The BRASS Project The BRASS Project University of North Dakota 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 Critical Design Review
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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.
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.