CDR_NorthDakota by hedongchenchen

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									   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       Status
The vessels must maintain pressure during ascent.             Design,
                                                              Test
The vessels must be fully purged at apogee. Specifically      Design,
the biological payload first, followed by the remaining gas   Test
sensor vessels.
The vessels must maintain vacuum when evacuated.              Design,
                                                              Test
The microcontroller and subsequent electronics must be        Design,
turned on at lift off by the use of a RBF pin and G-Switch.   Test,
                                                              Simulation
Nonconductive, no out gassing tubing used.                    Design
           Payload Requirements Matrix
                  Payload Requirements                                           Method          Status
The payload center of gravity (CG) for half canister shall be within 1” of the   Design
geometric central axis of the half ICU. (current simulations show within ½”)
The allowable physical envelope of the canister is a cylindrical right prism     Design
with a diameter of 9.2” and a height of 4.7” for half canister customers
The payload must not exceed a weight of 6.375 lbs                                Design,
Current Payload weight : 5.0683 lbs                                              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                               Design, Test
objectives. Terrier-Orion default plumbing internal volume
not known hence the status is partially compliant.

Stress, Cracking, Corrosion (SCC) analysis.                                      Design,
                                                                                 Simulation
    Payload Function Diagram
               1       1. Electrical subsystem
                           •   Batteries
                           •   Remove Before Flights
                           •   G-Switches
                           •   PIC micro controller
                           •   Data logging
                           •   Analog switch
    3
                       2. Sensors subsystem
                           • Nanocrystalline Oxide
                             semiconductors
                   2
                           • Vacuum vessels
                       3. Solenoid subsystem
                       4. Particle counter subsystem
4
                           •   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               Model
Flow selection Solenoid valve Bio-Chem valve Inc.   080T81232
Tubing (PTFE)                 Bio-Chem Fluidics     008716-080-20
Omnilok- Type P Fitting       Bio-Chem Fluidics     008NF16-YC5
                                                    P Type ferrule-
                                                    008FT16
Temperature Sensor           HoneyWell              HEL-705-T-0-12-00
Pressure Sensor              Intersema              MS5534B
RS232 Connection             Maxim-IC               MAX232A
EEPROM                       Microchip Inc.         25LC1024
A/D Voltage Conditioner      Analog Devices         AD621
Multiplexer                  Maxim-IC               MAX305
PIC Microcontroller          Microchip Inc.         PIC18F4520
Voltage Regulator            Microchip Inc.         MCP1541
           BRASS Team Management
                                                 Mentor Team lead
                                                     Ron Fevig

                                             Student Team Lead
                                                Matthew Voigt




                                                                General Guru of
                               Physics Advisor
                                                                  Electronics
                                 Tim Young
                                                                  John Nordlie




                                                                Sensor Specialist
                              Particle Detector
                                                                    Dr. Patel
                                 Specialist
                                David Delene




Student Sensor                                                            Atmospheric Sciences
                 Electrical Engineer        Mechanical Engineer
   Specialist                                                               and secondary EE     Biological Payload
                   Joshua Peterson            Telang Kaiwalya
 Nathan Ambler                                                                Gökhan Sever           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

								
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