nirmal Patel (University of North Florida)Baike Xi

Joshua PetersonDavid DeleneLen Hillhouse

Telang KaiwalyaGökhan Sever

December 16th, 2008

Balloon and Rocket Atmospheric Sampling and Sensing

Critical Design ReviewCritical Design Review

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 OverviewMission 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 OverviewMission Overview

•The theory of the payloadNanocrystalline 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 OverviewMission Overview

The theory of the dataThe 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.

Mission OverviewMission Overview

Scientific Requirements MatrixScientific Requirements Matrix

Scientific Requirements Method Status

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

Payload Requirements MatrixPayload Requirements MatrixPayload Requirements Method Status

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 customersDesign

The payload must not exceed a weight of 6.375 lbsCurrent 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

2

1

3

4

1. Electrical subsystem

• 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. Particle counter subsystem

• Optical particle counter

Payload Function DiagramPayload Function Diagram

Payload Mechanical DesignPayload 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.

Canister and payload assembly

Interfacing details with canister bottom bulk headand the sharing customer

Payload height for half canister = 4.7”

Payloadexploded view

Main Electrical Schematics Main Electrical Schematics View View

Analog and Serial Analog and Serial Interfacing SchematicsInterfacing Schematics

Sensor Interfacing Sensor Interfacing SchematicsSchematics

Main Controller CircuitryMain Controller Circuitry

Power Interface Power Interface SchematicsSchematics

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

Subsystems OverviewSubsystems Overview

Parts Company ModelFlow selection Solenoid valve Bio-Chem

valve Inc.

080T81232Tubing (PTFE)

Bio-Chem

Fluidics

008716-080-20Omnilok-

Type P Fitting

Bio-Chem

Fluidics

008NF16-YC5P Type ferrule-

008FT16

Temperature Sensor

HoneyWell

HEL-705-T-0-12-00Pressure Sensor

Intersema

MS5534B RS232 Connection Maxim-IC

MAX232AEEPROM Microchip Inc.

25LC1024A/D Voltage Conditioner Analog Devices

AD621Multiplexer Maxim-IC MAX305 PIC Microcontroller

Microchip Inc. PIC18F4520Voltage Regulator Microchip Inc.

MCP1541

Parts ListParts List

Mentor Team leadRon Fevig

Student Team LeadMatthew Voigt

Mentor Team leadRon Fevig

Student Team LeadMatthew Voigt

Student Sensor Specialist

Nathan Ambler

Student Sensor Specialist

Nathan AmblerElectrical Engineer

Joshua PetersonElectrical Engineer

Joshua PetersonMechanical Engineer

Telang KaiwalyaMechanical Engineer

Telang KaiwalyaAtmospheric Sciences

and secondary EEGökhan Sever

Atmospheric Sciences and secondary EE

Gökhan Sever Biological Payload

SpecialistLen Hillhouse

Biological Payload Specialist

Len Hillhouse

Physics AdvisorTim Young

Physics AdvisorTim Young

General Guru of ElectronicsJohn Nordlie

General Guru of ElectronicsJohn Nordlie

Particle Detector Specialist

David Delene

Particle Detector Specialist

David Delene

Sensor SpecialistDr. Patel

Sensor SpecialistDr. Patel

BRASS Team ManagementBRASS Team Management

Testing Plans- MechanicalComputer 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 FailureParticle counter being vacuum readyComputer can lock up and stop running (soft errors)

Test PlansTest Plans

–

Issues and concernsPossibility of flightPlumbing volume in rocketArgon gas ventingBattery chemistryCoordination with canister partner Apogee detection

Issues and ConcernsIssues and Concerns