1. The BRASS Project 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 16 th, 2008 Balloon and Rocket Atmospheric Sampling and Sensing Critical Design Review

2. 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

3. 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

4. The theory of the payload Nanocrystalline Oxide semiconductors such as Indium-tin oxide s olid 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

5. 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. Mission Overview

6. Scientific Requirements Matrix Scientific RequirementsMethodStatus 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

7. Payload Requirements Matrix Payload RequirementsMethodStatus 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

8. 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 Diagram

9. 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.

10. Canister and payload assembly Interfacing details with canister bottom bulk head and the sharing customer

11. Payload height for half canister = 4.7”

12. Payload exploded view

13. Main Electrical Schematics View

14. Analog and Serial Interfacing Schematics

15. Sensor Interfacing Schematics

16. Main Controller Circuitry

17. Power Interface Schematics

18. 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 Overview

19. Parts CompanyModel Flow selection Solenoid valve Bio-Chem valve Inc.080T81232 Tubing (PTFE)Bio-Chem Fluidics008716-080-20 Omnilok- Type P FittingBio-Chem Fluidics008NF16-YC5 P Type ferrule- 008FT16 Temperature SensorHoneyWellHEL-705-T-0-12-00 Pressure Sensor IntersemaMS5534B RS232 Connection Maxim-ICMAX232A EEPROM Microchip Inc.25LC1024 A/D Voltage Conditioner Analog DevicesAD621 Multiplexer Maxim-ICMAX305 PIC MicrocontrollerMicrochip Inc. PIC18F4520 Voltage Regulator Microchip Inc.MCP1541 Parts List

20. Mentor Team lead Ron Fevig Student Team Lead Matthew Voigt Student Sensor Specialist Nathan Ambler Electrical Engineer Joshua Peterson Mechanical Engineer Telang Kaiwalya Atmospheric Sciences and secondary EE Gökhan Sever Biological Payload Specialist Len Hillhouse Physics Advisor Tim Young General Guru of Electronics John Nordlie Particle Detector Specialist David Delene Sensor Specialist Dr. Patel BRASS Team Management

21. Testing Plans- Mechanical Computer simulations for SCC – Monday January 21 st Mass Moment of Inertia Testing – Monday April 7 th Vibration table testing – looking into UND’s abilities – Monday April 14 th Pressure/Vacuum, Testing – Monday April 21 st Temperature Testing – Monday April 28 th Day in the Life Testing Event – Monday May 12 th Testing Plans – Electrical Prototype Friday February 18 th Working Circuit Tuesday March 3 rd Manufacture Printed Circuit Tuesday March 17 th Populated Circuit board Tuesday March 31 st Potential Points of Failure Particle counter being vacuum ready Computer can lock up and stop running (soft errors) Test Plans

22. –Issues and concerns Possibility of flight Plumbing volume in rocket Argon gas venting Battery chemistry Coordination with canister partner Apogee detection Issues and Concerns